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Chelomei mobile-launched short range cruise missile derived from the German V-1. Did not reach production.
10KhN.
Manufacturer's designation for 10Kh short range cruise missile.
11A510.
Article Number of Vostok 11A510 orbital launch vehicle.
11A511.
Article Number of Soyuz 11A511 orbital launch vehicle.
11A511L.
Article Number of Soyuz 11A511L orbital launch vehicle.
11A511M.
Article Number of the Soyuz 11A511M orbital launch vehicle. Reapplied 40 years later to the Soyuz M orbital launch vehicle.
11A511U.
Article Number of Soyuz 11A511U orbital launch vehicle.
11A511U2.
Article Number of Soyuz 11A511U2 orbital launch vehicle.
Russian intercontinental ballistic missile. FOBS version. Warhead accuracy 5 km along orbital track, 3 km to either side. OKB-1 estimated warhead would be detected by Western defences only two minutes before it detonated. The designation SS-10 was assigned by the DOD to the UR-200, but was commonly and erroneously applied to the GR-1, which was shown publicly after its cancellation.
11A514.
Article Number of Soyuz 11A514 orbital launch vehicle.
11A52.
11A53.
11A54.
Article Number of N111 heavy-lift orbital launch vehicle.
11A57.
Article Number of Voskhod 11A57 orbital launch vehicle.
11A59.
Article Number of Sputnik 11A59 orbital launch vehicle.
11K25.
Article Number of Energia winged orbital launch vehicle.
11K54.
Complex of N111 heavy-lift orbital launch vehicle.
11K55.
Article Number of Soyuz 11K55 orbital launch vehicle.
11K56.
Article Number of Soyuz 11K56 orbital launch vehicle.
11K63.
Article Number of Kosmos 11K63 orbital launch vehicle.
11K64.
Article Number of 64S5 intercontinental ballistic missile.
11K65.
Article Number of Kosmos 11K65 orbital launch vehicle.
11K65M.
Article Number of Kosmos 11K65M orbital launch vehicle.
11K67.
Article Number of Tsiklon-2A orbital launch vehicle.
11K68.
Article Number of Tsiklon-3 orbital launch vehicle.
11K69.
Article Number of Tsiklon-2 orbital launch vehicle.
11K77.
Article Number of Zenit-2 orbital launch vehicle.
15A10.
15A11.
Article Number of Perimetr 15A11 strategic communications missile.
15A14.
Article Number of R-36M intercontinental ballistic missile.
15A15.
Article Number of MR-UR-100 intercontinental ballistic missile.
15A16.
Article Number of MR-UR-100U 15A16 intercontinental ballistic missile.
15A18.
Article Number of R-36MU 15A18 intercontinental ballistic missile.
15A18M2.
Article Number of R-36M2 15A18M intercontinental ballistic missile and Dnepr space launch vehicle.
15A20.
Article Number of UR-100K intercontinental ballistic missile.
15A20U.
Article Number of UR-100U intercontinental ballistic missile.
15A30.
Article Number of UR-100N intercontinental ballistic missile and Strela and Rokot space launch vehicles.
15A35.
Article Number of UR-100NU intercontinental ballistic missile.
15B86.
Standard RV of R-36M intercontinental ballistic missile.
15F1.
Standard RV of RT-2 intercontinental ballistic missile.
15F173.
Standard RV of R-36M2 15A18M intercontinental ballistic missile.
15F183.
Standard RV of R-36MU 15A18 intercontinental ballistic missile.
15F842.
Standard RV of UR-100 and UR-100M SLBM intercontinental ballistic missiles.
15P015.
Launch System of MR-UR-100 intercontinental ballistic missile.
15P016.
Launch System of MR-UR-100U 15A16 intercontinental ballistic missile.
15P020.
Launch System of UR-100U intercontinental ballistic missile.
15P030.
Launch System of UR-100N missile.
15P035.
Launch System of UR-100NU intercontinental ballistic missile.
15P084.
Launch System of UR-100M missile.
15P098.
Launch System of RT-2 intercontinental ballistic missile.
15P098P.
Launch System of RT-2P intercontinental ballistic missile.
15P696.
Launch System of RT-15 intermediate range ballistic missile.
15P784.
15P884.
Launch System of UR-100K intercontinental ballistic missile.
15Zh41.
Article Number of RT-21 intercontinental ballistic missile.
15Zh42.
Article Number of Temp-2S intercontinental ballistic missile.
15Zh44.
Article Number of RT-23 15Zh44 intercontinental ballistic missile.
Russian intermediate range ballistic missile. The missile was given a different DOD mod designation according to the number of warheads - Mod 1 for the single warhead version, Mod 2 for the triple warhead version.
Russian intermediate range ballistic missile. The UTTKh model featured improved accuracy, range, and MIRV dispersal spread. It was not given a separate DoD 'mod' number.
15Zh52.
Article Number of RT-23 15Zh52 intercontinental ballistic missile.
Russian intermediate range ballistic missile. Development of a modernised version of the 15Zh45 IRBM began at the beginning of the 1980's. Flight trials either began in 1985 or were cancelled prior to their planned start in 1986. In 1988 the project was cancelled following the signature of the INF Treaty that banned intermediate range ballistic missiles. The missile (known to the Pentagon as both the SS-20 Mod 3 and the SS-28) would have had a range of 7500 km with a single warhead, or 5500 km with multiple warheads.
Compared to the Pioner-U it used a larger launch container, a larger MIRV bus with greater accuracy. The KB Minsk Auto Factory developed a lighter, more comfortable crew cabin - important on constant field deployments.
15Zh58.
Article Number of Topol intercontinental ballistic missile, and Start and Start-1 orbital launch vehicles.
15Zh60.
Article Number of RT-23U 15Zh60 intercontinental ballistic missile.
15Zh61.
Article Number of RT-23U 15Zh61 intercontinental ballistic missile.
17D.
Russian surface-to-air missile. Prototype air-breathing surface-to-air missile, using air-augmented solid propellant.
A small two stage to orbit horizontal takeoff / horizontal landing vehicle proposed for the Russian Air Force in 1993.
18D.
Russian surface-to-air missile. Variant of the 18D air-breathing surface-to-air missile using a magnesium alloy in the fuel to double the initial launch thrust.
205.
Standard warhead of Tu-121 intermediate range cruise missile, Tu-123 intercontinental boost-glide missile, and Tu-133 intercontinental cruise missile.
205.
Russian surface-to-air missile. Original missile of the S-25 system, development described above.
206.
Russian surface-to-air missile. The 206 was a version of the 205 using a single-chamber Isayev engine in place of the four-chamber design of the 205. Cancelled in April 1953.
207.
Russian surface-to-air missile. This was an improvement of the 205 with an improved warhead and reduced cruise thrust. Trials were conducted of the missile in 1953, but it was decided not to put it into service.
207A.
Russian surface-to-air missile. The 207A, with numerous improvements to the 205 which had been developed in a crash program, completed trials in 1955 and rapidly replaced the 205 in PVO service. It basically doubled all of the performance characteristics of the 205.
207T.
Russian surface-to-air missile. The 207T was an alternative derivative of the 207A with a nuclear warhead. It was developed during 1958 but does not seem to have entered service.
208.
Russian surface-to-air missile. In this version of the V-300 the warhead was increased to 430 kg to compensate for accuracy problems in the original production version. Cancelled in favour of the 207A.
212.
Russian air-to-surface missile. Korolev's second design for a rocket-propelled cruise missile. It was flight tested twice after his arrest in 1939 but work was then abandoned.
215.
Russian surface-to-air missile. The 215 was a derivative of the 207A with a nuclear warhead. It entered service in 1957.
217.
Russian surface-to-air missile. The 217 was a version of the V-300 with a variable thrust engine. Entered production.
First anti-aircraft missile flown in the USSR. The 217/I had a conventional aircraft layout, with a main wing and aerodynamic control surfaces on the tail.
Pre-World War II anti-aircraft missile flown in the USSR. The 217/II follow-on to the 217/I had the first 'rocket' layout - four small wings, each all-moving.
217M.
Russian surface-to-air missile. Developed together with the improved S-25M missile system, the 217M entered production and gave the S-25 an enormous performance in improvement.
218.
Russian surface-to-air missile. The 218 was a version of the 217M with a nuclear warhead, which entered service in 1964.
22D.
Russian surface-to-air missile. Prototype surface-to-air missile, using liquid-propellant ramjets in place of the air-augmented solid propellant of the 17D.
2K11.
Article Number of Krug surface-to-air missile.
2K12.
Complex of Kub surface-to-air missile.
2K6.
3 stage vehicle consisting of 1 x TX-500 + 1 x TX-454 + 1 x TX-239.
Alternate designation for Spartan anti-ballistic missile.
32B.
Russian surface-to-air missile. Alternate missile developed for the S-25 system. Technically superior but not put into production, it led to the S-75 and later Soviet surface-to-air missiles.
3M17.
Article Number of R-31 submarine launched ballistic missile.
3M20.
Russian submarine-launched ballistic missile. First flight 1979. Four unsuccessful tests in 1980, two successful in 1981. Development completed 1983. SLBM on Typhoon subs.
3M30.
Missile of Bulava intercontinental ballistic missile.
3M37.
Missile of R-29RM submarine-launched ballistic missile.
3M40.
Missile of R-29R submarine-launched ballistic missile.
3M41.
Alternate Designation of S-300F surface-to-air missile.
3M65.
Missile of R-29RL submarine-launched ballistic missile.
3M65.
First flight 1983. As of March 1986 only Russian SLBM in production.
3M9.
Alternate designation for Kub surface-to-air missile.
3M91.
3M9M / 9M9.
Missile of Kub surface-to-air missile.
3R1.
Article Number of Mars tactical ballistic rocket.
3R10.
Russian tactical ballistic rocket.
3R2.
Article Number of Filin tactical ballistic rocket.
3R65.
Article Number of 3M20 submarine-launched ballistic missile.
3R9.
Missile of Frog 5 tactical ballistic rocket.
3R9.
Russian tactical ballistic rocket.
44N6.
Alternate Designation of 218 surface-to-air missile.
46A.
Standard warhead of R-7A missile.
48N6.
48N6E.
Missile of S-300PMU-1 48N6E surface-to-air missile.
Russian surface-to-air missile. Improved version of the 48N6E for the S-400 system, capable of shooting down tactical ballistic missiles at incoming speeds of 4.8 km/s or hypersonic targets flying at 3.0 km/s at 150 km altitude.
48N6E2.
Missile of S-300PMU-2 surface-to-air missile.
49FUE.
Standard RV of Variant S submarine-launched ballistic missile.
4K10.
Article Number of R-27 submarine-launched ballistic missile.
4K18.
Article Number of R-27K submarine-launched ballistic missile.
4K22.
Article Number of RT-15M submarine-launched ballistic missile.
4K48.
Article Number of P-6 intermediate range cruise missile.
4K50.
Article Number of R-13 missile.
4K55.
Article Number of R-21 submarine-launched ballistic missile.
4K75.
Article Number of R-29 submarine-launched ballistic missile.
4K75D.
Article Number of R-29D submarine-launched ballistic missile.
4K75DU.
Article Number of R-29R submarine-launched ballistic missile.
4K75K.
Article Number of R-29K submarine-launched ballistic missile.
4K75R.
Article Number of R-29RL submarine-launched ballistic missile.
4K75RM.
Article Number of R-29RM submarine-launched ballistic missile.
Canadian gun-launched sounding rocket. When most people think of the HARP Program they usually think of the big 16 inch guns roaring skywards as they launch test probes into the upper atmosphere. What most people do not realise was that even before HARP small portable gun launchers were used for the same purpose and even during HARP hundreds of high altitude flights were conducted using small guns. The 5 inch gun-launch system was initially designed to satisfy the requirements of the Meteorological Rocket Network This required that an 0.9 kg (2 lb) payload be carried to an altitude of 65 km (40 miles). Typical payloads were radar reflective chaff ejected at apogee, which was tracked by radar to yield wind data, and small Metsondes which drifted to earth under large parachutes and returned radio telemetry of temperature, humidity and the like.
51T6.
Russian anti-ballistic missile. Exo-atmospheric interceptor component of A-135 ABM system.
51T6, 53T6.
Missile article number for A-135 missile.
53T6.
Russian anti-ballistic missile. Endo-atmospheric interceptor component of A-135 ABM system.
5V11.
Manufacturer's designation for Dal surface-to-air missile.
5V21.
5V28.
5V28E.
Manufacturer's designation for V-880E surface-to-air missile.
5V28M.
Manufacturer's designation for V-880M surface-to-air missile.
5V55R.
Missile article number for S-300 missile.
5V55RM.
Missile of S-300F surface-to-air missile.
5V55U.
Missile of S-300PMU-1 5V55U surface-to-air missile.
5Ya24.
Manufacturer's designation for 218 surface-to-air missile.
5Ya25.
Manufacturer's designation for 217 surface-to-air missile.
5Ya25M.
Manufacturer's designation for 217M surface-to-air missile.
5Ya26, 5Ya27.
Manufacturer's designation for S-225 anti-ballistic missile.
63S1.
Manufacturer's designation for Kosmos 63S1 orbital launch vehicle.
63S1M.
Manufacturer's designation for Kosmos 63S1M orbital launch vehicle.
63SM.
Manufacturer's designation for Kosmos 11K63 orbital launch vehicle.
64S5.
Ukrainian intercontinental ballistic missile. Space launch version, never went beyond design stage.
65MP.
Manufacturer's designation for Kosmos 65MP orbital launch vehicle.
65S3.
Manufacturer's designation for Kosmos 65S3 orbital launch vehicle.
Canadian gun-launched sounding rocket. The highly successful 5 inch HARP gun had demonstrated the immense versatility of small portable gun systems for atmospheric exploration. The 7 inch HARP gun system represented the 5 inch system scaled up to the largest barrel size practical, while still remaining portable.
761.
Chinese sounding rocket. Lightweight two-stage solid propellant sounding rocket. Designation indicates development was authorised in January 1976. Evidently replaced both the HP2 and HP6 from about 1980 on. Used for routine measurement of the upper atmosphere.
8A11.
Article number for R-1 missile.
8A61.
Article Number of R-11 submarine-launched ballistic missile.
8A62M.
Missile of R-5M intermediate range ballistic missile.
8A63.
Article Number of R-3A intermediate range ballistic missile.
8A67.
Article Number of R-3 intermediate range ballistic missile.
8A91.
Article Number of Sputnik 8A91 intercontinental ballistic orbital launch vehicle.
8A92.
Article Number of Vostok 8A92 orbital launch vehicle.
8A92M.
Article Number of Vostok 8A92M orbital launch vehicle.
8F17.
Standard RV of R-16 intercontinental ballistic missile.
8K11.
Article Number of R-1 missile.
8K14.
Article Number of R-11A suborbital launch vehicle and R-11 and R-11M submarine-launched ballistic missiles.
8K51.
Article Number of R-5M intermediate range ballistic missile.
Russian anti-satellite missile. ASAT version. Little has emerged about Korolev's ASAT project, designed in competition with Chelomei's in 1961-1964.
8K61.
Article Number of R-11FM submarine-launched ballistic missile.
8K62.
Article Number of R-5 intermediate range ballistic missile.
8K63.
Article Number of R-12 missile.
8K63U.
Article Number of R-12U intermediate range ballistic missile.
8K64.
Article Number of R-16 intercontinental ballistic missile.
8K64U.
Article Number of R-16U intercontinental ballistic missile.
8K65.
Article Number of R-14 missile.
8K65U.
Article Number of R-14U intermediate range ballistic missile.
8K66.
Article Number of R-26 intercontinental ballistic missile.
8K67.
Article Number of Tsiklon missile.
8K67P.
Article Number of R-56 Polyblock, R-56 Polyblock ICBM, R-56, and R-36 8K67P intercontinental ballistic missiles and space launch vehicles.
8K69.
Article Number of R-36-O orbital missile.
8K71.
Article Number of R-7 missile.
Russian ballistic missile. Korolev project. No other information available.
8K713.
Article Number of GR-1 intercontinental ballistic missile.
Russian intercontinental ballistic missile. ICBM version. Article number sometimes erroneously given as 8K73.
8K71PS.
Article Number of Sputnik 8K71PS intercontinental ballistic orbital launch vehicle.
8K72.
Article Number of Luna 8K72, Vostok 8K72, and Vostok 8K72K orbital launch vehicles.
8K73.
Alternate designation of GR-1 intercontinental ballistic missile.
8K73.
Russian ballistic missile. Korolev project. Possibly designation for variant of GR-1.
8K74.
Article Number of R-7A missile.
8K75.
8K75M.
Complex of R-9M intercontinental ballistic missile.
8K76.
Article Number of R-9M intercontinental ballistic missile.
8K76.
Russian intercontinental ballistic missile. Version using storable propellants and Isayev engines. Studied but rejected prior to start of development.
8K77.
Russian intercontinental ballistic missile. Version with vacuum-isolated liquid oxygen tanks to provide capability to hold ready for instant launch. Studied but never developed.
8K78.
Article Number of Molniya 8K78 orbital launch vehicle.
8K78L.
Article Number of Molniya 8K78L orbital launch vehicle.
8K78M.
Article Number of Molniya 8K78M orbital launch vehicle.
8K79.
Russian intermediate range ballistic missile. Korolev 1961 design for a single stage military rocket. A competing missile was selected for the requirement.
8K81.
Article Number of UR-200 intercontinental ballistic missile.
8K82.
Article Number of UR-500 missile.
8K82K.
Article Number of Proton-K orbital launch vehicle.
8K82K / 11S824.
Article Number of Proton-K-D orbital launch vehicle.
8K82K / 11S824F.
Article Number of Proton-K-D-2 orbital launch vehicle.
8K82K / 11S824M.
Article Number of Proton-K-D-1 orbital launch vehicle.
8K82K / 11S86.
Article Number of Proton-K-DM orbital launch vehicle.
8K82K / 11S861.
Article Number of Proton-K-DM-2 orbital launch vehicle.
8K82K / 11S861-01.
Article Number of Proton-K-DM-2M orbital launch vehicle.
8K82K / 17S40.
Article Number of Proton-K-17S40 orbital launch vehicle.
8K82KM.
Article Number of Proton-K-Briz-M orbital launch vehicle.
8K82M.
Article Number of Proton-M-Briz-M orbital launch vehicle.
8K82M / 11S861.
Article Number of Proton-M-DM-2 orbital launch vehicle.
8K83.
Article Number of UR-200B orbital missile.
8K84.
8K84K.
Alternate Designation of UR-100K intercontinental ballistic missile.
8K84M.
Article Number of UR-100M missile.
8K84UTTKh.
Complex of UR-100M missile.
8K94.
Ukrainian intermediate range ballistic missile. Unusual designation for the upper stages of another Yangel project - possibly reflecting design originally was stand-alone IRBM?
8K95.
Article Number of RT-1 intermediate range ballistic missile.
8K96.
Article Number of RT-15 intermediate range ballistic missile.
8K97.
Article Number of RT-25 intermediate range ballistic missile.
8K98.
Article Number of RT-2 intercontinental ballistic missile.
8K98M.
Article Number of RT-2M intercontinental ballistic missile.
8K98P.
Article Number of RT-2P intercontinental ballistic missile.
8K99.
8Zh38.
Article Number of R-2 intermediate range ballistic missile.
9K21.
Article Number of R-65 tactical ballistic rocket.
9K52.
Russian intermediate range ballistic missile. First flight 1974. SS-21 is Tochka SRBM mounted on a ZIL-375 transporter, while SS-23 is the same missile on an 8-wheeled TEL.
9K72.
Article Number of R-17 short-range ballistic missile.
9K76.
Russian intermediate range ballistic missile.
Russian intermediate range ballistic missile. Initially designated SS-22 by DoD; redesignated SS-12M Scaleboard B
9K79.
Russian intermediate range ballistic missile. Tactical ballistic missile. SS-21 is Tochka SRBM mounted on a ZIL-375 transporter, while SS-23 is the same missile on an 8-wheeled TEL.
Russian intermediate range ballistic missile. Improved version.
Russian short range ballistic missile. Two-stage deployed short range missile. Four solid motors strapped together, operating in staged pairs.
9M76.
9M79.
9M79M1.
Missile of 9K79-1 intermediate range ballistic missile.
9M8.
Missile of Krug surface-to-air missile.
9M82.
Russian surface-to-air missile. Anti-tactical ballistic missile; outer-layer defense.
Russian surface-to-air missile. Anti-tactical ballistic missile; outer-layer defense.
9M82M, 9M83M.
Missile of Antey-2500 surface-to-air missile.
9M83.
Russian surface-to-air missile. Anti-tactical ballistic missile; inner-layer defense.
Russian surface-to-air missile. Anti-tactical ballistic missile; inner-layer defense.
9M96.
Article number of missile of S-400 missile system.
9M96.
Russian surface-to-air missile. Improved, longer range version of 9M96 for the S-400. Four 9M96's can be housed in a single 48N6E launch container position.
9M96E.
Missile of S-300PMU-1 9M96E surface-to-air missile.
9M96E2.
Missile of S-300PMU-1 9M96E2 surface-to-air missile.
A.
Library of Congress Designation for Soviet rockets derived from R-7 ICBM with no upper stages: of R-7A missile, and Sputnik 8K71PS, Sputnik 11A59, Sputnik 8A91, and Vostok 11A510 orbital launch vehicle.
A.
Complex of V-1000 anti-ballistic missile.
A1.
German test vehicle. First in series of rockets leading to V-2. Exploded at Kummersdorf during a test run. Considered aerodynamically unstable (a stabilising flywheel was mounted forward) and no launch attempts were made.
A-1.
Library of Congress Designation for Soviet rockets derived from R-7 ICBM with a smaller single-engine upper stage: Luna 8K72, Vostok 8K72, Vostok 8K72, Vostok 8A92, and Vostok 8A92M orbital launch vehicles.
Single stage vehicle.
A12.
Alternate designation for Von Braun 1948, Von Braun 1952, and Von Braun 1956 winged orbital launch vehicles.
A-135.
Two-tier Russian anti-ballistic missile system for the defence of Moscow, with both endoatmospheric and exoatmospheric interceptor missiles. After protracted development, the system was said to have gone into operation in 1995.
A2.
German test vehicle. First flight test rocket in the series that led to the V-2. Two were built, dubbed Max and Moritz. Both were successfully flown.
A-2.
Library of Congress Designation for Soviet rockets derived from R-7 ICBM with larger four-exhaust nozzle third stage, no fourth stage: Voskhod 11A57, Soyuz 11A511, Soyuz 11A511L, Soyuz 11A511U, Soyuz 11A514, Soyuz 11A511M orbital launch vehicle.
A-2e.
Library of Congress Designation of Molniya 8K78M orbital launch vehicle.
A-2-e.
Library of Congress Designation of Molniya 8K78 orbital launch vehicle.
A3.
German test vehicle. The A3 was the first large rocket attempted by Wernher von Braun's rocket team. It was equipped with an ambitious guidance package consisting of three gyroscopes and two integrating accelerometers. The rocket was intended as a subscale prototype for the propulsion and control system technology planned for the much larger A4. All of the launches were failures, and a total redesign, the A5, was developed.
A-35.
Complex of A-350Zh anti-ballistic missile.
A-35.
Russian anti-ballistic missile. First operational Soviet ABM system, going into limited operation around Moscow in 1972.
A-350.
Alternate designation for A-350R missile.
Russian anti-ballistic missile. Radiation-hardened version of the A-350.
Russian anti-ballistic missile. Initial version of the A-350 missile.
A-350Zh, A-350R.
Missile article number for A-35 missile.
A-35M.
Complex of A-350R anti-ballistic missile.
Russian anti-ballistic missile. Improved version of the A-35 with radiation-hardened missiles and command centres, improved radars, and capability against tactical missiles fired from Europe against Moscow. Went into operation in 1978.
A4.
Manufacturer's designation for V-2 short range ballistic missile.
A-4.
German production version.
A4b.
German intermediate range boost-glide missile. Winged boost-glide version of the V-2 missile. The A4b designation was used to disguise work on the prohibited A9 program.
A5.
German test vehicle. Subscale test model of A4 (V-2). Replaced the A3 in this role after its unsuccessful test series. The A5 used the same powerplant as the A3, but had the aerodynamic form of the A4 and a new control system. 25 all-up versions were flown, some several times.
A6.
German intermediate range cruise missile. The A6 designation was applied to a version of the A5 subscale V-2 using alternate propellants. It also seems to have been applied to a manned, ramjet-powered version of the A9 winged V-2.
A7.
German test vehicle. Subscale test model of the A9 rocket. Considered for use as a weapon as well.
A8.
German cruise missile. Planned stretched version of the V-2 with storable propellants. Never reached the hardware stage, but design continued after the war in France as the 'Super V-2'.
A9.
Alternate designation for A4b intermediate range boost-glide missile.
German intercontinental boost-glide missile. The A9/A10 was the world's first practical design for a transatlantic ballistic missile. Design of the two stage missile began in 1940 and first flight would have been in 1946. Work on the A9/A10 was prohibited after 1943 when all efforts were to be spent on perfection and production of the A4 as a weapon-in-being. Von Braun managed to continue some development and flight tests of the A9 under the cover name of A4b (i.e. a modification of the A4, and therefore a production-related project). In late 1944 work on the A9/A10 resumed under the code name Projekt Amerika, but no significant hardware development was possible after the last test of the A4b in January 1945.
German winged orbital launch vehicle. The A11 was planned at Peenemuende to use the A9/A10 transoceanic missile atop the tubby A11 stage to form the basis for launching the first earth satellite - or as an ICBM....
German orbital launch vehicle. The A12 has been named as the designation for a true orbital launch vehicle, as sketched out at Peenemuende. It would have been a four-stage vehicle consisting of the A9+A10+A11+A12 stages. Caluclation suggest it could have placed 10 tonnes into low earth orbit.
A-925.
Alternate designation for 51T6 anti-ballistic missile.
American winged orbital launch vehicle. In 1965-1966 NASA and the Department of Defense jointly studied two-stage-to-orbit reusable launch vehicles as a follow-on to existing expendable launchers. Following review of the three classes of alternative approaches, it was recommended that the immediate goal of the United States should be development of a partially reusable 'Class I' launch vehicle, which could be available by 1975 and would be competitive with existing expendable boosters. A fully reusable vehicle should only be pursued at a later date.
American winged orbital launch vehicle. The AACB Class II launch vehicle was a fully reusable, two-stage-to-orbit launch vehicle. Both stages would be lifting bodies and be powered by Lox/LH2 engines. The system would be operational by 1978 and place 9,100 kg of payload in orbit.
American winged orbital launch vehicle. The AACB Class III launch vehicle was an advanced concept use air-breathing stages, but still requiring two stages to achieve orbit. The joint NASA/USAF panel concluded that the technology did not yet exist to develop this concept, so it was only regarded as an option by 1982 at the earliest.
Pakistani single-stage solid propellant tactical ballistic missile. Indigenous Pakistani design, developed by the Space and Upper Atmosphere Research Commission (SUPARCO).
ABM-1.
ABM-1A.
Department of Defence Designation of A-350Zh anti-ballistic missile.
ABM-1B.
Department of Defence designation of A-350R missile.
ABM-2.
Department of Defence designation of A-35M missile.
ABM-3.
Department of Defence Designation of 53T6 anti-ballistic missile.
ABM-4.
Department of Defence Designation of 51T6 anti-ballistic missile.
ACES.
American anti-ballistic missile. SDIO/BMDO project, follow on to Arrow
French orbital launch vehicle. Ariane-5 derived semi-reusable proposal of 1993. Expendable fuel tanks but recoverable propulsion/avionics module.
Advanced Launch System.
Alternate designation for ALS heavy-lift orbital launch vehicle.
Advanced Satellite Launch Vehicle.
Full name of ASLV all-solid orbital launch vehicle.
American all-solid orbital launch vehicle. Proposed upgrade of Scout proposed by the University of Rome with two strap-ons from the Ariane 4. Launch would have been from Italy's San Marco platform off Kenya. Further work cancelled in 1993.
Advanced Solid Rocket Motors.
Alternate designation for Shuttle ASRM winged orbital launch vehicle.
Australian test vehicle. Two stage vehicle consisting of 1 x Aeolus Booster + 1 x Mayfly
Australian sounding rocket. Two stage vehicle consisting of 1 x Gosling IV + 1 x Vela
American sounding rocket. In late 1945 James Van Allen was assigned by John Hopkins University to survey sounding rocket requirements for upper atmosphere research. The V-2 was found to be too heavy and complex. In 1946 Van Allen decided that what was needed was a small rocket, derived from the Aerojet Wac Corporal and the Bumblebee missile developed under a US Navy program. This combination of an Aerojet booster and a Bumblebee second stage was dubbed the Aerobee. Aerobees were launched for 53 m tall launch towers to provide the necessary stability until enough speed had been gained for the fins to be effective in controlling the rocket. Launch towers were built at White Sands, Fort Churchill, Wallops Island, and aboard the research ship USN Norton Sound. The Aerobee could take 68 kg to 130 km altitude.
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee 100
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee 150.
American sounding rocket.
American sounding rocket.
American sounding rocket.
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee 150A
American sounding rocket.
American sounding rocket. Two stage sounding rocket consisting of a solid Nike booster paired with an Aerobee 150 liquid-propellant second stage.
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x Aerobee 150
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x Aerobee 150
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x AJ60-92
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x AJ60-92
American sounding rocket. The Aerobee 300, also called the Sparrowbee, consisted of an Aerobee 150 or Aerobee 180 lower stage with a 20 cm diameter Sparrow rocket as an upper stage. The Sparrow would ignite at 35 km altitude at 53 seconds into the flight, and boost the payload to 10,000 kph, allowing it to coast up to 420 km apogee. The rocket was designed for studies of the sun above the atmosphere and was only fired from Fort Churchill (the White Sands range was too small to cover the possible impact points of the high-altitude rocket).
American sounding rocket. Aerobee 300A used a four-fin Aerobee 150A second stage rather than the older three-fin 150.
American sounding rocket. In March 1957 an Aerojet engineer conceived of the 'ultimate Aerobee', with the body diameter increased to 46 cm diameter and powered by four engines. The design found no takers until it was pitched to NASA in 1961 and development was authorised. The final configuration selected used a Nike Ajax missile booster, 56 cm in diameter, followed by the Aerobee 350, equipped with 4 Aerobee 150A engines. The rocket could take 65 kg to 480 km altitude or 455 kg to 240 km altitude.
American sounding rocket. Single stage vehicle.
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee AJ10-25
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee AJ10-27
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee AJ10-34
American sounding rocket. Aerobee Hi was a development of the basic Aerobee with longer propellant tanks, improved materials, a better propellant fraction, and smaller fins. 9.3 m l x 0.39 m dia. The booster stage fired for 2.5 seconds and took the rocket to 270 m altitude and 820 kph. The upper stage then fired for 25 seconds, burning out at 40 km altitude travelling at 6400 kph. Thereafter the payload would coast up to 270 km altitude before falling back toward earth.
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee XASR-1
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee AJ10-25
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee XASR-1
American sounding rocket. Single stage vehicle.
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee XASR-1
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee AJ10-25
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee AJ10-24
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee AJ10-34
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee XASR-1
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee XASR-1
American sounding rocket. Two stage vehicle consisting of 1 x Aerobee Booster + 1 x Aerobee XASR-1
Aerobee-Hi.
Manufacturer's designation for Aerobee 150 sounding rocket.
Aerofan.
Popular Name of R-17 short-range ballistic missile.
Aerokosmos.
Popular Name of Shtil-3A intercontinental ballistic orbital launch vehicle.
American winged orbital launch vehicle. Development project from 1958-1963 for a horizontal takeoff / horizontal landing, single-stage-to-orbit vehicle that would carry three crew and additional paylaod from any airfield to orbit and back
French SSTO VTOVL orbital launch vehicle. Aerospatiale vertical takeoff, vertical landing single stage to orbit study.
The Agate was the first of the 'precious stone' series of French rockets leading to the Diamant satellite launcher. The single-stage vehicle used the NA801 Mammouth solid propellant rocket developed originally for the SSBT program. The purpose of the fin-stabilised unguided rocket was to test the recoverable instrument pod planned for later missile tests. The Agate R / VE110RR version was used to develop recovery procedures at sea.
AGM-131A.
Department of Defence Designation of SRAM-2 air-to-surface missile.
AGM-28.
Department of Defence designation of Hound Dog missile.
American intermediate range cruise missile.
American intermediate range cruise missile.
AGM-48A.
Department of Defence Designation of Skybolt air-to-surface missile.
AGM-69A.
Department of Defence Designation of SRAM air-to-surface missile.
AGM-86.
Department of Defence designation of ALCM missile.
American air-to-surface missile. Subsonic Cruise Armed Decoy, full scale development begun in 1968, project cancelled 1973. Nuclear warhead.
American air-to-surface missile. The SCAD project was revived and the redesigned missile was designated the 'Air-Launched Cruise Missile'. Nuclear warhead.
American air-to-surface missile. Conventional warhead version of ALCM.
Agni.
Indian intermediate range ballistic missile. Two stage ballistic missile consisting of 1 x Agni + 1 x Prithvi
Indian single-stage short range ballistic missile.
Indian intermediate range ballistic missile. Program revived in 1998, assumed to be nuclear warhead-capable.
Indian intermediate range ballistic missile.
Indian intermediate range ballistic missile.
Advanced Intercontinental Ballistic Missile, a planned 1966 successor to the Minuteman. Cancelled in 1967, with the Minuteman also outlasting such competitors as the Peacekeeper and SICBM, to remain in service to the mid-21st Century.
The Aigle's simple mission was to allow test of the telemetry equipment that would be used on later instrumented warheads. The first version of the Aigle was a simple fin-stabilised solid rocket propelled by a Stromboli SEPR 737 loaded with 984 kg of 'Plastolite' propellant.
The VE10A used an improved, lightened version of the Stromboli booster.
Air-Launched Cruise Missile.
Alternate designation for AGM-86B air-to-surface missile.
Air-Launched Miniature Vehicle.
Popular Name of ASAT anti-satellite missile.
ait.
American target missile. The ait vehicles were developed to support the USAF Airborne Intercept Technology program. They consisted of a Minuteman SR19AJ1 first stage (the basic ait version) or Thiokol Castor IVB first stage (designated ait-2), and a Minuteman II M57A1 second stage. A front-end module housed the payloads, the control system, GPS, and inertial guidance electronics.
American target missile. Version with a Thiokol Castor IVB first stage, and a Minuteman II M57A1 second stage.
Ajax.
Russian sled-launched winged orbital launch vehicle. Sled-launched, air-breathing, single stage to orbit, horizontal takeoff / horizontal landing launch vehicle proposed in Russia.
Akvamarin.
Popular Name of Rif-MA missile.
Iraqi intermediate range ballistic missile.
Iraqi modification of the R-17 with an 800-km range, achieved by reducing warhead weight to 125 kg, and increasing propellant load by 30 percent .
Al Fatah
Iraqi modification of the R-17 that doubled the missile's range at the expense of more than halving the payload and accuracy.
Egyptian intermediate range ballistic missile.
Egyptian intermediate range ballistic missile.
Egyptian short range ballistic missile.
Egyptian short range ballistic missile. United Arab Republic neither confirmed nor denied reports of November 8 that it had successfully launched its first rocket. Dr. Eugen Saenger of the Stuttgart Jet Propulsion Institute in Germany denied any connection with the United Arab Republic program as charged by Israel.
Argentinan short range ballistic missile.
American air-launched test vehicle. Two stage vehicle consisting of 1 x F4D Phantom + 1 x Genie-Alarr
Unique Russian space shuttle design of 1974. Hydrofoil-launched, winged recoverable first and second stages. Hydrofoil would have been propelled to launch speed by the launch vehicles rocket engines, using a 200 tonne fuel store in the hydrofoil. Advantages: launch from the Caspian Sea into a variety of orbital inclinations, variations in launch track possible to meet range safety requirements. Proposal of Alexeyev/Sukhoi OKBs.
Russian intercontinental ballistic missile. Albatros was an ICBM designed by NPO Mashinostroeniya under Chief Designer Gerbert Yefremov according to a decree of 9 February 1987. Like the Yuzhnoye Universal ICBM, it was to be built in enormous numbers in order to defeat any deployment by America of mass missile defences under their Strategic Defence Initiative. With the dissolution of the Soviet Union, and the abandonment of SDI by the United States, the missile was cancelled.
ALCM.
Popular Name of AGM-86B air-to-surface missile.
ALCM.
Air-Launched Cruise Missile, the major long-range standoff attack missile of the for USAF B-52 bombers. At the end of the Cold War the nuclear warheads were replaced with high explosives.
Aldan.
Launch System of A-35 missile.
American nuclear-powered orbital launch vehicle. Immense nuclear pulse launch vehicle proposed by Dandridge Cole.
Alfa.
Italy briefly flirted with the creation of an independent nuclear deterrent in the late 1960's. The Alfa project for an indigenous Italian submarine- and ship-launched ballistic missile was begun in 1971. Three Alfa test missiles with inert second stages were successfully launched in 1975-1976 from Salto di Quirra in Sardinia. The programme was abandoned at this stage, when Italy and its neighbours ratified the nuclear proliferation treaty.
ALS.
American heavy-lift orbital launch vehicle. The Advanced Launch System (ALS), was a US Air Force funded effort in 1987-1989 to develop a flexible, modular, heavy-lift, high rate space launch vehicle that could deliver payloads to earth orbit at a tenth the cost of existing boosters. Such a vehicle was seen as essential to supporting the launch of the huge numbers of satellites required for deployment of the ‘Star Wars' ballistic missile defense system. With the end of the Cold War, Star Wars was abandoned. The projected launch rate without the Star Wars requirement could never pay back the $15 billion non recurring cost, and the program was ended.
American test vehicle. Two stage vehicle consisting of 1 x F-104A Starfighter + 1 x Viper I
American air-launched target missile. Single-stage launch vehicle air dropped from a C-130 consisting of a surplus Minuteman SR19 stage and a payload section.
ALV.
American sounding rocket. Family of small low-cost all-solid-propellant launch vehicles, which use numerous off-the-shelf components and require minimal ground support
American low cost orbital launch vehicle. The AMROC corporation proposed to develop low-cost hybrid-propulsion orbital launch vehicles in the 1980's. Actual flight hardware did not go beyond a small test vehicle.
American low cost orbital launch vehicle. Single stage vehicle.
American tactical ballistic missile. Advanced Missile System - Heavy, US Army
American orbital launch vehicle. Proposed Earth-to-Orbit Segment booster for Andrews CEV architecture. Consisted of an Atlas V core, two Zenit-2 booster strap-ons, and a new-development Lox/LH2 upper stage.
Angara.
Launch System of S-200 missile.
Angara.
Launch System of V-860P surface-to-air missile.
The Angara was a new all-Russian heavy launch vehicle designed to replace the Zenit (which was built by a Ukrainian company) and Proton (which had launch pads only on Kazakh territory). The booster was sized for rail transport of modular manufactured components to cosmodromes at Plesetsk and Svobodniy. The design featured a single modular core that could be clustered for large payloads or used as a first stage with a variety of existing upper stages. All plans for the Angara were dependent on financing and subject to constant change.
Russian orbital launch vehicle. The initial flight version would be the Angara 1.1, featuring a single URM core module with the existing Briz upper stage. Payload would be 2.0 tonnes to a 200 km / 63 deg orbit). Other vehicle variants were numbered according to the number of URM's.
Russian orbital launch vehicle. First planned upgrade of Angara, the 1.2 version would use a new Block I lox/kerosene upper stage. Payload would be 3.7 tonnes to a 200 km / 63 deg orbit.
Russian orbital launch vehicle. The Angara 3A was a proposed variant of the modular launch vehicle that would use two universal rocket modules (URM's) as boosters flanking one URM in the core, with a Lox/Kerosene upper stage. It could put 14 tonnes into low earth orbit
Russian orbital launch vehicle. The Angara 4A had the same configuration as the Angara 1.2 but with a winged, recoverable URM. The booster would have 158 tonnes lift-off mass, and could place a 2.7 tonne payload into a 200 km / 63 deg orbit). The winged URM would have two jet engines and fly back to the Mirniy airfield at Plesetsk for recovery. One problem was that some abort profiles would require overflight of Norway. First flight of this version was predicted for 2003 in 1998.
Russian orbital launch vehicle. The Angara 5A was a proposed variant of the modular launch vehicle that would use four universal rocket modules (URM's) as boosters surrounding one URM in the core, with a Lox/LH2 upper stage. It could put 5.0 tonnes into geosynchronous orbit, or 8.0 tonnes into geosynchronous transfer orbit.
Russian orbital launch vehicle. The Orel, consisted of the Angara 3I plus an MKK spaceplane, similar to the MAKS. This would have a 431 tonne gross lift-off mass, with the spacecraft weighing 13.5 tonnes including a 4.2 tonne payload. This could be an eventual replacement of the Soyuz spacecraft for ferry of crews to space stations.
French test vehicle. Antares was a re-entry vehicle test booster. The first three stages lofted the fourth stage and RV model to 150 km altitude. The fourth stage then fired downward to ram the RV at Mach 7 into the atmosphere.
Russian surface-to-air missile. The Antey-2500 was a new generation of the S-300V, capable of shooting down re-entry vehicles of IRBMs of up to 2500 km range.
American sounding rocket. The Apache upper stage was an improved version of the Cajun. The Thiokol engine used aluminised polyurethane propellant with a higher specific impulse and phenolic lining in the steel nozzle. Cost to NASA was $ 6,000 per rocket. The Apache could be used in a single stage version, but was normally used with a booster stage, usually the Nike.
American intermediate range cruise missile. In July 1944, the USAAF implemented the idea to convert "war-weary" B-17 Flying Fortress bombers to radio-controlled assault drones. About 25 B-17s, mostly B-17F, were converted to BQ-7 configuration under program Aphrodite. The BQ-7 was to be flown from Great Britain against very hardened or heavily defended German targets - submarine pens or V-1 missile sites.
American test vehicle. Flight tests from a surface pad of the Apollo Launch Escape System using a boilerplate capsule.
American sea-launched orbital launch vehicle. Proposed expendable, water launch, single-stage-to-orbit, liquid oxygen/hydrogen, low-cost launch vehicle designed to carry small bulk payloads to low earth orbit. A unique attribute was that low reliability was accepted in order to achieve low cost.
Aquila.
Alternate designation for Industrial Launch Vehicle low cost orbital launch vehicle.
American sounding rocket. The Arcas (All-Purpose Rocket for Collecting Atmospheric Soundings) was developed by the Atlantic Research Corporation for the Office of Naval Research (ONR) with the support of the Navy Bureau of Aeronautics and the Air Force Cambridge Research Laboratories. Primarily a meteorological rocket, the Arcas was first fired in July 1959. The single-stage version was designed to lift 5.4 kg to 64 km. For more demanding missions, several versions of boosted Arcas were developed, as well as a stretched Super Arcas motor.
American sounding rocket.
American sounding rocket. Similar to the Deacon and Cajun. Developed by the Atlantic Research Corp. for NRL. First used in 1958. Designed to lift 18 kg to 113 km. The two-stage vehicle consisted of two Arcon motors in tandem.
Ares.
American heavy-lift orbital launch vehicle. The design selected to boost America's Orion manned spacecraft into space in the 21st Century was a family of launch vehicles dubbed Ares. Originally sold as being derivatives of space shuttle technology, tinkering by NASA engineers and necessary changes during development quickly resulted in the designs being essentially all-new. Following inevitable cost growth and schedule slippage, it was cancelled in 2010.
American winged orbital launch vehicle. The ARES ((Affordable REsponsive Spacelift) concept was of a reusable fly-back booster with expendable upper stages. The US Air Force began development of a demonstrator in May 2005, with a first flight date of 2010. It was felt that derivatives of the concept could support all space lift requirements of the USAF.
American heavy-lift orbital launch vehicle. Shuttle-derived launch vehicle design selected by NASA Administrator Mike Griffin to boost the manned CEV Crew Exploration Vehicle into low earth orbit. A single five-segment version of the shuttle solid rocket booster would be mated with a Lox/LH2 upper stage powered by a single J-2S engine.
American intercontinental ballistic missile. The Ares single-stage, liquid-propellant ICBM was the objective of propulsion studies at both Aerojet and Rocketdyne.
American orbital launch vehicle. The Ares launch vehicle was designed for support of Zubrin's Mars Direct expedition. It was a shuttle-derived design taking maximum advantage of existing hardware. It would use shuttle Advanced Solid Rocket Boosters, a modified shuttle external tank for handling vertically-mounted payloads, and a new Lox/LH2 third stage for trans-Mars or trans-lunar injection of the payload. Ares would put 121 tonnes into a 300 km circular orbit , boost 59 tonnes toward the moon or 47 tonnes toward Mars. Without the upper stage 75 tonnes could be placed in low earth orbit.
American heavy-lift orbital launch vehicle. NASA baseline heavy-lift vehicle to renew manned lunar exploration by 2020.
Argo.
Alternate Designation of Jason sounding rocket.
Argo.
American sounding rocket. Argo sounding rockets measured radiation caused by the Project Argus high altitude nuclear explosions. The missiles reached 800 km altitude, and were launched from Wallops Island, AMR, and Ramey AFB, Puerto Rico. The Argo A-1, also known as Percheron, consisted of a modified Sergeant plus 2 Recruits, and was later used on occasion by NASA's Langley Research Center. It could lift 180 kg to 177 km. The Argo D-4, D-8, and E-5 are listed under Javelin, Journeyman, and Jason.
Argo D-4.
Alternate Designation of Javelin sounding rocket.
Argo D-8.
Manufacturer's designation for Journeyman sounding rocket.
Argo E-5.
Manufacturer's designation for Jason sounding rocket.
American sounding rocket. NASA Bios (biological investigation of space).
French orbital launch vehicle. First successful European commercial launch vehicle, developed from L3S Europa launch vehicle replacement design. Development of the Ariane 1 was authorised in July 1973, took eight years, and cost 2 billion 1986 Euros.
French orbital launch vehicle. First version of the Ariane launch vehicle.
French orbital launch vehicle. Basic three stage vehicle without solid rocket motor strap-ons. Payload to geosynchronous transfer orbit was 2,175 kg.
French orbital launch vehicle. Improved version of the Ariane 1. It featured increased thrust first and second stage engines, a 25% stretched third stage, 4 seconds specific impulse improvement in the third stage, a larger internal payload fairing volume, and introduced the Sylda payload carrier for dual payloads. The Ariane 3 version added two solid rocket motor strap-ons. Development was authorised in July 1980 and had a total cost of 144 million 1986 Euros.
French orbital launch vehicle. Projected version of Ariane 5 with improvements in engine and materials.
French orbital launch vehicle. Four stage vehicle consisting of 2 x PAP solid rocket boosters + Ariane 2 core.
French orbital launch vehicle. The ultimate Ariane development. Compared with the Ariane 2/3, the Ariane 4 featured stretched first (61%) and third stages, a strengthened structure, new propulsion bay layouts, new avionics, and the Spelda dual-payload carrier. The basic 40 version used no strap-on motors, while the Ariane 42L, 44L, 42P, 44P, and 44LP versions used varous combinations of solid and liquid propellant strap-on motors). Development was authorised in January 1982, with the objective of increasing payload by 90%. Total development cost 476 million 1986 ECU's.
French orbital launch vehicle. 3 stage core vehicle with original Ariane H10 upper stage. A fully fueled Ariane core cannot lift off the ground without strap-on liquid or solid motors. When Ariane 4 is launched in this configuration, the propellant tanks of the first and second stages are not completely filled.
French orbital launch vehicle. 3 stage core vehicle with Ariane Ariane H10-3 upper stage.
3 stage core vehicle with Ariane H10+ upper stage.
French orbital launch vehicle. Ariane 4 with 2 liquid rocket strap-ons.
French orbital launch vehicle. As Ariane 42L but with Ariane H10-3 upper stage.
French orbital launch vehicle. Ariane 4 with 2 solid rocket strap-ons.
French orbital launch vehicle. As Ariane 42P but with Ariane H10-3 upper stage.
As Ariane 42P but with Ariane H10+ upper stage.
French orbital launch vehicle. Ariane 4 with 4 liquid rocket strap-ons.
French orbital launch vehicle. As Ariane 44L but with Ariane H10-3 upper stage.
French orbital launch vehicle. Ariane 4 with 2 liquid rocket + 2 solid rocket strap-ons.
French orbital launch vehicle. As Ariane 44LP but with Ariane H10-3 upper stage.
As Ariane 44L but with Ariane H10+ upper stage.
As Ariane 44LP but with Ariane H10+ upper stage.
French orbital launch vehicle. Ariane 4 with 4 solid rocket strap-ons.
French orbital launch vehicle. As Ariane 44P but with Ariane H10-3 upper stage.
French orbital launch vehicle. The Ariane 5 was a completely new design, unrelated to the earlier Ariane 1 to 4. It consisted of a single-engine Lox/LH2 core stage flanked by two solid rocket boosters. Preparatory work began in 1984. Full scale development began in 1988 and cost $ 8 billion. The design was sized for the Hermes manned spaceplane, later cancelled. This resulted in the booster being a bit too large for the main commercial payload, geosynchronous communications satellites. As a result, development of an uprated version capable of launching two such satellites at a time was funded in 2000.
French orbital launch vehicle. The ultimate evolved Ariane 5 funded as of the end of the millenium. A larger Lox/LH2 upper stage using the Vinci motor in place of the HM7B. The core remains the same. Result is an increase in GTO payload from 10.5 tonnes to 12.0 tonnes.
French orbital launch vehicle. Partially reusable concept of 1988 using Ariane 5 core with twin reusable flyback boosters.
French orbital launch vehicle. Partially reusable concept of 1993 using Ariane 5 core with flyback booster stages with Russian engines (RD-120 or RD-701).
French orbital launch vehicle. Version of the evolved Ariane 5 using a version of the EPS storable propellant stage instead of a new Lox/LH2 stage. Result is a payload to GTO of 8 tonnes. The use of the new Aestus restartable engine in the upper stage fitted the vehicle for space station logistics missions or launch of space probes requiring complex orbital maneouvres.
Ariane 5 Versatile.
Alternate designation for Ariane 5 V orbital launch vehicle.
French orbital launch vehicle. Partially reusable concept of 1995 using Ariane 5 core with vertical takeoff, vertical landing boosters.
French orbital launch vehicle, first version of the evolved Ariane 5. The solid booster motors propellant load was increased by 2.43 tonnes and the case was welded, for a weight saving in dry mass of 1.9 tonnes. The core was powered by an improved Vulcain 2 engine. The oxygen-rich cycle of the engine allowed the oxygen bulkhead to be moved within the stage, resulting in a 15.2 tonne increase in propellant in the core. A new Lox/LH2 upper stage, using the HM7B engine and oxygen tank from the Ariane 4 series, replaced the storable propellant EPS stage of earlier models. The result was an increase in payload to geoscynchronous transfer orbit from 6 tonnes to 10.5 tonnes.
Version of the Ariane 5 designed to orbit ESA's Automated Transfer Vehicle (ATV) resupply vehicle for the International Space Station.
French orbital launch vehicle. Initial version of the Ariane 5, a bit too large for the main commercial geosynchronous communications satellite payloads.
French orbital launch vehicle.
French orbital launch vehicle.
Ariane 6.
Manufacturer's designation for FLTP winged orbital launch vehicle.
American target missile. Space Vector Corporation developed and flew the Aries test vehicle (based on the Minuteman 1 second stage) for Strategic Defence Initiative payloads.
American all-solid orbital launch vehicle. Four stage version consisting of 1 x TU-904 + 1 x Orion 50 + 1 x Orion 50 + 1 x Orion 38
American sounding rocket.
Israeli anti-ballistic missile. The Arrow weapon system was a ground-based, ballistic missile defense system designed to protect Israel against ballistic missiles.
Prototype and initial model Israeli Anti Tactical Ballistic Missile, originally an SDIO/BMDO project.
Israeli theater missile defense weapon developed and manufactured using substantial American funding.
ARS.
The ARS-2 was an improvement by the American Interplanetary Socity of the German Mirak design. It used liquid oxygen and gasoline propellants, and was successfully launched on 14 May 1933. Successive rockets refined the design.
Article R.
Alternate Designation of D-6 submarine-launched ballistic missile.
ASA.
Russian sled-launched winged orbital launch vehicle. Sled-launched airbreathing single stage to orbit horizontal takeoff / horizontal landing launch vehicle proposed in Russia.
ASAT.
American anti-satellite missile. The ASAT air-launched anti-satellite missile was developed by Vought in response to a 1977 Air Force requirement for a missile that could be launched from an F-15A fighter yet was capable of intercepting and destroying enemy satellites in low earth orbit. Four of five tests were successful before the program was cancelled in 1988.
American sounding rocket. Two stage vehicle consisting of 1 x Asp + 1 x RTV Motor
British winged rocketplane. The Bristol Spaceplanes Ascender of the 1990`s was a sub-orbital manned spaceplane concept proposed by David Ashford. The Ascender spaceplane would use a small Viper tubojet engine as well as a main liquid fuel rocket engine. The Ascender would act as a technology demonstrator for the orbiter of the orbital Spacecab concept,.
Iranian two-stage solid-propellant missile, evidently using some Shahab systems and its re-entry vehicle.
ASLV.
Indian all-solid orbital launch vehicle.
ASM-135A.
Department of Defence Designation of ASAT anti-satellite missile.
ASMP.
French cruise missile. Tactical nuclear. ASMP-A is improved version expected to enter service in 2008.
Asp.
American sounding rocket. Sounding rocket (Atmospheric Sounding Projectile) originally designed against a US Navy Bureeau of Ships requirement to sample the mushroom clouds of nuclear explosions. Developed by Cooper Development Corporation for the Naval Radiological Defense Laboratory. Flight test in 1956. Designed to lift 13.6 kg to 40 km.
American sounding rocket. Two stage vehicle consisting of 1 x Asp + 1 x Apache
American sounding rocket.
American sounding rocket.
American sounding rocket.
American test vehicle. Single stage vehicle to demonstrate laser-pumped propulsion.
American winged orbital launch vehicle. Douglas design of the early 1960's for a two-stage-to-orbit, winged, recoverable vehicle. Two versions were envisioned - a preliminary one the size of a DC-8 and a monster vehicle capable of delivering one million pounds payload to orbit. It was assumed at this scale that Lox/LH2 vehicles could achieve stage propellant mass fractions of 88% to 86%.
American orbital launch vehicle. A two-stage all-Lox/LH2 vehicle proposed for the USAF SLV-4 requirement. Ruled out because it did not use the large segmented solids then favored by the USAF and its think tanks.
American sounding rocket. Aerojet-designed family of sounding rockets conceived as a lower-cost replacement of the liquid-propellant Aerobee.
American sounding rocket. Three stage vehicle consisting of 2 x Recruit + 1 x Aerojet Jr + 1 x Alcor
American sounding rocket. Two stage vehicle consisting of 1 x Genie + 1 x Alcor
American sounding rocket. Three stage vehicle consisting of 1 x Genie + 1 x Alcor + 1 x Asp
American sounding rocket. Single stage vehicle.
American sounding rocket. Single stage solid-fueled dual-thrust rocket replacement for the Aerobee 150.
American air-launched orbital launch vehicle. The Kelly Space & Technology Astroliner Space Launch System was a two-stage-to-orbit, towed space launch concept. Towing an aerodynamic vehicle to an altitude of 6,000 m yielded higher system performance due to vacuum engine performance, reduced drag and gravity losses, and aerodynamic lift during flight.
American winged orbital launch vehicle. Martin concept of 1961 for a horizontal takeoff / horizontal landing, single-stage-to-orbit vehicle that would be powered by nuclear magnetohydrodynamic engines.
German sled-launched winged orbital launch vehicle. Under the Future European Space Transportation Investigation Programme (FESTIP) of 1994-1999 French agencies and contractors designed a number of alternative reusable space launchers. This one was a Sled-launched horizontal takeoff / horizontal landing single stage to orbit. Essentially similar to FESTIP FSS-4
American short range ballistic missile. The ATACMS (Army Tactical Missile System) is the U.S. Army's current short/medium-range tactical ballistic missile system.
ATACMS (Block 1).
Popular Name of Block 1 short range ballistic missile.
ATACMS (Block 1A).
Popular Name of Block 1A short range ballistic missile.
ATACMS (Block 2).
Popular Name of Block 2 short range ballistic missile.
American short range ballistic missile. ATACMS Block II is a derivative of the MGM-140 ATACMS (Army Tactical Missile System). The Block II designation applies to ATACMS variants designed to deliver the BAT (Brilliant Anti-Tank) guided submunition.
ATBM.
Alternate designation for Arrow 1 anti-ballistic missile.
New Zealander sounding rocket. Single-stage New Zealand hybrid sounding rocket.
New Zealander sounding rocket. Two-stage increased-diameter New Zealand hybrid sounding rocket.Payload: 25 kg (55 lb) to a 250 km altitude.
American orbital launch vehicle. Privately funded family of solid propellant satellite launch vehicles. Originally known as LMLV (Lockheed-Martin Launch Vehicle); LLV (Lockheed Launch Vehicle). Sales did not develop as hoped by the company after the MEO-satellite bubble burst in the 1990's.
American test vehicle. Four stage vehicle consisting of 4 x Recruit + 1 x Castor 4 + 1 x Antares 2 + 1 x Alcor IA
Athena III.
Alternate designation for Satellite Launch Vehicle.
American test vehicle. The Athena was designed to simulate the re-entry environment of an intercontinental ballistic missile and was one of the few examples of sustained interstate missile tests within the United States.
American all-solid orbital launch vehicle. Basic version of the Athena with a Castor 120 first stage, Orbus second stage, and OAM Orbital Adjustment Module.
American all-solid orbital launch vehicle. The Athena-2 version featured a Castor 120 first stage, Castor 120 second stage, Orbus third stage, and OAM Orbital Adjustment Module.
American all-solid orbital launch vehicle. Planned but never flown heavier-lift version of Athena.
ATK Launch Vehicle.
American sounding rocket. Suborbital version.
Atlantis.
Alternate designation for UR-500 launch vehicle.
The Atlas rocket, originally developed as America's first ICBM, was the basis for most early American space exploration and was that country's most successful medium-lift commercial launch vehicle. It launched America's first astronaut into orbit; the first generations of spy satellites; the first lunar orbiters and landers; the first probes to Venus, Mars, Mercury, Jupiter, and Saturn; and was America's most successful commercial launcher of communications satellites. Its innovative stage-and-a-half and 'balloon tank' design provided the best dry-mass fraction of any launch vehicle ever built. It was retired in 2004 after 576 launches in a 47-year career.
Atlas 3A.
Alternate designation for Atlas IIIA orbital launch vehicle.
Atlas 3B.
Alternate designation for Atlas IIIB orbital launch vehicle.
American orbital launch vehicle.
American orbital launch vehicle.
American test vehicle. First test model of Atlas ICBM. Two booster engines, no sustainer, dummy warhead. 50% reliability in 8 flight tests.
American orbital launch vehicle. Atlas with upper stage based on Vanguard second stage.
American orbital launch vehicle. Atlas D + 1 x Agena A upper stage. Agena originally called 'Hustler', based on engine for cancelled rocket-propelled nuclear warhead pod for B-58 Hustler bomber.
American orbital launch vehicle. Atlas D with improved, enlarged Agena upper stage.
American orbital launch vehicle. Atlas D with further improved and lightened Agena upper stage.
Standardized Atlas booster with Agena D upper stage.
Uprated Atlas booster with Agena D upper stage.
American test vehicle. First all-up test version of the Atlas ICBM, with jettisonable booster engines and a single engine sustainer on core - a '1 1/2' stage launch vehicle.
American orbital launch vehicle. Atlas SLV-3 + 1 x Star 37B upper stage.
American orbital launch vehicle. Atlas F + 1 x Star 37B + 1 x Star 26B upper stages.
American test vehicle. Last development version of Atlas. Never deployed operationally or used for space launches.
American orbital launch vehicle. Version with Atlas C first stage, Able AJ10-101A second stage, Altair solid third stage.
American orbital launch vehicle. First test version of Atlas with Centaur upper stage.
American orbital launch vehicle. Version with Centaur D upper stage.
Atlas-Centaur launch vehicles using stretched, uprated Atlas core.
American orbital launch vehicle. Version with basic Centaur upper stage.
Standardised SLV-3C Atlas booster with Centaur D upper stage.
Fully developed version of Atlas with Centaur D-1A upper stage.
American intercontinental ballistic missile. Rocket used both as a space launcher and ICBM.
American orbital launch vehicle. Version with Atlas D first stage, Able AJ10-101A second stage, Altair solid third stage.
Atlas E.
Popular Name of CGM-16E intercontinental ballistic missile.
American intercontinental ballistic missile. Initial fully operational version of Atlas ICBM. Differed in guidance system from Atlas F. Deployed as missiles from 1960 to 1966. After retirement, the ICBM's were refurbished and used over twenty years as space launch vehicles.
American orbital launch vehicle. Atlas E + 1 x Star 20 upper stage.
American orbital launch vehicle. Atlas E + 1 x MSD upper stage.
American orbital launch vehicle. Atlas E + 1 x OIS upper stage.
American orbital launch vehicle. Atlas E + 1 x Star 48 + 1 x Star 48 upper stages.
American orbital launch vehicle. Atlas E + 1 x Star 37E + 1 x Star 37E upper stages.
Atlas F.
Popular Name of HGM-16F intercontinental ballistic missile.
American intercontinental ballistic missile. Final operational version of Atlas ICBM. Differed in guidance systems. Deployed as missiles from 1961 to 1966. After retirement, the ICBM's were refurbished and used for over thirty years as space launch vehicles.
American orbital launch vehicle. Atlas F + 1 x MSD upper stage.
American orbital launch vehicle. Atlas F + 1 x OIS upper stage.
American orbital launch vehicle. Atlas F + 1 x Star 37E upper stage.
American orbital launch vehicle. Atlas F + 1 x Star 37E + 1 x Star 37E upper stages.
American orbital launch vehicle. Atlas H used the Atlas first stage developed for the Atlas G vehicle. It was flown without the Centaur upper stage.
American orbital launch vehicle. The Atlas I launch vehicle was derived from the Atlas G, and included the same basic vehicle components (Atlas booster and Centaur upper stage). Significant improvements in the guidance and control system were made with an emphasis on replacing analog flight control components with digital units interconnected with a digital data bus.
American orbital launch vehicle. The Atlas II booster was 2.7-meters longer than an Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. The original Atlas II model was developed to support the United States Air Force Medium Launch Vehicle II program. Its Centaur used RL10A-3-3A engines operating at an increased mixture ratio. The first Atlas II flew on 7 December 1991, successfully delivering AC-102/Eutelsat II F3 to orbit.
American orbital launch vehicle. Atlas IIA was a commercial derivative of the Atlas II developed for the US Air Force. Higher performance RL10A-4 (or RL10A-4-1) engines replaced Atlas II's RL10A-3-3A engines.
American orbital launch vehicle. The Atlas II booster was 2.7-meters longer than the Atlas I and included uprated Rocketdyne MA-5A engines. The Atlas I vernier engines were replaced with a hydrazine roll control system. The Centaur stage was stretched 0.9-meters compared to the Centaur I stage. Fixed foam insulation replaced Atlas I's jettisonable insulation panels. Higher performance RL10A-4 or RL10A-4-1 engines replaced Atlas II's RL10A-3-3A. The Atlas IIAS model added four Thiokol Castor IVA solid rocket boosters (SRBs) to the core Atlas stage to augment thrust for the first two minutes of flight.
American orbital launch vehicle. The Atlas IIIA was a development of the Atlas using Russian engines in place of the Rocketdyne MA-5 booster/sustainer group used on all previous models. It was the centerpiece of Lockheed Martin's strategy to remain a leader in the commercial launch services industry. However customers never materialized, and it was used for only two launches in 2002-2004 before being replaced by the Atlas V.
American orbital launch vehicle. This was the first version of the Atlas to fly using Russian RD-180 engines; and the last version to fly using the original balloon-tank concept for the first stage. It differed from the Atlas IIIA in use of a stretched, two-engine upper stage, and had a brief three-year operational career in 2002-2005 before being superseded by the Atlas V.
Atlas IIR; Atlas IIAR.
Alternate Designation of Atlas IIIA orbital launch vehicle.
Atlas IIRC; Atlas IIARC.
Alternate Designation of Atlas IIIB orbital launch vehicle.
American orbital launch vehicle. Atlas D modified for use in Project Mercury.
American orbital launch vehicle. Standardized Atlas booster with no or small solid upper stage.
American orbital launch vehicle. The Atlas V launch vehicle system was a completely new design that succeeded the earlier Atlas series. Atlas V vehicles were based on the 3.8-m (12.5-ft) diameter Common Core Booster (CCB) powered by a single Russian RD-180 engine. These could be clustered together, and complemented by a Centaur upper stage, and up to five solid rocket boosters, to achieve a wide range of performance.
American orbital launch vehicle. Atlas V version with a 4-m diameter payload fairing, single engine Centaur upper stage, and no strap-on solid boosters. Payloads: 7,095 kg (15,642 lb) to sun synchronous orbit; 4,950 kg (10,910 lb) to geosynchronous transfer orbit.
American orbital launch vehicle. Atlas V with 4-m diameter payload fairing, single engine Centaur upper stage, and one strap-on solid booster. Payloads: 8,763 kg (19,320 lb) to sun synchronous orbit; 6,075 kg (13,393 lb) to geosynchronous transfer orbit.
American orbital launch vehicle. Atlas V with 4-m diameter payload fairing, single engine Centaur upper stage, and two strap-on solid boosters. Payloads: 10,168 kg (22,416 lb) to sun synchronous orbit; 7,000 kg (15,432 lb) to geosynchronous transfer orbit.
American orbital launch vehicle. Atlas V with 4-m diameter payload fairing, single engine Centaur upper stage, and three strap-on solid boosters. Payloads: 11,547 kg (25,458 lb) to sun synchronous orbit; 7,800 kg (17,196 lb) to geosynchronous transfer orbit.
Atlas V with 5-m diameter payload fairing, single engine Centaur upper stage, and no strap-on solid boosters. Payloads: 6,319 kg (13,931 lb) to sun synchronous orbit; 3,970 kg (8,752 lb) to geosynchronous transfer orbit.
American orbital launch vehicle. Atlas V with 5-m diameter payload fairing, single engine Centaur upper stage, and two strap-on solid boosters. Payloads: 10,161 kg (22,401 lb) to sun synchronous orbit; 6,485 kg (14,297 lb) to geosynchronous transfer orbit.
Atlas V 531
American orbital launch vehicle. Atlas V with 5-m diameter payload fairing, single engine Centaur upper stage, and five strap-on solid boosters. Payloads: 20,520 kg (45,238 lb) to sun synchronous orbit; 8,700 kg (19,180 lb) to geosynchronous transfer orbit.
American orbital launch vehicle. Proposed growth variant of the heavy-lift version of the Atlas V launch vehicle with three parallel 3.8-m-diameter Common Core Boosters (CCB), a 5-m-diameter wide body version of the Centaur upper stage with a single-engine, and a 5 m diameter payload fairing. Another variant would use a stretched wide body version of the Centaur upper stage with 2 or 4 motors, allowing payloads of up to 13,500 kg to be lofted to earth escape velocity.
American orbital launch vehicle. Proposed growth variant of the heavy-lift version of the Atlas V launch vehicle with three parallel 5-m-diameter wide-body Common Core Boosters (CCB), each with 1 or 2 RD-180 engines; a 5-m-diameter new Lox/LH2 stage with 2 or 4 engines with a total thrust of 180,000 kgf; and a 5 m diameter payload fairing.
American orbital launch vehicle. Proposed Saturn-V class variant of the heavy-lift version of the Atlas V launch vehicle with five parallel 5-m-diameter wide-body Common Core Boosters (CCB), each with 1 or 2 RD-180 engines; a 7-m-diameter new Lox/LH2 stage; and a 7 m diameter payload fairing.
American orbital launch vehicle. Heavy-lift version of the Atlas V launch vehicle system with three parallel 3.8-m-diameter Common Core Boosters (CCB), and a stretched version of the Centaur upper stage (CIII), which could be configured as a single-engine Centaur (SEC) or a dual engine Centaur (DEC), and a 5 m diameter payload fairing. As of 2004 no work had been authorised to build Atlas V Heavy facilities at either Cape Canaveral or Vandenberg AFB.
American orbital launch vehicle. Atlas-Vega consisted of an Atlas booster with a storable propellant upper stage. It was planned by NASA at its inception for deep space and planetary missions before the Atlas Centaur was available. Work had already begun when NASA discovered that the CIA and the US Air Force had an essentially identical launch vehicle (Atlas-Hustler, later called Atlas-Agena) in development for the highly classified Corona reconnaisance satellite program. Atlas-Vega was accordingly cancelled.
Atlas F + 1 x Agena D upper stage.
Atlas E + 1 x Trident upper stage.
Atlas F + 1 x Trident upper stage.
Atlas-Hustler.
Alternate designation for Atlas Agena A orbital launch vehicle.
Atmospheric Sounding Projectile.
Alternate designation for Asp sounding rocket.
ATV.
American SSTO VTOVL orbital launch vehicle. George Detko of NASA's Marshall Space Flight Center produced designs for SSTO vehicles as early as 1960. The expendable vehicle had a gross listoff mass of only 22 tonnes, and could deliver a two-person crew to orbit.
French sounding rocket. Single stage vehicle.
Australian low cost orbital launch vehicle. Proposed southern hemisphere launcher.
B-1.
Library of Congress Designation of Kosmos 63S1, Kosmos 63S1M, and Kosmos 11K63 orbital launch vehicles.
B-29.
Alternate Designation of Banshee intercontinental cruise missile.
B-61A.
Alternate designation for Matador intermediate range cruise missile.
B-65.
Alternate designation for Atlas A test vehicle.
B-75.
Alternate designation for Thor intermediate range ballistic missile.
B-76.
Alternate designation for CGM-13B intermediate range cruise missile.
B-78.
Alternate designation for Jupiter intermediate range ballistic missile.
B-87.
Alternate designation for Skybolt air-to-surface missile.
Baby Babylon.
Alternate designation for Babylon Gun gun-launched orbital launch vehicle.
From March of 1988 until the invasion of Kuwait in 1990, Iraq contracted with Gerard Bull to build three superguns: two full sized 'Project Babylon' 1000 mm guns and one 'Baby Babylon' 350 mm prototype. Nine tonnes of special supergun propellant could fire a 600 kg projectile over a range of 1,000 kilometres, or a 2,000 kg rocket-assisted projectile. The 2,000 kg projectile would place a net payload of about 200 kg into orbit at a cost of $ 600 per kg. The 1000 mm guns were never completed. After the war UN teams destroyed the guns and gun components in Iraqi possession.
Egyptian intermediate range ballistic missile.
Ballistisches Enistufiges Traeger-Aggregat I.
Alternate designation for Beta ssto vtovl orbital launch vehicle.
Ballistisches Enistufiges Traeger-Aggregat II.
Alternate designation for Beta II ssto vtovl orbital launch vehicle.
Ballistisches Enistufiges Traeger-Aggregat III.
Alternate designation for Beta III ssto vtovl orbital launch vehicle.
Ballistisches Enistufiges Traeger-Aggregat IV.
Alternate designation for Beta IV ssto vtovl orbital launch vehicle.
American intercontinental cruise missile. Cruise missile version of B-29 bomber
Russian surface-to-air missile. First Soviet anti-aircraft barrage rocket, fired in limited numbers during siege of Leningrad, and downing two German aircraft.
American heavy-lift orbital launch vehicle. Proposed launch vehicle for large SDI 'Star Wars' payloads. Expected to cost $ 400-500 million, the Barbarian could place the Zenith-Star chemical laser into low earth orbit. It would consist of 3 Shuttle SRM's, attached around a ring of six Delta RS-27 first stage boosters, which in turn clustered around a single Delta first stage booster that was the last stage of the launch vehicle.
American heavy-lift orbital launch vehicle. The Zenith Star space-based chemical laser missile defence weapon required a launch vehicle capable of placing a 45,000 kg payload into low earth orbit. Martin and Aerojet turned to their work 20 years earlier on advanced Titans for the MOL program. These earlier studies were combined with new concepts for tank construction and materials. The Martin Barbarian was a 4.57 m diameter Titan vehicle (instead of the customary 3.05 m) with four LR-87 engines on the first stage, and a single LR-87 engine on the second stage.
American low cost orbital launch vehicle. The Beal Aerospace BA-2 was a privately-financed heavy-lift commercial launch vehicle that used innovative technical solutions to achieve low cost to orbit. It harkened back to the low-cost Truax Sea Dragon or TRW 'Big Dumb Booster' concepts of the 1960's but added several new twists. Beal abandoned the project at the end of 2000 after the collapse of the MEO satellite market and active measures by NASA to support other, competing, more high-tech projects by the major aerospace contractors.
French sounding rocket. Two stage vehicle consisting of 1 x Elan + 1 x Aurore
French sounding rocket. Two stage vehicle consisting of 1 x Elan + 1 x Belisama
Family of sounding rockets, developed by Sud Aviation, with the only or upper stage being variants of the Belier stage powered by a Jericho rocket motor. These were the most significant series of French civilian suborbital rockets. Manufacturing licenses were sold to India and Pakistan, becoming the basis of their rocket industries.
French sounding rocket. Basic Belier single stage vehicle, powered with a Jericho rocket motor loaded with 208 kg of 'Epictete' solid propellant with a specific impulse of 190 seconds.
French sounding rocket. Improved Belier single stage vehicle, loaded with 'Plastolite' propellant with a 205 second specific impulse.
French sounding rocket. Improved Belier single stage vehicle, using a Vega motor loaded with 230.5 kg of 'Isolane' propellant with a specific impulse of 240 seconds.
French sounding rocket.
Belka.
Launch System of RM-205 surface-to-air missile.
French sounding rocket. Berenice was Onera's successor to the Antares re-entry vehicle test booster. It was nearly double the mass of Antares.
French orbital launch vehicle. In April 1963, ONERA proposed using a modified Berenice suborbtial test vehicle to place a small 3.5 kg satellite ('Satmos') into a 250 x 1800 km orbit. They claimed this booster could be ready in 1964, one year before Diamant. However the given the marginal growth potential of such a design, the government decided to stick with Diamant.
Berkut.
Beta.
German SSTO VTOVL orbital launch vehicle. In 1969 rocket pioneer Dietrich Koelle was working at MBB (Messerschmitt-Bolkow-Blohm). There he sketched out a reusable VTOVL design called BETA using Bono's SASSTO as a starting point. The vehicle, taking European technology into account, was a bit heavier than Bono's design. But the thorough analysis showed even this design would be capable of delivering 2 tonnes of payload to orbit.
German SSTO VTOVL orbital launch vehicle. Beta II was Dietrich Koelle's nominal 350 tonne lift-off mass SSTO design for launch of a 10 tonne European spaceplane.
German SSTO VTOVL orbital launch vehicle. In 1969 Dietrich Koelle proposed his BETA III design. This was to deliver 20 tonnes to orbit with a launch mass of 600 tonnes. In 1996 and 1998 he updated the design for use as an ISS resupply vehicle in place of the shuttle, and as a space tourism vehicle for 100 passengers.
German SSTO VTOVL orbital launch vehicle. Beta II was Dietrich Koelle's largest SSTO concept, with a nominal 2000 tonne lift-off mass SSTO design and 100 tonne payload.
American intermediate range cruise missile. Losing design in Sea-Launched Cruise Missile competition. Nuclear warhead version with warhead mass of 120 kg.
BGM-75.
Department of Defence Designation of AICBM intercontinental ballistic missile.
Big Dumb Booster.
Manufacturer's designation for LCLV low cost orbital launch vehicle.
Big Stick.
Alternate designation for SLAM intercontinental cruise missile.
The British Interplanetary Society (BIS) reusable booster concept of 1950 was a 3 stage, rocket, similar to Von Braun concepts of the time. The third stage was a winged vehicle which would use the skip-glide re-entry technique conceived by Saenger.
Russian air-launched orbital launch vehicle. Bizan was the 1982 Soviet air-launched spaceplane design iteration between the '49' and 'MAKS' concepts. Like the '49', it was air-launched from atop an An-124 transport. Unlike the '49', it was a single-stage-to-orbit tripropellant concept.
Russian air-launched orbital launch vehicle. Air launched from catamaran heavy-life aircraft, predecessor of later Gerakl / Molniya-1000 design. 900 tonnes takeoff mass. Release conditions: Suspended load, Mach 0.7 at 8 to 9 km altitude. Effective velocity gain compared to vertical launch 270 m/s.
British orbital launch vehicle. Britain's only indigenous launch vehicle. Following cancellation of the project in July 1971, one final launch was permitted, which successfully placed the Prospero satellite in orbit.
The Black Brant originated in a 1957 Canadian government requirement for a sounding rocket to characterize the ionosphere in order to improve military communications. Bristol Aerospace of Winnipeg, Manitoba was selected to design the rocket, while the Canadian Armament Research and Development Establishment (CARDE) was responsible for the propellant and filling. The prototype was called the Propulsion Test Vehicle. It was a relatively heavy rocket, since it was designed to stand up to the use of a wide range of engine burning time, propellant loadings and launch angles associated with fuel development. The lighter production version of the vehicle was renamed Black Brant. Later versions of Black Brant used a variety of booster and upper stages to supplement the original single-stage vehicle.
Canadian sounding rocket. Single stage vehicle using the Black Brant VA.
Canadian sounding rocket. Three stage vehicle consisting of 1 x Terrier + 1 x Black Brant VB or VC + 1 x Nihka. Payload 90 kg to 1,200 km or 317 kg to 550 km.
Canadian sounding rocket.
Canadian sounding rocket.
Canadian sounding rocket. Three stage vehicle. Payload weights of 320 kg to 500 km or 550 kg to 350 km altitude.
Canadian sounding rocket. The Black Brant XII rocket system was a four stage system used primarily to carry a variety of payloads to high altitudes. Its development is a spin-off of the Black Brant X development. Four stage vehicle consisting of 1 x Talos + 1 x Taurus + 1 x Black Brant VB + 1 x Nihka. Payload 136 kg to 1,500 km or 522 kg to 500 km.
Canadian sounding rocket. Single stage vehicle.
Canadian sounding rocket.
Canadian sounding rocket. Single stage vehicle consisting of 1 x Black Brant IIIA or IIIB.
Canadian sounding rocket.
Canadian sounding rocket. Two stage vehicle consisting of 1 x Black Brant VA + 1 x Black Brant IIIA or IIIB.
Canadian sounding rocket.
Canadian sounding rocket.
Canadian sounding rocket. Single stage vehicle consisting of 1 x Black Brant VA, VB, or VC.
Canadian sounding rocket.
Canadian sounding rocket. Three-fin version. The Black Brant VB provided slightly improved performance over the VC. The burnout roll rate for the Black Brant V was 4 cycles per second. Maximum longitudinal acceleration varied with payload weight; for a typical payload weight of 270 kg, maximum thrust axis acceleration is approximately 12g's.
Canadian sounding rocket. Four-fin version.
Canadian sounding rocket. Single stage vehicle.
Canadian sounding rocket. Single stage vehicle.
Canadian sounding rocket. Two stage vehicle consisting of 1 x Nike booster + Black Brant VB or VC upper stage. Payload 136 kg to 430 km or 408 kg to 230 km.
Canadian sounding rocket.
Canadian sounding rocket.
Canadian sounding rocket. Two stage vehicle consisting of 1 x Terrier Mk 70 + 1 x Black Brant VB.
Canadian sounding rocket.
Canadian sounding rocket.
Canadian sounding rocket.
Black Brant I.
Alternate designation for Black Brant 1 sounding rocket.
Black Brant II.
Alternate designation for Black Brant 2 sounding rocket.
Black Brant IIB.
Alternate designation for Black Brant 2B sounding rocket.
Black Brant III.
Alternate designation for Black Brant 3 sounding rocket.
Black Brant IIIB.
Alternate designation for Black Brant 3B sounding rocket.
Black Brant IVA.
Alternate designation for Black Brant 4A sounding rocket.
Black Brant IVB.
Alternate designation for Black Brant 4B sounding rocket.
Black Brant IX.
Alternate designation for Black Brant 9 sounding rocket.
Black Brant IXB.
Alternate designation for Black Brant 9B sounding rocket.
Black Brant VA.
Alternate designation for Black Brant 5A sounding rocket.
Black Brant VB.
Alternate designation for Black Brant 5B sounding rocket.
Black Brant VC.
Alternate designation for Black Brant 5C sounding rocket.
Black Brant VI.
Alternate designation for Black Brant 6 sounding rocket.
Black Brant VII.
Alternate designation for Black Brant 7 sounding rocket.
Black Brant X.
Alternate designation for Black Brant 10 sounding rocket.
Black Brant XB.
Alternate designation for Black Brant 10B sounding rocket.
Black Brant XI.
Alternate designation for Black Brant 11 sounding rocket.
Black Brant XII.
Alternate designation for Black Brant 12 sounding rocket.
American air-launched orbital launch vehicle. Winged, first stage of a launch vehicle using aerial refueling and existing engines. Takes off from runway; rendezvous with tanker to load oxidizer; then flies to Mach 12/150 nm to release Star 48V second stage and 450 kg payload. In comparison to Black Horse, uses existing engines and a much more achievable mass fraction by only flying to half orbital speed.
American air-launched winged orbital launch vehicle. Winged, single stage to orbit launch vehicle using aerial refueling and lower performance, non-cryogenic propellants. Takes off from runway at 22,000 kg gross weight; rendezvous with tanker to load 66,760 kg oxidizer; then flies to orbit.
The Black Knight was a British test vehicle designed to test re-entry vehicles for the Blue Streak MRBM. It was subsequently used for a series of US-sponsored test of RV radar signatures.
British test vehicle. Single stage vehicle.
British test vehicle. Two stage vehicle consisting of 1 x Black Knight 201 + 1 x Cuckoo IB
British test vehicle. Two stage vehicle consisting of 1 x Black Knight 201 + 1 x Cuckoo II
British test vehicle. Two stage vehicle consisting of 1 x Black Knight 301 + 1 x Cuckoo IB
British test vehicle. Two stage vehicle consisting of 1 x Black Knight 301 + 1 x Cuckoo II
Black Sparrow
American short range ballistic missile. In production. Advanced TACtical Missile System, Fire Support , Deep Attack Field Artillery, 1000 bomblets
American short range ballistic missile. In production.
American short range ballistic missile. In development.
British surface-to-air missile.
British surface-to-air missile.
British surface-to-air missile. 4 wrap-around spr, ramjet sustainer. Program ended.
Bloodhound Mk.1.
Manufacturer's designation for Bloodhound Mk. 1 surface-to-air missile.
American suborbital launch vehicle. Air Force version of Scout used for suborbital tests.
American all-solid orbital launch vehicle. Air Force version of Scout used for suborbital and orbital military tests.
American strategic communications missile. USAF initial Emergency Rocket Communications System booster.
Blue Scout I.
Alternate designation for Blue Scout 1 suborbital launch vehicle.
Blue Scout II.
Alternate designation for Blue Scout 2 all-solid orbital launch vehicle.
American suborbital launch vehicle. Four stage vehicle consisting of 1 x Castor + 1 x Antares + 1 x Alcor + 1 x Cetus
American suborbital launch vehicle. Three stage version consisting of 1 x Castor + 1 x Antares + 1 x Alcor
American suborbital launch vehicle.
American suborbital launch vehicle.
American suborbital launch vehicle. Smaller Air Force version of Scout used for suborbital military tests.
British air-to-surface missile.
British intermediate range ballistic missile. Cancelled 1960
British tactical ballistic missile. Cancelled 1962
American orbital launch vehicle. Boeing EELV as proposed in 1992.
American orbital launch vehicle. The Boeing SDV Class I vehicle would lead to the Shuttle-C, using the shuttle aft fuselage with SSME engines to power a cargo canister into orbit.
American SSTO VTOVL orbital launch vehicle. In 1977 Boeing produced a vehicle design for a 227 tonne payload vertical takeoff launch vehicle to be used to launch components for the huge Satellite Solar Power platforms that NASA was promoting at the time. The booster would launch from the edge of a water-filled man-made lagoon and recover in the lagoon and used a water-cooled heat shield for reentry.
American air-launched anti-ballistic missile. Dropped from B-47 medium bombers, the missile consisted of a Sergeant booster and Altair upper stage.
American anti-ballistic missile. Two stage vehicle consisting of 1 x B-47 Stratojet + 1 x Sergeant
American anti-ballistic missile. Three stage vehicle consisting of 1 x B-47 Stratojet + 1 x Sergeant + 1 x Altair
Bolo.
Alternate Designation of SLAM intercontinental cruise missile.
Bomarc.
Popular Name of CIM-10A surface-to-air missile.
USAF Mach 3 ramjet surface-to-air missile; later converted to target missiles and launched from Vandenberg AFB.
Bomarc B.
Popular Name of CIM-10B surface-to-air missile.
Intercontinental supersonic cruise missile. A follow-on to the Snark that was Northrop's competitor with the North American Navaho. Never reached development stage and no details available. Name obviously derived from the punchline of Lewis Carroll's poem: "...for the Snark was a Boojum, you see..."
American sounding rocket. Two stage vehicle consisting of a booster + 1 x Arcas second stage.
American sounding rocket. Two stage vehicle consisting of 1 x MARC 42A1 + 1 x Arcas
American sounding rocket. Single stage vehicle.
BQ-1/BQ-2.
Department of Defence Designation of BQ-1-BQ-2 intermediate range cruise missile.
American intermediate range cruise missile. In March 1942, the USAAF initiated a program to develop radio-controlled assault drones, frequently called "aerial torpedoes" at that time. These aerial torpedoes were to be unmanned expendable aircraft (either purpose-built or converted from existing types), fitted with a large payload of high-explosive, remote-control equipment and a forward-looking TV camera. The drones were to be directed to the target by radio commands from a control aircraft, where the operator would "fly" the drone watching the video transmitted by the camera.
BQ-3.
American intermediate range cruise missile. In October 1942, Fairchild received a contract to build two XBQ-3 prototype unmanned assault drones based on the AT-21 Gunner twin-engined trainer design.
BQ-4.
Department of Defence Designation of BQ-4-TDR intermediate range cruise missile.
Early family of American unmanned remotely-controlled aircraft for use in combat.
BQ-7.
Department of Defence Designation of Aphrodite intermediate range cruise missile.
BQ-8.
American intermediate range cruise missile. In 1944 the USAAF intended to convert some worn-out Consolidated B-24D/J Liberator bombers to BQ-8 radio-controlled assault drones for use against heavily defended targets on Japanese islands in the Pacific. The concept was the same as used for the B-17 Flying Fortress conversions in the BQ-7 Aphrodite project.
American intermediate range cruise drone. Drone version.
American anti-ballistic missile. ABM-missiles, SDIO/BMDO project
Japanese sounding rocket. Derivative of S-310.
BTDS.
American anti-ballistic missile. SDIO/BMDO project, Baseline Terminal Defense System (ex-LoADS), with Sentry
Russian intercontinental ballistic missile. Solid-propellant Soviet intercontinental-range ballistic missile, equipped with multiple independently targeted warheads.
American sounding rocket. Two stage vehicle consisting of 1 x Bullpup + 1 x Apache
American sounding rocket. Two stage vehicle consisting of 1 x Bullpup + 1 x Cajun
American test vehicle in the 1940's. The primary goal of the U.S. Navy's Bumblebee missile program was to develop a ramjet-powered surface-to-air missile. Bumblebee test vehicles and technologies led to the operational Terrier and Talos missile of the 1950's.
German short range ballistic test vehicle. Pioneering US demonstration of a two stage launch vehicle, coupling a V-2 with a WAC Corporal. The first ballistic missile fired from Cape Canaveral.
Russian intercontinental cruise missile. A government decree on 20 May 1954 authorised the Myasishchev aircraft design bureau to proceed with full-scale development of the Buran trisonic intercontinental cruise missile. The competing Burya design of Lavochkin was launched in July 1957, but the development of unstoppable ICBM's had made intercontinntal cruise missiles oboslete. The equivalent American Navaho project was cancelled ten days later. Korolev's R-7 ICBM completed its first successful test flight in August. Buran was being prepared for its first flight when Myasishchev's project was cancelled on November 1957.
Fully recoverable version of Energia launch vehicle, with four winged boosters and a winged core stage.
Russian air-launched winged orbital launch vehicle. Burlak air-launched satellite launcher was proposed in 1992 and studied by Germany in 1992-1994. Evidently based on secret anti-satellite missile. Air launched from Tu-160 bomber, released at 13,500 m altitude and Mach 1.7. Development estimated to cost only DM 50 million, but not proceeded with. Burlak/Diana variant would have been launched from Concorde.
A government decree on 20 May 1954 authorised the Lavochkin aircraft design bureau to proceed with full-scale development of the Burya trisonic intercontinental cruise missile. Burya launches began in July 1957. The project was cancelled, but the team was allowed final tests in 1961 that demonstrated a 6,500 km range at Mach 3.2 with the 2,350 kg payload. In cancelling Burya the Russians gave up technology that Lavochkin planned to evolve into a manned shuttle-like recoverable launch vehicle.
Butterfly.
Alternate Designation of Schmetterling surface-to-air missile.
C-1.
Library of Congress Designation of Kosmos 65S3, Kosmos 65MP, Kosmos 11K65, and Kosmos 11K65M orbital launch vehicles.
American sounding rocket. The Cajun research rocket was developed as a dimensionally-similar but higher performance successor to the Deacon.
American sounding rocket. Single stage vehicle.
CALCM.
Popular Name of AGM-86C air-to-surface missile.
American air-launched orbital launch vehicle. Heavily classifed project related to air-launched ASAT development. Launch tests in 1958. NOTS project staff believed they successully orbited a satellite but unconfirmed.
Argentinan sounding rocket. Single stage vehicle.
Argentinan sounding rocket. Single stage vehicle.
Spanish all-solid orbital launch vehicle. Small all-solid-propellant launch vehicle pursued by Spain in 1992-1999. Cancelled in 2000 before any flights could be made.
Cargo Launch Vehicle.
Alternate designation for Ares V heavy-lift orbital launch vehicle.
American suborbital launch vehicle. Single stage version.
Argentinan sounding rocket. Two stage vehicle consisting of 4 x Canopus + 1 x Canopus
American suborbital launch vehicle. 2 stage vehicle version of 2 x Recruit + 1 x Castor
American sounding rocket. Single stage vehicle. First launch 1996.07.15.
American sounding rocket. Two stage vehicle consisting of 1 x Castor + 1 x Lance
Castor-M57A1.
Alternate designation for ait-2 target missile.
American sounding rocket. Vehicle consisting 1 x Castor + 1 x Orbus 1, sometimes augmented with a Recruit booster stage.
American sounding rocket. Two stage vehicle consisting of 1 x Castor + 1 x Recruit
French sounding rocket. Two stage sounding rocket. The Belier I II, or III single stage sounding rocket was augmented by a Venus booster with 94 kg of solid propellant. The rocket was spin stabilised by small solid rocket engines on the four fins.
French sounding rocket.
French sounding rocket.
French sounding rocket.
French sounding rocket.
American intermediate range cruise missile.
American intermediate range cruise missile.
CGM-16C.
Department of Defence Designation of Atlas C test vehicle.
American intercontinental ballistic missile. ICBM version
CGM-16F.
Department of Defence Designation of HGM-16F intercontinental ballistic missile.
Chinese winged orbital launch vehicle. The Chang Cheng 1 (Great Wall 1) vertical takeoff / horizontal landing two-stage space shuttle was a compromise design created jointly by Shanghai Astronautics Bureau 805 (now the Shanghai Academy of Spaceflight Technology) and Institute 604 of the Air Ministry in 1988. An expendable booster, consisting of three of Shanghai's planned liquid oxygen/kerosene modular boosters, would boost the winged second stage shuttle to a high altitude. The engines of the winged shuttle stage would take it to orbit. This approach would allow a first flight to be made in 2008.
Chang Zheng 1.
Alternate designation for CZ-1 orbital launch vehicle.
Chang Zheng 1D.
Alternate designation for CZ-1D orbital launch vehicle.
Chang Zheng 2A.
Alternate designation for CZ-2A orbital launch vehicle.
Chang Zheng 2C.
Alternate designation for CZ-2C orbital launch vehicle.
Chang Zheng 2C-III/SD.
Alternate designation for CZ-2C-SD orbital launch vehicle.
Chang Zheng 2D.
Alternate designation for CZ-2D orbital launch vehicle.
Chang Zheng 2E.
Alternate designation for CZ-2E orbital launch vehicle.
Chang Zheng 2F.
Alternate designation for CZ-2F orbital launch vehicle.
Chang Zheng 3.
Alternate designation for CZ-3 orbital launch vehicle.
Chang Zheng 3A.
Alternate designation for CZ-3A orbital launch vehicle.
Chang Zheng 3B.
Alternate designation for CZ-3B orbital launch vehicle.
Chang Zheng 4.
Alternate designation for CZ-4A orbital launch vehicle.
Chang Zheng 4B.
Alternate designation for CZ-4B orbital launch vehicle.
Chang Zheng 4C.
Alternate designation for CZ-4C orbital launch vehicle.
Chang Zheng Next Generation Launch Vehicle Type A.
Manufacturer's designation for CZ-NGLV-522-HO orbital launch vehicle.
Chang Zheng Next Generation Launch Vehicle Type B.
Manufacturer's designation for CZ-NGLV-504-HO orbital launch vehicle.
Chang Zheng Next Generation Launch Vehicle Type C.
Manufacturer's designation for CZ-NGLV-540-HO orbital launch vehicle.
Chang Zheng Next Generation Launch Vehicle Type D.
Manufacturer's designation for CZ-NGLV-504 orbital launch vehicle.
Chang Zheng Next Generation Launch Vehicle Type E.
Manufacturer's designation for CZ-NGLV-522 orbital launch vehicle.
Chang Zheng Next Generation Launch Vehicle Type F.
Manufacturer's designation for CZ-NGLV-540 orbital launch vehicle.
Chang Zheng-1.
Manufacturer's designation for CZ-1 orbital launch vehicle.
Chang Zheng-1C.
Manufacturer's designation for CZ-1C orbital launch vehicle.
Chang Zheng-1D.
Manufacturer's designation for CZ-1D orbital launch vehicle.
Chang Zheng-1M.
Manufacturer's designation for CZ-1M orbital launch vehicle.
Chang Zheng-2A.
Manufacturer's designation for CZ-2A orbital launch vehicle.
Chang Zheng-2C.
Manufacturer's designation for CZ-2C orbital launch vehicle.
Chang Zheng-2C/SD.
Manufacturer's designation for CZ-2C-SD orbital launch vehicle.
Chang Zheng-2D.
Manufacturer's designation for CZ-2D orbital launch vehicle.
Chang Zheng-2E.
Manufacturer's designation for CZ-2E orbital launch vehicle.
Chang Zheng-2E(A).
Manufacturer's designation for CZ-2E(A) orbital launch vehicle.
Chang Zheng-2F.
Manufacturer's designation for CZ-2F orbital launch vehicle.
Chang Zheng-3.
Manufacturer's designation for CZ-3 orbital launch vehicle.
Chang Zheng-3A.
Manufacturer's designation for CZ-3A orbital launch vehicle.
Chang Zheng-3B.
Manufacturer's designation for CZ-3B orbital launch vehicle.
Chang Zheng-3B(E).
Manufacturer's designation for CZ-3B(A) orbital launch vehicle.
Chang Zheng-3C.
Manufacturer's designation for CZ-3C orbital launch vehicle.
Chang Zheng-4A.
Manufacturer's designation for CZ-4A orbital launch vehicle.
Chang Zheng-4B.
Manufacturer's designation for CZ-4B orbital launch vehicle.
Chang Zheng-4C.
Manufacturer's designation for CZ-4C orbital launch vehicle.
Chang Zheng-5-2.25.
Manufacturer's designation for CZ-NGLV-200 orbital launch vehicle.
China Type E.
Alternate designation for Project 921 orbital launch vehicle.
Chinese orbital launch vehicle. By the late 2000 a leading candidate for China's first reusable launch vehicle was a CALT-designed two-stage fully reusable rocket similar to the Kistler K-1.
In January 1995 the Chinese army unveiled a 21 m long supergun capable of firing large artillery shells into South Korea and Taiwan. The gun could fire 85 mm shells over a 300 km range. Nothing further was heard of the weapon. Interestingly, China was one of the countries that retained Gerard Bull as a consultant in artillery design in the 1980's. It would seem that the supergun retained its military appeal as a psychological weapon or in anti-satellite applications.
Taiwanese short range ballistic missile.
Russian surface-to-air missile.
Chusovaya.
Launch System of R-14U intermediate range ballistic missile.
CIM-10.
Department of Defence designation of Bomarc missile.
American surface-to-air missile. Also XIM-10, YIM-10.
American surface-to-air missile. CQM-10 drone version
Cirrus was a two-stage sounding rocket developed by the German Rocket Society in the late 1950's. All launches were made from Cuxhaven, and discontinued when the German government prohibited civilian rocket launches in June 1964. The propellant was developed by the DRG and fabricated at Liebenau Company for Production of Chemical Materials (GmbH zur Verwertung chemischer Erzeugnisse Liebenau).
Cirrus B.
Alternate designation for Cirrus II sounding rocket.
German sounding rocket. Cirrus I could carry meteorological or biological payloads up to a speed of 1000 m/s and an altitude of 35 km.
German sounding rocket. Cirrus II could carry meteorological or biological payloads to a speed of over 1000 m/s and an altitude of 50 km. The first stage produced 1800 kgf and the second 508 kgf.
American test vehicle. Single stage vehicle.
Clipper Graham.
Alternate Designation of DC-X vtovl test vehicle.
CLV.
Alternate Designation of Ares I heavy-lift orbital launch vehicle.
French studies in the 1960's were supervised by the French Space Agency, CNES, and developed along two paths. Path 1 was a manned hypersonic booster stage, with upper stages coming in manned or unmanned variants according to the mission. Path 2 was more conservative, with either the Path 1 booster or an expendable booster launching a small re-entry vehicle - a 'Space Taxi'.
American test vehicle, part of the U.S. Navy's Bumblebee missile program that led to the operational Talos ramjet-powered surface-to-air missile in the 1950's.
The Cockatoo solid-propellant sounding rocket replaced HAD at Woomera in 1970, and consisted of a British Gosling I first stage and an Australian Lupus 1 second stage.
American orbital launch vehicle. Commercial version of Titan 34D military booster. It differed in having a lengthened second stage and a 4 m diameter payload shroud to handle shuttle-class or Ariane-type dual payloads.
American orbital launch vehicle. The January 1951 design for the Atlas used seven main engines plus two vernier engines to hurl the 3600 kg nuclear warhead over a 9300 km range. CEP was optimistically estimated as 460 m.
Argentinan intermediate range ballistic missile.
Argentinan short range ballistic missile.
Argentinan intermediate range ballistic missile.
American low cost orbital launch vehicle.
American all-solid orbital launch vehicle. Four stage vehicle consisting of 4 x Castor 4B + 2 x Castor 4B + 1 x Castor 4B + 1 x Star 48V
Consolidated BQ-8.htm.
Alternate designation for BQ-8 intermediate range cruise missile.
American orbital launch vehicle. The 1954 design for the Atlas as contracted for by the Air Force used three main engines to power a 110 metric ton rocket able to send a 1400 kg nuclear warhead over a 10,200 km range. CEP was 3700 m. The missile actually delivered six years later would have the same dimensions and launch mass, but 63% more range and four times better accuracy.
Conventional Air-Launched Cruise Missile.
Alternate designation for AGM-86C air-to-surface missile.
American winged orbital launch vehicle. DARPA program of 1984 that proved the technologies and concept for the X-30 National Aerospace Plane concept.
Copper Canyon Phase 2.
Alternate designation for X-30 ssto winged orbital launch vehicle.
Cora.
European orbital launch vehicle. Cora was an experimental rocket to test the second and third stages of the Europa launch vehicle.
Australian sounding rocket. Two stage vehicle consisting of 1 x Gosling + 1 x Dorado
Corporal.
American short range liquid-propellant ballistic missile. The first American operational guided missile, deployed 1954-1964. Replaced by the Sergeant solid-propellant missile.
American short range ballistic missile. Experimental version of Corporal Missile
American short range ballistic missile. First prototype of Corporal missile.
American short range ballistic missile. Second prototype of Corporal Missile
American sounding rocket.
Crew Launch Vehicle.
Alternate designation for Ares I heavy-lift orbital launch vehicle.
American air-to-surface missile, development started in 1953. Program cancelled in 1957.
CSL-1.
Department of Defence Designation of CZ-1 orbital launch vehicle.
CSL-2.
Department of Defence Designation of CZ-2A orbital launch vehicle.
CSL-3.
Department of Defence Designation of CZ-3 orbital launch vehicle.
CSS-1.
Department of Defence Designation of DF-2 intermediate range ballistic missile.
CSS-10.
Department of Defence Designation of DF-41 intercontinental ballistic missile.
CSS-2.
Department of Defence Designation of DF-3 intermediate range ballistic missile.
CSS-3.
Department of Defence Designation of DF-4 intermediate range ballistic missile.
CSS-4.
Department of Defence Designation of DF-5 intercontinental ballistic missile.
CSS-5.
Department of Defence Designation of DF-21 intermediate range ballistic missile.
CSS-6.
Department of Defence designation of DF-15 missile.
CSS-7.
Department of Defence Designation of DF-11 short range ballistic missile.
CSS-8.
Department of Defence Designation of M-7 short range ballistic missile.
CSS-9.
Department of Defence Designation of DF-31 intercontinental ballistic missile.
CSS-C-3.
Alternate designation for JL-1 submarine-launched ballistic missile.
CSS-N-3.
Department of Defence Designation of JL-1 submarine-launched ballistic missile.
CSS-N-4.
Department of Defence Designation of JL-2 intercontinental ballistic missile.
CSST-600.
Alternate Designation of M-9 intermediate range ballistic missile.
CTV-G-5.
Popular Name of Hermes A-1 tactical ballistic missile.
CTV-N-8.
Department of Defence Designation of Bumblebee STV test vehicle.
Cyclone 3.
Popular Name of Tsiklon-3 orbital launch vehicle.
Cyclone 4.
Popular Name of Tsiklon-4 orbital launch vehicle.
CZ.
Chinese orbital launch vehicle. China's first ICBM, the DF-5, first flew in 1971. It was a two-stage storable-propellant rocket in the same class as the American Titan, the Russian R-36, or the European Ariane. The DF-5 spawned a long series of Long March ("Chang Zheng") CZ-2, CZ-3, and CZ-4 launch vehicles. These used cryogenic engines for upper stages and liquid-propellant strap-on motors to create a family of 12 Long-March rocket configurations capable of placing up to 9,200 kg into orbit. In 2000 China began development of a new generation of expendable launch vehicles using non-toxic, high-performance propellants with supposedly lower operating costs. However these encountered development delays, and it seemed the reliable Long March series of rockets would continue in operational use for nearly fifty years before being replaced.
CZ-1.
Chinese orbital launch vehicle. China began development of the CZ-1 (Changzheng-1 = Long March-1) launch vehicle in the second half of 1965. The project was undertaken with the specific objective of launching China's first satellite, the DFH-1. The CZ-l's first and second stages were adapted from those of the DF-3 intermediate range ballistic missile. The third stage used a new-design solid rocket motor.
Chinese orbital launch vehicle. Proposed launch vehicle derived from the CZ-1, with a new upper stage. Never flown.
Chinese orbital launch vehicle. Proposed launch vehicle derived from the CZ-1, but with a new N2O4/UDMH second stage. Used for a suborbital re-entry vehicle test but never flown on an orbital mission.
Chinese orbital launch vehicle. Proposed launch vehicle derived from CZ-1, with an Italian Mage upper stage. Never flown.
Chinese orbital launch vehicle. Tsien's manned spacecraft design proposed in the late 1970's was a winged spaceplane, launched by a CZ-2 core booster with two large strap-on boosters. It so strongly resembled the cancelled US Dynasoar of 15 years earlier that US intelligence analysts wondered if it wasn't based on declassified Dynasoar technical information.
Chinese orbital launch vehicle. The CZ-2 was originally designed for launch of the FSW-1 recoverable military reconnaissance satellite.
Chinese orbital launch vehicle. The CZ-2C was the definitive low earth orbit launch vehicle derived from DF-5 ICBM. It became the basis for an entire family of subsequent Long March vehicles. Many adaptive modifications were made to the configuration of the CZ-2A to handle a variety of new satellites and upper stages. The CZ-2C had improved technical performance and payload capacity compared to the CZ-2A, with later versions having a payload capability of 2,800 kg into a 200 km circular orbit.
CZ-2C/CTS.
Article Number of CZ-2C-SD orbital launch vehicle.
On April 28, 1993, the Chinese Great Wall Industrial Corporation and Motorola signed a launch services contract for multiple launch of Iridium communications satellites using CZ-2C/SD launch vehicles. The main differences between the CZ-2C and the CZ-2C/SD were: a modified fairing with a diameter of 3.35m; a newly developed Smart Dispenser; improved second stage fuel and oxidizer tanks; and second stage engines with higher expansion ratio nozzles.
Chinese orbital launch vehicle. The Long March 2D was a two-stage launch vehicle with storable propellants, suitable for launching a variety of low earth orbit satellites. Developed and manufactured by the Shanghai Academy of Spaceflight Technology, the CZ-2D had a typical payload capability of 3,500kg in a 200 km circular orbit. Its first stage was identical to that of the CZ-4. The second stage was essentially the same as that of the CZ-4, except for an improved vehicle equipment bay.
Chinese orbital launch vehicle. The CZ-2E added four liquid rocket booster strap-ons to the basic CZ-2 core to achieve a low earth orbit payload capability approaching the Russian Proton, US Titan, or European Ariane rockets. The Long March 2E had a maximum payload capability of 9,500 kg to low earth orbit.
Planned upgrade of CZ-2E with enlarged liquid boosters. Probably intended for launch of Chinese space station modules in the 21st century. Fairing was 5.20 m in diameter and 12.39 m long.
Chinese orbital launch vehicle. Man-rated version of CZ-2E, designed for launch of the Shenzhou spacecraft. Little difference externally. Modifications were related to improved redundancy of systems, strengthened upper stage to handle large 921-1 spacecraft fairing and launch escape tower. President Jiang Zemin gave the name 'Shenjian' ('Divine Arrow') to the CZ-2F after the successful launch of the Shenzhou-3 mission.
CZ-3.
Chinese orbital launch vehicle. The Long March 3 was a three-stage launch vehicle designed for delivery of satellites of 1,500 kg mass into geosynchronous transfer orbit. The first and second stages were based on the CZ-2C, and designed and manufactured by the Shanghai Academy of Spaceflight Technology. The majority of the technology and flight hardware used in the CZ-3 had been qualified and proven on the CZ-2C. The third stage, manufactured by CALT, was equipped with an LOX/LH2 cryogenic engine. Long March 3 was also capable of placing spacecraft into an elliptical or circular low earth orbit and sun synchronous orbit.
Chinese three-stage orbital launch vehicle. The Long March 3A, by incorporating the mature technologies of the CZ-3 and adding a more powerful cryogenic third stage and more capable control system, had a greater geosynchronous transfer orbit capability, greater flexibility for attitude control, and better adaptability to a variety of launch missions.
Chinese orbital launch vehicle. The Long March 3B was the most powerful Long March launch vehicle. It could inject a 5,000 kg payload into geosynchronous transfer orbit. The CZ-3B was developed on the basis of the CZ-3A, but had enlarged propellant tanks, larger fairing, and four boosters strapped onto the core stage. The CZ-3B boosters were identical to those of the CZ-3A.
Chinese orbital launch vehicle. In February 1999 the China Great Wall Company announced it was developing more powerful Long March rockets using larger-size liquid propellant strap-on motors. The Long March 3B(A) would be available in 2002.
Chinese orbital launch vehicle. Launch vehicle combining CZ-3B core with two boosters from CZ-2E. The standard fairing was 9.56 m long, 4.0 m in diameter. On August 23, 2001, the CZ-3C launcher passed its critical design review. CZ-3C development had begun in 1995 but was suspended in 1996-2000 due to the 1996 CZ-3B failure. First launch was in 2008.
Chinese orbital launch vehicle. The CZ-4 was developed and manufactured by the Shanghai Academy of Spaceflight Technology. Its first stage was essentially the same as that of the CZ-3 and the second stage was identical to that of the CZ-3. The CZ-4's third stage, however, was a development, featuring a thin wall common intertank bulkhead tankage and two-engine cluster with both engines gimbling about two perpendicular axes. The third stage engine cluster connected to the tank aft bulkhead through the engine bay. The CZ-4 had two payload fairing configurations: Type-A and Type-B. The CZ-4 was designed for launching satellites into polar and sun-synchronous orbits.
Chinese orbital launch vehicle. The CZ-4B introduced in 1999 was an improved model of the CZ-4B with an enhanced third stage and fairing. It measured 44.1 metres in length with a first stage thrust of 300 tonnes.
Chinese orbital launch vehicle. The CZ-4C, first flown in 2007, had an upgraded second-stage engine that could be restarted in space. The vehicle also had structural rings at the base of the first and second stages, an interstage weather cover,ejected at liftoff, and the larger payload shroud introduced on the CZ-4B. All of these indicated that the vehicle was designed to take larger payloads to higher, more precise orbits than the CZ-4B.
CZ-5-2.25.
Alternate Designation of CZ-NGLV-200 orbital launch vehicle.
CZ-5-3.35.
Alternate Designation of CZ-NGLV-320 orbital launch vehicle.
Chinese orbital launch vehicle. China's family of new generation expendable launch vehicles began development in 2000. Boosters of various capabilities would be assembled from three modular stages of 2.25 m, 3.35 m and 5.0 m diameter. These would be powered by new variable-thrust 120 tonne thrust Lox/Kerosene engines or 50 tonne thrust Lox/LH2 engines.
Chinese orbital launch vehicle. The Long March New Generation Launch Vehicle series small launcher would use the 2.25 m diameter module as the first stage and a single upper stage of the same diameter (probably the existing YF-73 stage of the CZ-3). Payload was given as 1.5 tonnes into low earth orbit. First launch was expected after 2008. Although the configuration was not shown at the Wuzhai Air Show in 2002 it re-emerged at the FAI in 2003. It seemed to be in competition with the all-solid-propellant KT-1, KT-2, and KT-2A series.
Chinese orbital launch vehicle. The Long March New Generation Launch Vehicle series medium launcher would use the 3.35 m diameter module and a new 3.35 m diameter second stage as the core vehicle. Either two or four 2.25 m diameter modules would be used as strap-ons. Payload to low earth orbit would be three tonnes with two strap-ons and 10 tonnes with four strap-ons.
The 504 configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m diameter core stage with four 3.35 m diameter stages as strap-ons. Payload was given as 25 tonnes to low earth orbit. A standard large 5.2 m diameter fairing tops the vehicle. It would be used to launch the Chinese Space Laboratory in 2010.
Chinese orbital launch vehicle. The 504/HO configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m core stage, topped by the 5.0 m upper stage, together with 4 x 3.35 m strap-on stages. First flight of this version was expected after 2010. Payload was given as 14 tonnes to geosynchronous transfer orbit.
Chinese orbital launch vehicle. The 522 configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m diameter core stage with 2 x 2.25 m plus 2 x 3.35 m strap-on stages. Payload is estimated as 18-20 tonnes to low earth orbit.
Chinese orbital launch vehicle. The 522/HO was the 'all up' baseline configuration for the Long March New Generation Launch Vehicle series. It would use the 5.0 m core stage, topped by the 5.0 m upper stage, together with 2 x 2.25 m plus 2 x 3.35 m strap-on stages. It was announced in 2003 that it would be first to fly, with a launch before the Beijing Olympics in 2008. It would be used for launch of large communications satellites. Payload is estimated as 10-12 tonnes to geosynchronous transfer orbit.
Chinese orbital launch vehicle. The 540 configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m diameter core stage with four 2.25 m diameter stages as strap-ons. Payload was given as 10 tonnes to low earth orbit. A standard short 5.2 m diameter fairing tops the vehicle.
Chinese orbital launch vehicle. The 540/HO configuration for the Long March New Generation Launch Vehicle series would use the 5.0 m core stage, topped by the 5.0 m upper stage, together with 4 x 2.25 m strap-on stages. First flight of this version was expected after 2010. Payload was given as 6 tonnes to geosynchronous transfer orbit.
CZ-NGLV-A.
Popular Name of CZ-NGLV-522-HO orbital launch vehicle.
CZ-NGLV-B.
Popular Name of CZ-NGLV-504-HO orbital launch vehicle.
CZ-NGLV-C.
Popular Name of CZ-NGLV-540-HO orbital launch vehicle.
CZ-NGLV-D.
Popular Name of CZ-NGLV-504 orbital launch vehicle.
CZ-NGLV-E.
Popular Name of CZ-NGLV-522 orbital launch vehicle.
CZ-NGLV-F.
Popular Name of CZ-NGLV-540 orbital launch vehicle.
CZ-NGLV-Light.
Popular Name of CZ-NGLV-200 orbital launch vehicle.
CZ-NGLV-Medium.
Popular Name of CZ-NGLV-320 orbital launch vehicle.
D.
Alternate designation for Tu-133 intercontinental cruise missile.
D.
Library of Congress designation of UR-500 missile.
D-1.
Launch System of R-11FM submarine-launched ballistic missile.
D-1.
Library of Congress Designation of Proton-K orbital launch vehicle.
D-1.
Russian tactical ballistic missile. Korolev design for a 'long range' rocket prior to orders to copy the V-2. The 1000 kg rocket would have a range of 32 km. Wingspan 1.0 m; 370 kg propellants; minimum range 12..8 km; maximum velocity 854 m/s; maximum altitude 12.5 km.
D-11.
Launch System of R-31 submarine launched ballistic missile.
D-19 Rif.
Launch System of 3M20 submarine-launched ballistic missile.
D-19M.
Launch System of Bulava intercontinental ballistic missile.
D-19UTH Grom.
Launch System of R-39M submarine-launched ballistic missile.
D-1e.
Library of Congress Designation of Proton-K-D, Proton-K-D-1, Proton-K-D-2, Proton-K-DM, Proton-K-DM-2, Proton-K-DM-2M, and Proton-K-17S40 orbital launch vehicles.
D-2.
Launch System of R-13 missile.
D-2.
Russian tactical ballistic missile. Korolev design for a 'long range' rocket prior to orders to copy the V-2. Extended-range winged version of the D-1. The 1200 kg rocket would have a range of 76 km. Wingspan 1.5 m; 370 kg propellants; minimum range 20 km; maximum velocity 628 m/s; maximum altitude 10.7 km.
D-21.
American air-launched drone. Project 'Tagboard', Project 'Senior Bowl'. Mach 3.5 ramjet recoverable reconnaisance drone air-launched from back of A-12 or with booster rocket from B-52.
D-3.
Launch System of R-15 submarine-launched ballistic missile.
D-4.
Launch System of R-21 submarine-launched ballistic missile.
D-5.
Launch System of R-27 submarine-launched ballistic missile.
D-6.
Russian submarine-launched ballistic missile. First Soviet solid propellant submarine launched ballistic missile. Development began in 1958, but the system was cancelled in 1961 in favour of the D-7 naval version of the RT-15 IRBM (itself in turn cancelled).
D-7.
Launch System of RT-15M submarine-launched ballistic missile.
D-8.
Launch System of R-29, R-29D, and UR-100M SLBM submarine-launched ballistic missiles.
D-9.
D-9RM Shtil.
Launch System of R-29RM submarine-launched ballistic missile.
American nuclear-powered orbital launch vehicle. Douglas/Bono 1963 concept for a chemical-boosted / nuclear upper stage launch vehicle, designed as alternatives to the Convair/Ehricke Helios. The baseline version used a nuclear, recoverable upper stage boosted above the atmosphere by a minimum chemical stage.
American nuclear-powered orbital launch vehicle. As the basic design, but featuring an Improved Specific Impulse chemical stage that used many engines feeding into single large nozzle.
American sounding rocket. Single stage vehicle.
Dal.
Russian surface-to-air missile. Trials of this long range surface-to-air missile were conducted in 1960-1963 but the project was cancelled after the system failed to down a single target. V-200 missiles were installed in the Dal installations built around Leningrad for the failed missile. In a bit of disinformation, the V-400 was paraded in Moscow, and US intelligence, thinking it was operational, applied the SA-5 designation. The SA-5 code was transferred to the V-200 after the La-400 was cancelled.
Russian surface-to-air missile. Planned next generation high performance long-range surface-to-air missile developed 1959-1963. Cancelled together with basic the Dal system at the end of 1963.
Dal-M.
Launch System of Dal-2 surface-to-air missile.
Russian surface-to-air missile. Planned improved version of the Dal high performance long-range surface-to-air missile developed 1959-1963. Cancelled together with basic the Dal system at the end of 1963.
French test vehicle. Three stage test vehicle for Israel's Jericho consisting of 1 x SPRAN-50 + 1 x MD-620 + 1 x Melanie
American low cost orbital launch vehicle. Lockheed Martin all-hybrid propulsion, mobile orbital launch system that could launch from an unimproved site with limited infrastructure on 24 hours notice, placing up to 840 kilograms into LEO
Dart.
American surface-to-surface anti-tank missile. Development started in 1953 Program cancelled in 1958 in favor of the the French SS.10.
French sounding rocket. Single stage sounding rocket consisting of a single Stromboli motor.
American tactical ballistic rocket.
American tactical ballistic rocket.
DC-I.
Alternate designation for DC-Y ssto vtovl orbital launch vehicle.
DC-X.
American VTOVL test vehicle. The DC-X was an experimental vehicle, 1/3 the size of a planned DC-Y vertical-takeoff/vertical-landing, single stage to orbit prototype. It was not designed as an operational vehicle capable of achieving orbital flight. Its purpose was to test the feasibility of both suborbital and orbital reusable launch vehicles using the VTOVL scheme. The DC-X flew in three test series. The first series ran from August 18 to September 30, 1993, before the initial project funding ran out in late October 1993. Additional funding was provided and a second series was conducted June 1994-July 1995.
American SSTO VTOVL orbital launch vehicle. Proposed intermediate 1/2 scale test vehicle between DC-X and DC-Y orbital version. No government agency was willing to fund the $450 million development cost -- and neither were any private investors.
DC-XA.
Alternate designation for DC-X vtovl test vehicle.
American VTOVL test vehicle. After a hard landing in the last flight of this series, the vehicle was rebuilt to the DC-XA configuration. The DC-XA flew from May 1996 until destroyed when it tipped over while landing on its fourth flight on 31 July 1996.
DC-Y.
American SSTO VTOVL orbital launch vehicle. The ultimate goal of the Delta Clipper program, a prototype reusable single-stage to orbit, vertical takeoff/vertical landing space truck. The DC-I Delta Clipper would be the full production version. No government sponsor could be found for the concept and the $ 5 billion development cost was never funded. If it had been funded in 1991, the first DC-Y suborbital flight was predicted for 1995, and a first orbital mission in 1997.
American test vehicle. The Deacon was an advanced solid rocket motor design cancelled at the end of World War II. In 1947 NACA began using reworked surplus motors to boost instrumented subscale aircraft models to speeds of up to Mach 4. They became a workhorse for the Agency's aerodynamic research, resulting in new production. Thousands were flown, until, by the end of the 1950's, supersonic wind tunnels took over the job. Data shown is for single-stage version.
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x Arrow II
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x Deacon
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x HVAR
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x Judi III
American sounding rocket. The Rockoon concept involved release of a 12 m diameter balloon from a ship, which took a Deacon sounding rocket to 9 to 27 km altitude in 80 minutes. The rocket was ignited at a preset time or altitude or by remote control, and then boosted an 18 kg payload to a 50 to 100 km altitude. The Deacon was painted black and wrapped in plastic to protect it against the cold, and fitted with larger fins for stability at high altitude.
Two stage version of Rockoon balloon-launched soundinr coekt consisting of a Deacon first stage and Loki second stage.
American test vehicle. Two stage vehicle consisting of 1 x Deacon + 1 x HPAG
American orbital launch vehicle. The Delta launch vehicle was America's longest-lived, most reliable, and lowest-cost space launch vehicle. Delta began as Thor, a crash December 1955 program to produce an intermediate range ballistic missile using existing components, which flew thirteen months after go-ahead. Fifteen months after that, a space launch version flew, using an existing upper stage. The addition of solid rocket boosters allowed the Thor core and Able/Delta upper stages to be stretched. Costs were kept down by using first and second-stage rocket engines surplus to the Apollo program in the 1970's. Continuous introduction of new 'existing' technology over the years resulted in an incredible evolution - the payload into a geosynchronous transfer orbit increasing from 68 kg in 1962 to 3810 kg by 2002. Delta survived innumerable attempts to kill the program and replace it with 'more rationale' alternatives. By 2008 nearly 1,000 boosters had flown over a fifty-year career, and cancellation was again announced.
American orbital launch vehicle. The military Thor-Delta vehicles were developed into the first of a series of commercial satellite launch vehicles. The Delta 0100 series featured Castor 2 solid propellant strap-ons and a Long Tank Thor core with MB-3 engine.
American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x DSV-3N-4
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x DSV-3N-4
American orbital launch vehicle. The Delta 1000 series used Castor 2 strap-ons and the Extended Long Tank core with MB-3 engine.
American orbital launch vehicle. Three stage vehicle consisting of 4 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201
American orbital launch vehicle. Four stage vehicle consisting of 6 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta F + 1 x Star 37C
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta F
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201 + 1 x Star 37D
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/MB-3 + 1 x Delta P /TR-201 + 1 x Star 37C
American orbital launch vehicle. The Delta 6000 series used the Castor 4A strap-ons with the ultimate Extra Extended Long Tank core with RS-27 engine.
American orbital launch vehicle. The Delta 7000 series used GEM-40 strap-ons with the Extra Extended Long Tank core, further upgraded with the RS-27A engine.
American orbital launch vehicle. The Delta 2000 series used Castor 2 strap-ons together with an Extended Long Tank core equipped with the more powerful RS-27 engine. This engine was derived from surplus H-1 engines intended for the Saturn IB booster of the Apollo programme. The Delta P upper stage was built by Douglas and used surplus Apollo lunar module engines from TRW.
American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201
American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37D
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37D
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 2 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37E
American orbital launch vehicle. Delta 3 was an attempt by the manufacturer to provide the ultimate development of the original Delta booster. The core vehicle was beefed-up to accomodate much larger solid rocket boosters and a new cryogenic upper stage. However problems were incurred during development, resulting in the first two launches being failures. Meanwhile the satellite launch market crashed and the new vehicle was left without customers. The venerable Delta 7925 soldiered on for NASA, and the new Delta 4 series captured the USAF EELV requirement.
American orbital launch vehicle. The Delta 3000 series upgraded the boosters to Castor 4 solid propellant strap-ons, while retaining the Extended Long Tank core with RS-27 engine. The 3910 series used the TRW Lunar Module engine in the second stage, while the 3920 series reintroduced the Aerojet AJ110 Delta engine.
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P + 1 x Star 48B
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37N
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4 + 1 x ELT Thor/RS-27 + 1 x Delta P /TR-201 + 1 x Star 37E
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K + 1 x Star 48B
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K + 1 x Star 37E
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K + 1 x Star 48B
American orbital launch vehicle. The Delta 4000 series used more powerful Castor 4A strap-ons, but the old Extended Long Tank core with MB-3 engine. Only two of these were launched.
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor /MB-3 + 1 x Delta K + 1 x Star 48B with 2.4 m (8 foot) diameter fairing)
Delta 4H.
Alternate designation for Delta IV Heavy orbital launch vehicle.
Delta 4M.
Alternate designation for Delta IV Medium orbital launch vehicle.
Delta 4M+(4,2).
Alternate designation for Delta IV Medium+ (4.2) orbital launch vehicle.
American orbital launch vehicle. The Delta 5000 series used the more powerful Castor 4A strap-ons but with the Extended Long Tank core with RS-27 engine. Only one was launched.
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x ELT Thor/RS-27 + 1 x Delta K with 2.4 m (8 foot) diameter fairing)
American orbital launch vehicle. Three stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K with 2.4 m (8 foot) diameter fairing)
Three stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K with 3.05 m (10 foot) diameter fairing
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K + 1 x Star 48B
American orbital launch vehicle. Four stage vehicle consisting of 9 x Castor 4A + 1 x EELT Thor/RS-27+ 1 x Delta K + 1 x Star 48B with 2.4 m (8 foot) diameter fairing)
American orbital launch vehicle. Three stage vehicle consisting of 3 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K
American orbital launch vehicle.
American orbital launch vehicle. Four stage vehicle consisting of 3 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 37FM with 2.9 m (9.5 foot) diameter fairing)
American orbital launch vehicle.
Three stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter composite fairing
American orbital launch vehicle. Four stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 3.05 m (10 foot) diameter fairing
American orbital launch vehicle. Four stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 2.9 m (9.5 foot) diameter fairing)
American orbital launch vehicle. Four stage vehicle consisting of 4 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 37FM with 2.9 m (9.5 foot) diameter fairing)
American orbital launch vehicle. Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter long fairing
American orbital launch vehicle. Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 2.4 m (8 foot) diameter fairing)
American orbital launch vehicle. Version of Delta 7000 using much larger GEM 46 solid rocket motors originally developed for the Delta 3.
Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter fairing
Three stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K with 3.05 m (10 foot) diameter composite fairing
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 3.05 m (10 foot) diameter fairing
American orbital launch vehicle.
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 2.4 m (8 foot) diameter fairing)
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-40 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B with 2.9 m (9.5 foot) diameter fairing)
American orbital launch vehicle. Four stage vehicle consisting of 9 x GEM-46 + 1 x EELT Thor/RS-27A + 1 x Delta K + 1 x Star 48B
Delta 8930.
Alternate designation for Delta 3 orbital launch vehicle.
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-21 + 1 x AJ10-118 + 1 x Altair
American orbital launch vehicle. Three stage vehicle consisting of 1 x Thor DM-21 + 1 x AJ10-118A + 1 x Altair
American orbital launch vehicle. Unaugmented Thor with Delta D and solid propellant upper stages.
Delta Clipper.
Manufacturer's designation for DC-Y ssto vtovl orbital launch vehicle.
Delta Clipper Experimental.
Manufacturer's designation for DC-X vtovl test vehicle.
Delta Clipper-Experimental.
Alternate designation for DC-X vtovl test vehicle.
Delta Clipper-Prototype.
Alternate designation for DC-X2 ssto vtovl orbital launch vehicle.
American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta D + 1 x Altair 2
American orbital launch vehicle. Thor augmented with 3 x Castor 2 motors with Delta E and Altair 2 upper stage.
American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E + 1 x FW4D
American orbital launch vehicle. Three stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E
Delta III.
Alternate designation for Delta 3 orbital launch vehicle.
American orbital launch vehicle. The Delta IV was the world's first all-Lox/LH2 launch vehicle and represented the only all-new-technology launch vehicle developed in the United States since the 1970's. It was the winner of the bulk of the USAF EELV orders and was based on the all-new RS-68-powered Lox/LH2 cryogenic Common Booster Core (CBC). This could be used with new Delta cryogenic upper stages powered by the RL10 engine but unrelated to previous Centaur upper stages. It could be flown without augmentation, or use 2-4 large GEM-60 solid rocket boosters. The heavy lift version used two core vehicles as a first stage, flanking the single core vehicle second stage.
American orbital launch vehicle. Heavy lift all-cryogenic launch vehicle using two Delta-4 core vehicles as first stage flanking a single core vehicle as second stage. A heavy upper stage is carried with a 5 m diameter payload fairing.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding RS-68B upgraded engines to the core vehicles and an AUS-60 upper stage powered by 2 MB-45 or RL-45 20 tonne thrust Lox/LH2 engines. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters, RS-68 Regen upgraded engines with regeneratively-cooled nozzles to the core vehicles, and cryogenic propellant densification. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding new RS-800 engines to the core vehicles, an AUS-60 upper stage powered by 2 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters, RS-68 Regen upgraded engines with regeneratively-cooled nozzles to the core vehicles, cryogenic propellant densification, and an AUS-60 upper stage powered by 1 MB-60 or RL-60 27 tonne thrust Lox/LH2 engine. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 6 GEM-60 solid rocket boosters, RS-68B upgraded engines to the core vehicles, and an AUS-60 upper stage powered by 1 MB-60 or RL-60 27 tonne thrust Lox/LH2 engine. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by adding 4 GEM-60 solid rocket boosters, RS-68 Regen upgraded engines with regeneratively-cooled nozzles to the core vehicles, cryogenic propellant densification, and cryogenic propellant cross-feed between the strap-ons and core. 6.5 m diameter payload fairing. Introduction would require modifications to existing launch pads.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering five common booster modules, using an AUS-60 upper stage powered by 2 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, and using an AUS-60 upper stage powered by 2 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines. A payload fairing over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using an AUS-60 upper stage powered by 3 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines. A payload fairing over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using an AUS-60 upper stage powered by 3 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using a new RS-800K engine in the booster stages, and an AUS-60 27 tonne thrust Lox/LH2 upper stage. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Proposed upgrade to Delta IV Heavy by clustering seven common booster modules, using a new RS-800K engine in the booster stages, an AUS-60 upper stage powered by 4 MB-60 or RL-60 27 tonne thrust Lox/LH2 engines, and aluminium-lithium lightweight alloy in place of the existing aluminium in all stages. Payload fairings over 6.5 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure.
American orbital launch vehicle. Basic Delta-4 vehicle with no strap-ons, the core vehicle, and RL10B-1 upper stage with a 4 m diameter payload fairing. World's first all-cryogenic launch vehicle.
American orbital launch vehicle. As Delta 4 medium but with 2 x GEM-60 solid rocket boosters and a 4 m diameter payload fairing.
American orbital launch vehicle. As Delta 4 medium but with 2 x GEM-60 solid rocket boosters and a 5 m diameter payload fairing.
American orbital launch vehicle. As Delta 4 medium but with 4 x GEM-60 solid rocket boosters and a 5 m diameter payload fairing.
American orbital launch vehicle. Light launch vehicle using the Delta-4 core with the traditional Delta K and PAM-D upper stages. 2 m diameter payload fairing. Not flown as of 2008 but cancellation of the Delta II could lead to its eventual use.
American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor + 1 x Thor DSV-2C + 1 x Delta E + 1 x Star 37D
American orbital launch vehicle. Four stage vehicle consisting of 3 x Castor 2 + 1 x LT Thor DSV-2L-1B + 1 x Delta E + 1 x FW4D
American orbital launch vehicle. Long Tank Thor augmented with 3 Castor 2 boosters and Delta E / Burner 2 (Star 37D) upper stages.
American orbital launch vehicle. Four stage vehicle consisting of 6 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x Delta E + 1 x Star 37D
American orbital launch vehicle. Long Tank Thor augmented with 3 Castor 2 boosters and Delta E upper stage.
American orbital launch vehicle. Three stage vehicle consisting of 6 x Castor 2 + 1 x LT Thor DSV-2L-1C + 1 x Delta E
Russian intercontinental ballistic missile. Silo-launched version, silo hardened to 15-30 atmospheres overpressure.
Desna-N.
Alternate Designation of Romashka intercontinental ballistic missile.
Desna-V.
Launch System of Desna intercontinental ballistic missile.
DF-1.
Chinese version of Soviet R-2.
DF-1 (before 1964).
Alternate designation for DF-3 intermediate range ballistic missile.
Chinese single-stage solid-propellant short range ballistic missile. Export designation M-11, assembled as Ghaznavi in Pakistan.
Chinese mobile single-stage solid propellant intermediate range ballistic missile.
DF-2.
First Chinese IRBM, a single stage missile with the objective of carrying a 1500 kg warhead to Japan. The starting point for the design were R-12 construction drawings and a single exemplar of the missile provided by the Soviet Union prior to the break with Moscow in 1960. Following protracted development the design was accepted by the Chinese military for service in 1970.
Chinese two-stage solid propellant intermediate range ballistic missile.
Chinese intermediate range ballistic missile. Extended-range version of DF-2. The missile featured reduced thrust, but 20% more range, and used autonomous gyroscopic guidance in place of the DF-2's radio system.
DF-3.
Chinese intermediate range ballistic missile. The DF-3 project began in 1964 with the objective of developing a nuclear-tipped missile capable of reaching the Philippines (earlier referred to as the DF-1).
Development of the original DF-3 10,000 km missile was undertaken personally by Tsien Hue Shen, the father of Chinese rocketry, but faced insurmountable technical and management difficulties. It was cancelled and replaced by the DF-4.
Chinese intercontinental ballistic missile. Version of JL-2. Mobile, solid propellant, land-based, medium range, three-stage ballistic missile. Basis for the KT-1 light orbital launch vehicle.
Chinese intermediate range ballistic missile.
DF-4.
Chinese intermediate range ballistic missile. Development of the DF-4 began in 1964 with the objective of fielding a ballistic missile capable of hitting Guam. The technical solution was to add a second stage to the DF-3 IRBM.
New Chinese solid propellant, mobile ICBM. The DF-41 is expected to be a longer-range version of the DF-31. It is still in the development stage, with deployment not expected until after 2010.
DF-5.
Development of the the DF-5 began in 1964. The goal was an ICBM capable of reaching the United States. Although deployed in very limited numbers as an ICBM, this rocket became the basis for an entire family of space launch vehicles and the foundation of the Chinese space program.
Chinese intercontinental ballistic missile.
Chinese intercontinental ballistic missile. Modernised DF-5 incorporating guidance and propulsion improvements developed for the CZ-series of launch vehicles.
Indian short-range, sea-based, liquid-propellant ballistic missile thought to be a variant of the Prithvi.
French orbital launch vehicle. In December 1961 France decided to demonstrate an indigenous satellite-launch capability, using stages in development for its ballistic missile program. Following careful evolutionary development, Diamant was successful on its first attempt in 1965. Improved versions were flown over the next ten years.
French orbital launch vehicle. Diamant development could be done relatively quickly using stages and systems being developed for strategic missiles. In May 1962 CNES selected DMA as program manager, with SEREB as the prime contractor. The Diamant orbital launch vehicle was created by replacing the payload of the existing Saphir test vehicle with a new third stage. Prior to any all-up satellite launch attempt the P064 third stage was flight tested on the smaller suborbital Rubis test vehicle. This evolutionary approach paid off.
French orbital launch vehicle. As a follow-on to the Diamant-A, CNES decided to evolve a more capable launch vehicle. The Diamant-B used a new first stage with 50% more propellants and 33% more thrust; the same second stage; and a fatter third stage. Six Diamant-B boosters were ordered. Originally four of these were to be used to test the Europa 2 launch vehicle's Perigee-Apogee System. These tests were cancelled and instead CNES used five of the six boosters for orbital attempts.
French orbital launch vehicle. In January 1972 a further evolution, the Diamant BP.4, was authorized. The second stage was replaced with the P4 Rita motor developed for the MSBS SLBM. The larger 1.38 m diameter fairing developed for the British Black Arrow launcher allowed larger payloads to be accommodated. Three launches of the BP.4 in 1975 completed the Diamant saga.
Divine Arrow.
Alternate Designation of CZ-2F orbital launch vehicle.
Ukrainian orbital launch vehicle based on decommissioned R-36M2 intercontinental ballistic missiles.
Russian intercontinental ballistic missile. Alternate silo-launched version, silo hardened to 15-30 atmospheres overpressure.
American sea-launched test vehicle. The Dolphin hybrid rocket (solid fuel and liquid oxygen oxidizer) was built by Starstruck (formerly ARC Technology), a predecessor to AMROC. The Dolphin included not only innovative propulsion technology but was also launched from a floating launch cannister at sea. One test article of the hybrid was successfully launched in the summer of 1984. But the project was backed entirely with private funds and when backing for further development was not forthcoming, the project folded.
Dong Feng 5.
Alternate designation for DF-5 intercontinental ballistic missile.
Dong Feng-15.
Popular Name of DF-15 missile.
Dong Feng-21.
Popular Name of DF-21 intermediate range ballistic missile.
Dong-Feng 1.
Popular Name of DF-1 intermediate range ballistic missile.
Dong-Feng 2.
Popular Name of DF-2 intermediate range ballistic missile.
Dong-Feng 2A.
Popular Name of DF-2A intermediate range ballistic missile.
Dong-Feng 3.
Popular Name of DF-3 intermediate range ballistic missile.
Dong-Feng 31.
Popular Name of DF-31 intercontinental ballistic missile.
Dong-Feng 3A.
Popular Name of DF-3A intermediate range ballistic missile.
Dong-Feng 4.
Popular Name of DF-4 intermediate range ballistic missile.
Dong-Feng 57.
Popular Name of DF-57 intercontinental ballistic missile.
Dong-Feng 5A.
Popular Name of DF-5A intercontinental ballistic missile.
American test vehicle. Test vehicle developed by Sandia for aeronomy measurements during atmospheric nuclear tests. One (Doorknob-1) or two surplus Lacrosse (Doorknob-2) missile motors were mated with the payload section.
American test vehicle. Single stage vehicle.
American test vehicle. Two stage vehicle consisting of 1 x Lacrosse + 1 x Lacrosse
DOT.
American sounding rocket. Three stage vehicle consisting of 2 x Recruit + 1 x Castor + 1 x Star 26C
American test vehicle. Two stage vehicle consisting of 2 x Cajun + 1 x T-40
American test vehicle. Single stage vehicles consisting of 2 Deacon motors fired in parallel.
Two stage vehicle consisting of 2 x HPAG + 1 x Deacon
American test vehicle. Two stage vehicle consisting of 1 x Mk7 + 1 x Mk7
American winged orbital launch vehicle. The Douglas "Astro" was a VTHL TSTO system designed for launching space station crews and cargo by the 1968-70 period. A key requirement was that off-the-shelf technologies must be used, e.g. existing M-1, J-2 and RL-10 engines from the Saturn and Nova expendable launch vehicle programs.
Douglas Clipper.
Alternate designation for DC-Y ssto vtovl orbital launch vehicle.
American orbital launch vehicle. The Douglas HATV design of 1946 was laid out by the Douglas engineer William Ballhaus. He proved that there were no obstacles to a single-stage-to-orbit space launch vehicle, as long as pressurized 'metal balloon' tanks were used instead of using aircraft-structure design approaches.
DP.
Alternate designation for Tu-130 intercontinental boost-glide missile.
DP.
Alternate designation for Tu-123 intercontinental boost-glide missile.
American test vehicle. Two stage vehicle consisting of 1 x TX-20 Sergeant + 1 x TX-30
Dragon.
Alternate designation for Dragon 1 sounding rocket.
French sounding rocket. Two stage sounding rocket. The Belier upper stage was augmented by a Stromboli booster with 686 kg of solid propellant. The rocket was spin stabilised by small solid rocket engines on the four fins.
French sounding rocket. Two stage vehicle consisting of 1 x Stromboli + 1 x Belier II
French sounding rocket. Two stage vehicle consisting of 1 x Stromboli + 1 x Belier III
American sounding rocket.
DRM1.
American heavy-lift orbital launch vehicle. The Mars Design Reference Mission version 1.0 studied a number of heavy-lift boosters capable of lofting more than 200 tonnes into low earth orbit. The Red Team recommended configuration was an NLS / shuttle-derived vehicle with F-1A powered liquid rocket boosters.
German winged orbital launch vehicle. Under the Future European Space Transportation Investigation Programme (FESTIP) of 1994-1999 French agencies and contractors designed a number of alternative reusable space launchers. This one was a Horizontal Takeoff / Horizontal Landing Two Stage to Orbit proposal with Mach 3 stage separation. Later evolved into the FESTIP FSS-11,which was merged with FSS-12. Reusable and expendable upper stage options.
DSV-2A.
Manufacturer's designation for Thor Agena D orbital launch vehicle.
DSV-2C.
Manufacturer's designation for Thor SLV-2A Agena D orbital launch vehicle.
DSV-2L.
Manufacturer's designation for Thorad SLV-2H Agena D orbital launch vehicle.
Dubna.
Launch System of V-880M surface-to-air missile.
Dun-1.
Alternate Designation of DF-2 intermediate range ballistic missile.
Dun-2.
Alternate Designation of DF-3 intermediate range ballistic missile.
Dvina.
Launch System of R-12U intermediate range ballistic missile.
Dvina.
First French liquid fuel rocket. Developed in the 1931-1942, tested in 1945.
EA 1946.
Alternate Designation of Eole test vehicle.
Eagle SLV.
Alternate designation for Scorpius low cost orbital launch vehicle.
Eagle S-Series.
Alternate designation for Eaglet all-solid orbital launch vehicle.
American all-solid orbital launch vehicle. E'Prime Aerospace of Titusville, Florida, conceived of a family of launch vehicles, called the Eagle S-series, using rocket stages from the LGM-118A Peacekeeper ICBM. The smallest vehicle, the Eaglet, could launch 580 kilograms into LEO. A somewhat larger version, the Eagle, could put 1,360 kilograms into LEO. Both vehicles would use Peacekeeper solid propellant lower stages and liquid propellant upper stages.
EARL.
German winged orbital launch vehicle. Vertical takoff / horizontal landing two-stage launch vehicle study from the 1980s.
German winged orbital launch vehicle. A larger Earl 14 configuration was studied, but the study centered on the Earl 5 / 18 / 7 configurations. The second stage was mounted on top of the booster. Earl 5 and 7 had winged second stages, with payloads to low earth orbit of 5380 kg to 7180 kg. Earl 14 featured an expendable upper stage which increased payload to 18,000 kg.
German winged orbital launch vehicle. Later EARL version from 1990. Parallel staging, both stages winged and recoverable. Expendable upper stage for heavy-lift missions.
German orbital launch vehicle. The EBH (Engel - Bödewaldt - Hanischlaunch) vehicle was a 1949 manned design which would had a gross launch mass of 220 tonnes and delivered a payload of 3 tonnes to a 557-kilometre orbit
EC47.
Standard warhead of Polaris A1 missile.
American winged orbital launch vehicle. In February 1976 this version of the shuttle was proposed. A single liquid rocket booster under the external tank would replace the two solid rocket boosters.
American low cost orbital launch vehicle. Aries launched to promote a commercial launch vehicle of entirely different configuration.
EKR.
Russian intermediate range cruise missile. B Chertok of NII-8 took the preliminary German R-13 cruise missile design and elaborated it, including consideration of the key problem of long-range automatic astronavigation. By 1951 to 1953 Korolev's design bureau had prepared an experimental design, the EKR. I Lisovich had developed a prototype astronavigation system that met the necessary specifications, and solution of basic problems in use of steel and titanium hot airframe technology had been solved at VIAM (All-Union Institute of Aviation Materials) and MVTU Bauman Institute. An expert commission in 1953 examined the EKR design and felt that there were still many technical problems to be solved, most of which were better handled by an aircraft designer rather than Korolev.
Elbrus.
Launch System of R-17 short-range ballistic missile.
ELDO A.
Alternate designation for Europa orbital launch vehicle.
European orbital launch vehicle. Three stage version of the Europa vehicle.
French orbital launch vehicle. Emeraude was a step toward larger liquid propellant launch vehicles, building on the Veronique and Vesta experience. It burned 12.8 tonnes nitric acid/turpentine pressure-fed propellants in 91 seconds. Tthe engine was gimbaled for pitch and yaw control, with aerodynamic fins controlling roll. In anticipation of the next step, Saphir, a dummy Topaze stage topped the vehicle to confirm aerodynamic characteristics. The first three launches were failures due to propellant sloshing. This was remedied in the later tests.
Emma.
French test vehicle. Two stage vehicle consisting of 1 x Emma Booster + 1 x Emma
The Energia-Buran Reusable Space System (MKS) began development in 1976 as a Soviet booster that would exceed the capabilities of the US shuttle system. Following extended development, Energia made two successful flights in 1987-1988. But the Soviet Union was crumbling, and the ambitious plans to build an orbiting defense shield, to renew the ozone layer, dispose of nuclear waste, illuminate polar cities, colonize the moon and Mars, were not to be. Funding dried up and the Energia-Buran program completely disappeared from the government's budget after 1993.
Launch vehicle originally designed in the 1980's to fullfill the third generation 20-30 tonnes to orbit launcher requirement. It was an adaptation of the Energia launch vehicle, using two strap-on booster units instead of four, and a reduced-diameter core using a single RD-0120 engine instead of four. In the 1990's a structural test article was built and it was proposed that several Energia-M's be launched for commercial customers using surplus Energia components. No buyers came forward for the untested design.
Design version of Energia, with the reusable Buran manned spaceplane mounted to the side of the core.
Energiya/Buran.
Alternate designation for Energia-Buran winged orbital launch vehicle.
German surface-to-air missile, tested during World War II but abandoned in 1945 in favour of Wasserfall.
Eole.
French test vehicle. Second missile developed by Jean-Jacques Barre and end of that lineage.
French sounding rocket. Two stage vehicle consisting of 1 x Belisama + 1 x Belisama
EPOS.
Alternate designation for Spiral 50-50 winged orbital launch vehicle.
French sounding rocket. Two stage sounding rocket consisting of two Stromboli motors in tandem.
American anti-ballistic missile. Extended-Range Interceptor, Patriot improvements, SDIO/BMDO project
ERIS.
American anti-ballistic missile. Flight test vehicle for Exoatmospheric Re-Entry Interceptor Subsystem, an anti-ballistic missile hit-to-kill interceptor warhead. The ERIS vehicle itself consisted of surplus Minuteman ICBM second and third stages.
ETV.
Japanese test vehicle. Three stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x LE-3
European orbital launch vehicle. Europe's first space launcher. The first stage was a British Blue Streak IRBM, the second stage the French Coralie, and the third stage the German Astris. All orbital launch attempts failed due to unreliability of the third stage. The project was cancelled after withdrawal of British support and replaced by the Ariane.
European orbital launch vehicle. Four stage version of the Europa vehicle, adding a P068 fourth stage.
European eXperimental Test Vehicle.
Alternate designation for EXTV winged orbital launch vehicle.
American sea-launched orbital launch vehicle. Excalibur was a subscale version of Sea Dragon proposed by Truax Engineering in the 1990's. It featured the same attributes as Sea Dragon: low cost design (pressure fed engines), Lox/Kerosene first stage (combustion chamber pressure 24 atmospheres) and Lox/LH2 second stage (chamber pressure 5 atmospheres). Guidance would be by a combined Inertial/GPS system. An even smaller Excalibur S vehicle would prove the concept and place 500 kg in orbit.
American sea-launched orbital launch vehicle. Two recoverable pressure-fed stages.
The Canadian-made Excalibur Target System was a boosted dart ballistic rocket whose flight could be tailored to simulate various threats for anti-tactical ballistic missile (TBM) system tests. The solid-propellant launched the dart segment to the necessary angle and velocity for the mission. The dart then separated from the booster. It carried a sophisticated electronic RFSAS Radio Frequency Signature Augmentation System, which electronically enlarged the target's radar cross-section to mimic the larger missile appropriate to the mission.
Exos.
American sounding rocket. Three stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x Recruit
American heavy-lift orbital launch vehicle. Numerous NASA studies in the late 1980's and 1990's came to the same conclusion as the Nova studies of the 1960's - to get to Mars, an extremely heavy lift launch vehicle was needed to assemble Mars expeditions in low earth orbit. A nominal heavy list vehicle with a payload of at least 140 tonnes into a Space Station Freedom orbit would have to be developed for such missions.
EXTV.
French winged orbital launch vehicle. This was to be a reusable winged rocket-powered atmospheric reentry demonstrator capable of reaching speeds of Mach 4 to 10 in the atmosphere. The aim was for ESA to build up experience in reuse operations and high-speed atmospheric flight in the 2003-2007 period. The demonstrator would weigh two tonnes and have a range of 1500 kilometers. It would be able to land on a conventional runway. Dassault and Aerospatiale Matra were to merge their VEHRA and ARES projects to produce a single design. Ares estimated cost was 550 million dollars.
F-1.
Library of Congress Designation of Tsiklon-2 and Tsiklon-2A orbital launch vehicles.
F-1r.
Library of Congress Designation of R-36-O orbital missile.
F-2.
Library of Congress Designation of Tsiklon-3 orbital launch vehicle.
F-3.
Library of Congress Designation of Tsiklon-4 orbital launch vehicle.
American intermediate range cruise missile.
Fahd.
Iraqi short range ballistic missile.
American low cost orbital launch vehicle. Falcon I was a two stage, reusable, liquid oxygen and kerosene powered launch vehicle. A single engine powered the first stage. It was designed for cost-efficient and reliable transport of satellites to low Earth orbit. First launch of the Falcon I was scheduled for mid-2004 from Vandenberg, carrying a US Defense Department communications satellite. Development delays and problems with USAF clearances for launch from Vandenberg resulted in the first launch attempt being made in 2006 from a private facility at Omelek near Kwajalein atoll in the Pacific. Success was achieved on the fourth launch in 2008. The Falcon 1 was to be superseded by the Falcon 1e, with an extended-tank first stage, from 2010.
Version of Falcon 1 with stretched first stage and much more powerful Merlin engine.
American low cost orbital launch vehicle. Falcon V was a two stage, reusable, liquid oxygen and kerosene powered launch vehicle. The maiden flight was targeted for mid-2005 as of early 2004. It used of the same engines, structural materials and concepts, and avionics and launch system as the Falcon I, differing in having five first-stage engines instead of 1 and a larger diameter. This meant that all the critical components would have a flight proven history even before first launch. By 2006 it had been superseded by the slightly larger Falcon 9.
American low cost orbital launch vehicle. In September 2006 SpaceX was named as one of two winners of the NASA Commercial Orbital Transportation Services competition. The SpaceX award was $278 million for three flight demonstrations of the Falcon 9 booster carrying the Dragon space capsule. On 23 December 2008 NASA announced that the Falcon 9 / Dragon had been selected for launch of a guaranteed minimum of 20,000 kg of payload to the International Space Station in 2010-2014. The firm contract was worth $1.6 billion, with another $1.5 billion of options.
American low cost orbital launch vehicle. The Falcon 9 Heavy would consist of a standard Falcon 9 with two additional Falcon 9 first stages as liquid strap-on boosters.
FalconLaunch
British sounding rocket. Single stage hypersonic test vehicle using the Stonechat II solid rocket motor.
American sounding rocket. Project Farside was an attempt to reach extreme altitudes with the rockoon concept. Using a four-stage solid-propellant rocket hung below a 106 188-m3 (3 750 000-ft3) balloon, altitudes approaching 6437 km (4000 mi) were reached during the fall of 1957. Farside was a four stage vehicle consisting of 4 x Recruit + 1 x Recruit + 4 x Arrow II + 1 x Arrow II.
Favorit.
Popular Name of S-300PMU-2 surface-to-air missile.
FB-1.
Chinese orbital launch vehicle. The FB-1, like the CZ-2 launch vehicle begun the following year, was a two-stage booster developed from the DF-5 intercontinental ballistic missile. Payload for the booster was the JSSW, believed to have been a television-transmission military reconnaissance satellite. The incredible decision to develop two nearly identical rockets concurrently can be blamed on the turbulent factional politics after the Cultural Revolution.
Feng Bao 1.
Alternate designation for FB-1 orbital launch vehicle.
Feng-Bao-1.
Manufacturer's designation for FB-1 orbital launch vehicle.
FFAR.
American air-to-air rocket. Folding-Fin Air Rocket, boosted by 1 x Mk7. Unguided fighter weapon, later used as sounding rocket.
Russian tactical ballistic rocket.
Flamenco.
Popular Name of INTA-300 sounding rocket.
FLTP.
European winged orbital launch vehicle. Europe's Future Launcher Technology Program (FLTP) was an ESA study program that ran from 1999-2002, with the objective of identifying and developing technologies necessary for the successor to the Ariane 5. The planned configuration was a two-stage fully recoverable winged launch vehicle. The winged booster would deliver the orbiter to a given altitude, then booster fly back to its launch base at Kourou. The second stage orbiter continued to orbit, delivered its payload and then returned to Kourou. The program faded out following collapse of the commercial launch market, development problems with the Ariane 5, and cancellation of NASA reusable launch vehicle projects.
FOBS; Fractional Orbital Bombing System.
Alternate designation for R-36-O orbital missile.
German sounding rocket. Single stage vehicle.
Fort.
Popular Name of S-300F surface-to-air missile.
Fort-M.
Popular Name of S-300FM surface-to-air missile.
Frog 1.
Department of Defence Designation of Filin tactical ballistic rocket.
Frog 2.
Department of Defence Designation of Mars tactical ballistic rocket.
Frog 3.
Department of Defence Designation of 3R10 tactical ballistic rocket.
Frog 4.
Department of Defence designation of 3R9 missile.
Russian tactical ballistic rocket. Evidently redundant DOD designation.
Russian tactical ballistic rocket. Designation issued by US DOD, but cannot be linked to any known missile post-cold war.
Frog 7.
Department of Defence Designation of R-65 tactical ballistic rocket.
Frog 7A.
Department of Defence Designation of R-70 tactical ballistic rocket.
Frog 7B.
Department of Defence Designation of R-75 tactical ballistic rocket.
Russian tactical ballistic rocket. US designation; does not appear to have existed.
Russian tactical ballistic rocket. US designation; does not appear to have existed.
British sounding rocket. Two stage vehicle consisting of 1 x Heron (107 kN) + 1 x Snipe (16.7 kN).
Future Launcher Technology Program.
Alternate designation for FLTP winged orbital launch vehicle.
G-1.
Library of Congress Designation of N1 heavy-lift orbital launch vehicle.
G-1.
Russian intermediate range ballistic missile. The G-1, an improved 600 km range version of the V-2 missile, was the first design produced by Groettrup's German engineering team after they had been moved to Russia. A Soviet state commission found in 1948 that it was superior to Korolev's R-2 concept. Nevertheless the R-2 was put in production instead.
G-2.
The G-2 design objective was to create the first IRBM - to deliver a 1000 kg payload over a 2500 km range. The missile would use three V-2 derived engines with a total thrust of 100 tonnes. A variety of alternate configurations (R-12A through R-12K) were considered by the German team in Russia. These included parallel and consecutive staging, gimballed motors, and other innovations. The R-12K was particularly interesting because it represented a concept later used on the US Atlas missile - jettisoning of the two outboard engines at altitude to significantly improve range. The G-2 was given the secret designation R-6 and overt designation R-12 by the Russians.
G-3.
German aerodynamicist Albring designed the G-3 missile for the Russians in October 1949. This would use a rocket-powered Groettrup-designed G-1 as the first stage. The cruise stage would have an aerodynamic layout like that of the Saenger-Bredt rocket-powered antipodal bomber of World War II. Cruising at 13 km altitude, the supersonic missile would carry a 3000 kg warhead to a range of 2900 km.
G-4.
Russian intermediate range ballistic missile. The G-4 was designed by the Groettrup German team in the Soviet Union in competition with Korolev's R-3. Rocket chief Ustinov informed Groettrup of the requirement on 9 April 1949: to deliver a 3000 kg atomic bomb to a 3000 km. This requirement meant a massive improvement over existing V-2 technology. The G-4 was evaluated against Korolev's R-3 on 7 December 1949 - and the G-4 was found to be superior. Neither ended up in production, but the design concepts of the G-4 led directly to Korolev's R-7 ICBM (essentially a cluster of G-4's or R-3A's) and the N1 superbooster. Work on the G-4 continued through 1952.
G-5.
Russian intercontinental ballistic missile. Some sources indicate the G-5 / R-15 designation was assigned to an ICBM designed by the Groettrup team. If so, it may have been the 'packet of G-4's' that was the direct ancestor of the Korolev R-7. The designation G-5 / R-15 has also been reported as that of the ramjet missile more often referred to as G-3 or R-13.
Gainful.
ASCC Reporting Name of Kub surface-to-air missile.
Galosh Mod.1.
ASCC Reporting Name of A-350Zh anti-ballistic missile.
Galosh Mod.2.
ASCC Reporting Name of A-350R missile.
GAM-63.
Department of Defence Designation of Rascal air-to-surface missile.
GAM-67.
Department of Defence Designation of Crossbow air-to-surface missile.
GAM-77.
Alternate Designation of AGM-28A intermediate range cruise missile.
GAM-77A.
Alternate Designation of AGM-28B intermediate range cruise missile.
GAM-87.
Alternate Designation of Skybolt air-to-surface missile.
Argentinan sounding rocket. Argentine two-stage solid-propellant fin-stabilized rocket flown in the early 1960's for technology development and scientific research.
Gammon.
ASCC Reporting Name of S-200, V-860P, V-860PV, V-870, V-880, V-880E, V-880M, and V-880N surface-to-air missile.
Ganef.
ASCC Reporting Name of Krug surface-to-air missile.
Gazelle.
ASCC Reporting Name of 53T6 anti-ballistic missile.
Geostationary Satellite Launch Vehicle.
Full name of GSLV orbital launch vehicle.
Gerkules.
Alternate designation of UR-500 missile.
Pakistani intermediate range ballistic missile. Derivative of North Korean Nodong. First fired April, 1998. Payload is about 700 kg. Managed by A Q Khan Research Laboratories.
Pakistani single-stage solid-propellant tactical ballistic missile, a license-built version of the Chinese DF-11. Flown in October 2003, believed to have entered service in 2004.
Giant.
Russian sounding rocket. The first rocket successfully launched by the Soviet GIRD organisation was a hybrid, using a liquid oxygen to burn gelled petroleum in large casing. Development of the rocket was begun by GIRD's second brigade under M K Tikhonravov.
Russian sounding rocket. The first liquid propellant rocket launched in the Soviet Union, the GIRD-10 used liquid oxygen and alcohol propellants, pressure-fed to the combustion chamber by nitrogen gas.
Gladiator.
Canadian gun-launched orbital launch vehicle. When compared to the early Martlet 4 designs the GLO-1B was a considerably more sophisticated vehicle with many of the shortcomings of it's predecessor having been addressed. Not long after the original HARP project ended the major assets of the project were acquired by the projects management, Dr. Gerald Bull in particular. The HARP Program became the Space Research Corporation (SRC) with the intention of resurrecting the HARP orbital program. Over the years a much improved and considerably more sophisticated Martlet 4 was developed and given the name of GLO-1B.
GMD boost vehicle.
Library of Congress Designation of OBV anti-ballistic missile.
American anti-ballistic missile. Three-stage booster for use with the Missile Defense Agency's Ground-based Midcourse Defense System. Built by Lockheed Martin Corp., the booster was one of two slated for use with the GMD system. The system was designed to intercept and destroy long-range ballistic missiles.
Gnom.
Russian intercontinental ballistic missile. Gnom was a unique design which represented the most advanced work ever undertaken on an air-augmented missile capable of intercontinental ranges or orbital flight. Although cancelled in 1965 before flight tests could begin, Gnom was the closest the world aerospace engineering community ever came to fielding an orbital-capable launcher of less than half of the mass of conventional designs.
Robert H. Goddard was the father of American rocketry. In a series of rockets flown between World War I and World War II, he solved all of the fundamental problems of guided liquid propellant rockets.
American test vehicle. Rocket used by Goddard to achieve the first flight of a liquid-propellant rocket.
American test vehicle. After several tests indicating the model was too small to permit refinements, Goddard decided to build a rocket twenty-fold larger. During 1926 a new tower was built, and flow regulators, multiple liquid injection into large combustion chambers, means for measurement of pressure and lifting force, electrically fired igniter, and turntable for rotation were developed.
American test vehicle. First instrumented liquid fuel rocket. Length 11 ft 6 in.; maximum diameter 26 in.; weight 32 lb; gasoline 14 lb; liquid oxygen 11 lb; total loaded weight 57 lb.
American test vehicle. Goddard rocket using pressure-fed Lox/Gasoline propellants, streamline casing, and remote control guidance. Masses varied; typical values indicated.
American test vehicle. The A series rockets used simple pressure feed, gyroscopic control by means of vanes, and parachute. The rockets in this series averaged in length from 4.11 m to 4.65 m.; their weight empty varied from 26 kg to 39 kg.
American test vehicle. This consisted of ten proving-stand tests for the development of a more powerful motor, 10 in. in diameter. Weight of rocket, about 225 lb; weight of fuels, 50-70 lb for the series.
American test vehicle. Tests of the Goddard L Section A covered development of a nitrogen-pressured flight rocket using 10 in, motors based on the K series and ran from May 11 to November 7, 1936 (L1-L7). Length of the L Series Section A rockets varied from 10 ft 11 in, to 13 ft 6 1/2 in.; diameter 18 in.; empty weight 120 to 202 lb; loaded weight 295 to 360 lb; weight oxygen about 78 lb; weight gasoline 84 lb; weight nitrogen, 4 lb.
American test vehicle. The L-B series were check tests of 5.75-in.-diameter chambers with fuels of various volatilities; development of tilting cap parachute release; tests of various forms of exposed movable air vanes; test of retractable air vanes and parachute with heavy shroud lines. The series ran from November 24, 1930-May 19, 1937 (L8-L15). Final results of Section B of L Series showed two proving-stand tests, and six flight test attempts, all of which resulted in flights. Average interval between tests 22 days.
American test vehicle. Series L Section C rockets included light tank construction, movable-tailpiece (i.e. gimbal) steering, catapult launching, and further development of liquid nitrogen tank pressure method. Lengths varied from 17 ft 4.25 in. to 18 ft 5.75 in.; diameter 9 in., weight empty varied from 80 to 109 lb; loaded weight about 170 lb or more; lift of static tests varied from 228 lb to 477 lb; jet velocities from 3960 to 5340 ft/sec.
American test vehicle. Section C tests would run through October 10, 1941 and represent the final Goddard rocket flight tests. The series of twenty-four static and flight tests (P13-P36) was made with rockets of large fuel capacity, with the rocket motor, pumps, and turbines previously developed. These rockets averaged nearly 22 ft in length, and were 18 in, in diameter. They weighed empty from 190 to 240 lb. The liquid-oxygen load averaged about 140 lb, the gasoline 112 lb, making "quarter-ton" loaded rockets.
First American civilian sounding rocket to reach outer space.
American SSTO VTOVL orbital launch vehicle. Edward Gomersall of NASA's Ames Research Center produced a conservative design for an SSTO in 1970. His vehicle was based on realistic structural technology and used a derivative of the J-2S engine.
Gorgon.
ASCC Reporting Name of 51T6 anti-ballistic missile.
GR-1.
Russian intercontinental ballistic missile. Korolev's entry in the 'Global Rocket' competition, a missile that could place a nuclear warhead in orbit, where it could come in under or behind American anti-ballistic missile defences, and be deorbited with little warning. Cancelled in 1964 in preference to Yangel's R-36-O.
French test vehicle. Two stage vehicle consisting of 1 x Emilie + 1 x Melusine
Green Bee.
Alternate Designation of Ching Feng short range ballistic missile.
Griffon.
ASCC Reporting Name of Dal surface-to-air missile.
Grom.
Complex of P-750 intermediate range cruise missile.
Grom.
Russian orbital launch vehicle. Three stage vehicle consisting of 1 x R-39 St 1 + 1 x R-39 St 2 + 1 x R-39 St 3
Variant of the Energia launch vehicle with two strap-on boosters instead of four. This would have fullfilled the 50 tonne payload requirement had the third generation booster plan been fully implemented.
Grumble.
ASCC Reporting Name of S-300F, S-300FM, S-300P, and S-300PMU-1 5V55U surface-to-air missiles.
American winged orbital launch vehicle. Winged, horizontal-takeoff/horizontal concept space booster concept using an Air Collection and Enrichment System to generate liquid oxygen oxidiser from the atmosphere after takeoff. An upper rocket stage would deliver a crewed orbiter or payload to orbit.
GSLV.
Indian mixed-propulsion orbital launch vehicle for geosynchronous satellites using a Lox/LH2 upper stage developed from Russian technology.
GTD-21B.
Popular Name of D-21 air-launched drone.
Guideline.
ASCC Reporting Name of V-753 surface-to-air missile.
Guideline Mod 0,1.
ASCC Reporting Name of S-75 surface-to-air missile.
Guideline Mod 2, 3,4,5.
ASCC Reporting Name of S-75M surface-to-air missile.
Guild.
ASCC Reporting Name of S-25 missile.
Gun Projectile 5-inch
Gun Projectile 7-inch
H-1.
Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages.
American orbital launch vehicle. Three stage version consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x LE-5
American orbital launch vehicle. Four stage version consisting of 6 x Castor 2 + 1 x ELT Thor N + 1 x LE-5 + 1 x UM129A
H-2.
Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A.
Japanese orbital launch vehicle. Concept of H-2 augmented with Liquid-Air Cycle Engine boosters and advanced HIMES upper stage.
The H-2 horizontal takeoff / horizontal landing two-stage reusable space shuttle was proposed by Institute 601 of the Air Ministry in 1988. The first stage would used air breathing engines to accelerate the rocket-powered second stage to release velocity. This ambitious design would leapfrog China ahead of other spacefaring nations, but would be available no earlier than 2015. It was decided the concept was beyond Chinese technical capability, and it was not pursued further.
H-2A.
Japanese orbital launch vehicle. Low-cost version of H-2 developed for the commercial market. The two SRB-A solid rocket boosters can be supplemented by 4 smaller SSB solid boosters. 0 or 2 SSB's can be fitted for reduced 9,940 kg or 10,740 kg LEO payloads.
Japanese orbital launch vehicle. This version uses two core stages side-by-side in an asymmetric configuration, supplemented by two SRB-A solid rocket boosters.
HAD.
Australian test vehicle. The HAD vehicle was, like HAT, a two stage rocket, based on British Gosling and LAPStar motors. First launched in 1961, it had two test flights before becoming operational.
French short range ballistic missile. Single stage vehicle
HAEC.
HAEC
HAT.
Australian test vehicle. Two stage vehicle consisting of 1 x HAT + 1 x LAPSTAR
Pakistani single-stage solid propellant tactical ballistic missile Developed by the Space and Upper Atmosphere Research Commission (SUPARCO) based on French Stromboli engine technology. The unguided IA version went into service in 1992; the improved, inertiallty guided IB version in 2001.
Hatf 2.
Alternate designation for Abdali missile.
Hatf 3.
Alternate designation for Ghaznavi tactical ballistic missile.
Hatf 4.
Alternate designation for Shaheen 1 intermediate range ballistic missile.
Hatf 5.
Hatf 6.
Alternate designation for Shaheen 3 intermediate range ballistic missile.
HATV.
American orbital launch vehicle. Significant Navy program begun in 1946 to develop a single-stage-to-orbit satellite launch vehicle. The Air Force blocked Navy efforts to develop it on a joint basis, while at the same time having no interest in the project itself. Work was abandoned at the end of 1948.
Hawk.
Popular Name of MIM-23A surface-to-air missile.
Hawk.
American surface-to-air missile. The Hawk was the first mobile medium-range guided anti-aircraft missile deployed by the U.S. Army, and was the oldest SAM system still in use by U.S. armed forces in the late 1990s.
American sounding rocket. Balloon-launched Loki with larger fins for stability at high altitudes. The larger Loki II motor was used from 5 August 1957 as part of the IGY. This variant could reach 122 km and was called the 'Hawk Rockoon'.
HDP.
Manufacturer's designation for V-3 gun-launched missile.
The Heinkel He-112 was an unsuccessful pre-war German monoplane fighter, competing for orders with the Bf 109. However it entered rocketry history when tests were conducted with rocket engines.
American heavy-lift orbital launch vehicle. ATK Thiokol concept corresponding to earlier Shuttle-C proposals. The shuttle orbiter is replaced by a 6.5 m diameter x 25 m long cargo container, powered by two Space Shuttle main engines. Availability would be three to four years after go-ahead.
American heavy-lift orbital launch vehicle. ATK Thiokol concept for a shuttle-derived heavy lift vehicle. The shuttle orbiter would be replaced by a 6.5 m diameter x 35 m long cargo container, powered by three Space Shuttle main engines. The shuttle RSRM motors would have a fifth segment added, and the External Tank would be stretched to 56 m long. Availability would be six years after go-ahead.
American heavy-lift orbital launch vehicle. ATK Thiokol concept for a shuttle-derived heavy lift vehicle with a lift equivalent to the Saturn V. The radical reconfiguration would put all elements in-line. Four SSME engines would be at the base of a stretched external tank, flanked by two shuttle RSRM motors with a fifth segment added. Atop this would be an 8.7 m diameter Lox/LH2 stage, followed by a 10-m diameter payload fairing. Availability would be ten years after go-ahead.
Heavy Lift Launch Vehicle.
Alternate designation for Exploration HLLV heavy-lift orbital launch vehicle.
HEDI.
American anti-ballistic missile. Two stage vehicle consisting of 1 x X-265 + 1 x X-271
American nuclear-powered orbital launch vehicle. Study by Kraft Ehricke of a vehicle where the booster stage contains liquid oxygen tanks only and takes the nuclear second stage to the stratosphere. The nuclear sustainer then takes the payload to orbit or escape trajectory.
American nuclear-powered orbital launch vehicle.
American nuclear-powered orbital launch vehicle.
American nuclear-powered orbital launch vehicle.
Hera.
American target missile. Two stage vehicle used as a target for test of anti-ballistic missile systems. The vehicle consisted of surplus Minuteman 2 second and third stages (SR19AJ1 + M57A1).
Russian air-launched winged orbital launch vehicle. Launch vehicle design by NPO Molniya / TsAGI that would utilize air launch from a giant cargo aircraft capable of lifting 900 tonne payloads. The single stage to orbit spaceplane would be released at subsonic velocity.
American tactical ballistic missile. Hermes was a major US Army project to implement German rocket technology after World War II. Development started in 1944 with award to General Electric as the prime contractor. The program was cancelled in 1954 after $ 96.4 million had been spent. Most of this was for nought since the Air Force received the long-range missile assignment in the end.
The designs ran the gamut from short range solid propellant rockets through Mach 3 ramjets to intercontinental boost-glide vehicles. General Electric was also responsible for firing captured German V-2 rockets, training Army personnel in their use, and the Bumper project which created a two-stage vehicle using a V-2 and a WAC-Corporal. See individual entries for the Hermes A-1, Hermes A-3, Hermes B-1, and Hermes C.
The Army Hermes A-1 single stage test rocket was an American version of the German Wasserfall anti-aircraft rocket.
American tactical ballistic missile. The Army Hermes A-2 single stage test rocket proved the technology of large solid rocket motors as developed by H L Thackwell at Thiokol. But the Army preferred to have further development done in-house and JPL was selected to develop the Sergeant rocket. In addition to the flight tests, a total of 22 motors were static fired, including one after seven years of storage.
American tactical ballistic missile. Prototype of a single-stage liquid propellant tactical Army missile. Two versions test flown but abandoned in favour of the Redstone in-house design.
American tactical ballistic missile.
American tactical ballistic missile.
American tactical ballistic missile. Test vehicle for Hermes II Mach 3 ramjet cruise missile. The modified V-2 merely acted as a booster for the 'Ram' second stage.
Hermes C.
Alternate designation for Redstone short range ballistic missile.
American tactical ballistic missile. The Hermes C1 was a clustered-engine intercontinental ballistic missile proposed by General Electric in June 1946. It was eventually down-scoped to a single-engine tactical missile, which flew as the Redstone in 1953.
Hermes II.
Manufacturer's designation for Hermes B-1 tactical ballistic missile.
American intercontinental ballistic missile. ICBM version. Also CGM-16F
American anti-ballistic missile. Hibex was a 5.2 m long test vehicle used by the Army in a series of research experiments investigating high performance missile boosters. During mid-1960's experimental flights at White Sands, Hibex was fired successfully from underground cells and above-ground launch sites.
American air-launched test vehicle. Two stage vehicle consisting of 1 x B-58 Hustler + 1 x TX-20 Sergeant
H-II.
Alternate designation for H-2 orbital launch vehicle.
H-II.
Japanese orbital launch vehicle. 3 stage vehicle consisted of 2 x H-II SRB boosters + core vehicle.
Japanese orbital launch vehicle. Three stage version consisting of 2 x H-II SSB boosters + 2 x H-II SRB boosters + core vehicle.
Japanese orbital launch vehicle. Three stage version of H-IIA consisting of 2 x H-II SRB-A + two-stage core vehicle.
Japanese orbital launch vehicle.
H-IIA 2024.
Alternate designation for H-2A orbital launch vehicle.
Japanese orbital launch vehicle. Three stage vehicle consisting of 4 x Castor 4XL + 2 x H-II SRB-A boosters + two-stage core vehicle.
Japanese orbital launch vehicle.
H-IIA 212.
Alternate designation for H-2A 212 orbital launch vehicle.
Japanese orbital launch vehicle, utilizing H-IIA engines, but with larger-diameter all-new stages. Designed to place Japanese ISS HTV logistics vehicle into orbit.
American sounding rocket.
American test vehicle, built and flown by Convair in 1945-1947 to test technologies applied to the later Atlas ICBM.
HJ.
American sounding rocket. Single stage sounding rocket.
American sounding rocket. Two stage vehicle consisting of 1 x M-6 + 1 x Hydac
American sounding rocket. NASA/Canadian four-stage sounding rocket could reach altitudes of 850 km.
American sounding rocket. Two stage vehicle consisting of 1 x M-6 + 1 x Nike
American test vehicle. Three stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x Gosling
American sounding rocket. Three stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x Hydac
American sounding rocket. Three stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x Javelin 3
American sounding rocket. Three stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x Nike
Four stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x Nike + 1 x Cygnus 20
American test vehicle. Four stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x Nike + 1 x Recruit
American test vehicle. Five stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x Nike + 1 x Recruit + 1 x T-55
American test vehicle. Three stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x T-40
American test vehicle. Four stage vehicle consisting of 1 x M-6 + 1 x Nike + 1 x T-40 + 1 x T-55
American test vehicle. Four stage vehicle consisting of 1 x M-6 + 1 x Nike + 3 x Deacon + 1 x T-40
American sounding rocket. Two stage vehicle consisting of 1 x M-6 + 1 x Orion
American sounding rocket.
American tactical ballistic rocket.
Japanese sounding rocket. Single stage vehicle.
HOE.
American anti-ballistic missile. Two stage vehicle used to test the Homing Overlay Experiment anti-ballistic missile kill vehicle.
Holy Moses.
Popular Name of HVAR air-to-air rocket.
Honest John.
American tactical ballistic rocket. Unguided single-stage solid-propellant US Army missile developed by Douglas Aircraft. It was later used as the booster stage for a range of sounding rockets, test vehicles, and targets.
Hopi.
American sounding rocket. The Hopi-Dart vehicle consisted of a Hopi III booster as first stage, and an unpowered dart as second stage. A boosted version of the configuration used a Kiva motor as the first stage.
American sounding rocket. Single stage vehicle consisting of a Hopi III and an unpowered dart.
This single-stage-to-orbit winged horizontal takeoff/horizontal landing launch vehicle concept was powered by the unique Rolls-Royce RB545 air / liquid hydrogen / liquid oxygen rocket engine. HOTOL development was conducted from 1982 to 1986 before the British government withdrew funding. It was superseded by the Interim HOTOL design which sought to reduce development cost through use of existing Lox/LH2 engines.
Hound Dog.
First American air-launched cruise missile to become operational. Based on Navaho technology.
HP2.
Chinese sounding rocket. Two-stage solid propellant sounding rocket. Evidently used two of the first stage motors developed for the T-7A in tandem. Replaced the T-7 from 1970 on. Used for routine measurement of the upper atmosphere.
HP6.
Chinese sounding rocket. Lightweight single stage solid propellant sounding rocket. Used for routine measurement of the upper atmosphere.
HPAG.
American test vehicle. Single stage vehicle.
American test vehicle. Two stage vehicles consisting of HPAG boosters + 1 x Deacon
HPB.
American sounding rocket. Two stage vehicle consisting of 1 x Talos + 1 x M56A1
Hs-117.
Manufacturer's designation for Schmetterling surface-to-air missile.
HSM-80A.
Alternate Designation of Minuteman 1B intercontinental ballistic missile.
HSM-80B.
Alternate Designation of Minuteman 2 intercontinental ballistic missile.
HTV.
HTV
Hugo III
HVAR.
American air-to-air rocket. High-Velocity Air Rocket. An unguided fighter weapon, it was later adapted for use by NACA in the early 1950's to boost subscale aerodynamic models to supersonic speed.
American test vehicle. Two stage vehicle consisting of 1 x HVAR + 1 x Mk7
HW-1.
Johannes Winkler was a founding member and president of the VfR. On 14 March 1931, his HW-1 lifted off from a field outside of Dessau, Germany, becoming the first liquid fuel rocket in Europe to be successfully launched.
HW-2.
German sounding rocket. Johannes Winkler followed up his experimental HW-1 by the much larger and ambitious HW-2, which had an aerodynamic teardrop-shaped outer shell and a very respectful fuel mass fraction of 72% using an aluminium-magnesium structure.
North Korean mobile liquid propellant single stage tactical ballistic missile. Reverse-engineered from Russian R-17's provided by Egypt around 1980. Often referred to as 'Scud-B'. 340 km range compared to 300 km for the original R-17 design.
North Korean mobile liquid propellant single stage tactical ballistic missile. Derived from Russian R-17, often referred to as 'Scud-C'. The Hwasong had a 500 km range, achieved by halving the payload.
North Korean mobile liquid propellant single stage tactical ballistic missile. Derived from Russian R-17, often referred to as 'Scud-D'. The Hwasong had a 700 km range with a 500 kg payload and went into service in 1994.
American sounding rocket.
American sounding rocket.
American sounding rocket. Two stage underwater-launched vehicle consisting of 3 x Sparrow motors in the booster stage and an Iris upper stage.
American test vehicle. Two stage vehicle consisting of 1 x NB-52 + 1 x Orion 50S
American sounding rocket. Series of single-stage sounding rockets using eAc hybrid propulsion.
American nuclear-powered orbital launch vehicle. Hyperion was considered in 1958 as a ca. 1970 Saturn follow-on. It used a small jettisonable chemical booster stage that contained chemical engines and the LOX oxidizer for the conventional engines.
American sled-launched SSTO VTOVL orbital launch vehicle. Yet another of Philip Bono's single-stage-to-orbit designs of the 1960's, using a plug-nozzle engine for ascent and as a re-entry heat shield. Hyperion would have taken 18,100 kg of payload or 110 passengers to orbit or on 45 minute flights to any point on earth. Hyperion used a sled for launch, which would have seriously hurt its utility. The sled gave a 300 m/s boost to the vehicle before it ascended to orbit. The sled would have 3 km of straight course, followed by 1 km up a mountainside, with a 3 G acceleration.
HYSR.
American sounding rocket. Hybrid single stage rocket intended to replace multiple-stage sounding rockets.
HySTP.
Alternate Designation of X-30 ssto winged orbital launch vehicle.
Following the cancellation of Saenger II, Germany briefly considered a manned X-15/NASP type flight test vehicle (HYTEX) capable of Mach 6 flight. This too was cancelled for cost reasons.
IATV.
Indian Advanced Technology Vehicle consisting of a solid propellant booster first stage and a scramjet second stage. The booster burned for 120 seconds to take the scramjet to an altitude of 46km and a speed of Mach 6, at which point the scramjet would ignite.
American sounding rocket.
I-Hawk.
Popular Name of MIM-23B surface-to-air missile.
American orbital launch vehicle. Same concept as Shuttle C. Shuttle orbiter replaced by recoverable pod with shuttle main engines and payload cannister. Quick way for US to obtain heavy payload capability and reduce shuttle cost per kg to orbit by 3 X.
Argentinan sounding rocket.
Ikar.
Popular Name of Dnepr intercontinental ballistic missile.
Ikar.
Ukrainian intercontinental ballistic missile. Ikar was Yuzhnoye's design for a heavy ICBM, a next-generation replacement for the R-36M2. Design was begun at the beginning of the 1990's under Stanislav Us. It may have used all-solid propellants, and nested rocket stages. Work was quickly dropped after the dissolution of the Soviet Union.
IM-70.
Alternate designation for Talos missile.
IM-99A.
Alternate Designation of CIM-10A surface-to-air missile.
IM-99B.
Alternate Designation of CIM-10B surface-to-air missile.
American sounding rocket. Unguided solid propellant single stage rocket using a military surplus M112 Hawk rocket motor. The motor was a dual thrust burner with a boost phase of 5 seconds and a sustainer phase of approximately 21 seconds. The rocket accelerated the payload then for 26 seconds with peak acceleration during the boost phase of 21g. A payload mass of 100 kg could be carried to an apogee of approximately 110 km.
American low cost orbital launch vehicle. Low-cost hybrid launch vehicle proposed by AMROC in the 1980's.
Canadian gun-launched sounding rocket. Columbiad Launch Services announced itself publicly in August 2003. They were then developing a high-volume Industrial Sounding System based on gun propulsion technology, which was scheduled to be fully operational by late 2004. This would also serve as a prototype for a follow-on orbital gun-based launch system.
Russian orbital launch vehicle. While Chelomei's OKB was still preparing the UR-200 draft project, it was proposed to use this as the basis for the UR-500 heavy universal rocket, with five times the payload capacity. These initial 1961 studies consisted of 4 two-stage UR-200 rockets lashed together, the first and second stages working in parallel in clusters. A third stage would be modified from the UR-200 second stage. However analysis indicated that the payload capacity could not meet the military's requirements.
INTA.
The Instituto Nacional de Tecnica Aerospacial was tasked in 1967 to develop Spain's first sounding rocket. INTA contracted with British Aerojet to provide the necessary technical expertise and designed a rocket built from existing British solid motors. This was followed by versions using Spanish-manufactured versions of British motors. The stop-and-go program extended over nearly 30 years.
Spanish sounding rocket. Vehicle consisting of 4 x Chick + 1 x Goose. All motors ignited simultaneously at lift-off, the Chicks burning for 0.2 seconds, while the Goose continued for 17 seconds.
Spanish sounding rocket. Two stage vehicle consisting of 1 x Heron + 1 x Snipe
Spanish sounding rocket. Later version for heavier payloads fired in 1993-1994.
Interim Heavy Lift Launch Vehicle.
Alternate designation for IHLLV orbital launch vehicle.
Initiated by a British Aerospace team led by Dr Bob Parkinson in 1991, this was a less ambitious, scaled-back version of the original HOTOL. The single-stage to orbit winged launch vehicle using four Russian rocket engines. It was to have been air-launched from a Ukrainian An-225 Mriya (Dream) aircraft. Interim HOTOL would separate from the carrier aircraft at subsonic speeds, and would then pull up for the ascent to orbit. It would return via a gliding re-entry and landing on gear on a conventional runway. Interim HOTOL suffered from the same aerodynamic design challenges as HOTOL and went through many, many design iterations in the quest for a practical design.
Interstate BQ-4-TDR.htm.
Alternate designation for BQ-4-TDR intermediate range cruise missile.
Iranian short range ballistic missile.
Iris.
American sounding rocket. Sounding rocket developed by Navy, then handed over to NASA. Flown only four times, but then used in unique Hydra-Iris test series.
Russian short-range ballistic missile.
American winged rocketplane. CIA air-launched, rocket-powered high speed manned vehicle project of 1965-1968 that developed basic technologies used in later shuttle and reusable launch vehicle programmes.
New Russian tactical ballistic missile, conceived as a follow-on to the Scud. First fired on 25 October 1995.
American SSTO VTOVL orbital launch vehicle. An adaptation of Phillip Bono's enormous ROMBUS plug-nozzle semi-single-stage-orbit launch vehicle as a 1,200 soldier intercontinental troop transport!! The recoverable vehicle would re-enter, using its actively-cooled plug nozzle as a heat shield.
Ithacus Senior.
Alternate designation for Ithacus ssto vtovl orbital launch vehicle.
J.
Library of Congress Designation of Energia orbital launch vehicle.
J.
Japanese all-solid orbital launch vehicle. All-solid rocket motor launch vehicle. Because of the high cost, the original J-1 design was superseded by an alternate J-1 F2 with a different booster stage.
J-1.
Library of Congress Designation of Zenit-2 orbital launch vehicle.
J-1.
Japanese all-solid orbital launch vehicle. Original version.
Japanese all-solid orbital launch vehicle. Lower cost alternate to the original J-1 design. Uses the SRB-A of the H-2A vehicle as the first stage, the second and third stages of the J-1, with updated avionics.
The Rook motor was 0.43 m in diameter and 5.28 m long. It contained a case-bonded charge of 846 kg of non-aluminized plastic propellant giving a total impulse of 1760 kN-seconds in 5.6 seconds; with a maximum thrust of 323 kN and a specific impulse of 213 seconds. The motor was capable of withstanding the 40g acceleration it provided during firing. It was employed as the first propulsion stage of the Leopard and Jaguar (Jabiru) supersonic test vehicles, and by itself in single-stage test applications.
Two stage version consisting of 1 x Rook IIIA + 1 x Rook IIIB
The Jaguar was designed by the RAE Supersonics Department as part of the HRV (Hypersonic Research Vehicle) program. This was a joint project with the Australian Weapons Research Establishment for testing of re-entry vehicles at high speeds. Regardless of the variant, the Rook first stage would propel the upper stages and subscale RV to a high altitude. The upper stages would then fire downward to push the RV into the atmosphere at speeds of up to 5 km/s. After the conclusion of the HRV project in April 1970, tests continued using the Jabiru 3 with other aerothermal experiments until November 1974.
Three stage version consisting of 1 x Rook II + 1 x Gosling IIN + 1 x Lobster I
Three stage version consisting of 1 x Rook IIIA + 1 x Goldfinch II + 1 x Gosling IV
American air-launched test vehicle. Three stage vehicle air launched from a B-57A Canberra. The rocket consisted of consisting of 3 x Recruit + 1 x Recruit + 1 x Baby Sergeant
Japanese winged orbital launch vehicle. NAL / Mitsubishi Heavy Industries, Ltd. design for a single stage to orbit spaceplane. Crew of ten, empty mass 110 tonnes. LACE / Scramjet engines, 29 m wingspan.
American orbital launch vehicle. Launch vehicle planned for Pacific launch based on Saturn V engines, tooling. Masses, payload estimated.
American sounding rocket. The five-stage Jason rocket was developed by the US Air Force for monitoring of radiation in near-earth space (700-800 km) after high altitude nuclear explosions. Originally known as the Argo E-5, it consisted of an Honest John plus Nike plus Nike plus Recruit plus T-55. First used in 1958.
JATO.
American sounding rocket. JATO (Jet Assisted Take-Off) rockets came in many types and were used to shorten the takeoff of aircraft in short field or overload conditions. They were among the first practical applications of rocketry, and much early development of rocket technology by JPL, Aerojet, Goddard, and others was devoted to JATO applications.
American sounding rocket. The four-stage Javelin rocket was originally known as the Argo D-4 and was developed by the Air Force to replace its Jason rocket with the mission of measuring radiation in space after high-altitude nuclear explosions. It was subsequently used by NASA for a variety of high-altitude near-space scientific experiments.
American sounding rocket.
JCR.
Japanese sounding rocket. Single stage vehicle.
First Israeli ballistic missile. Developed by Dassualt in France as the MD-620. Test series included both one and two stage prototypes. Follow-on versions were said to have differed.
Israeli short range ballistic missile. Follow-on version differed from original French-derived Jericho. Probably used a single 4500 kg solid-propellant motor.
Israeli intermediate range ballistic missile. Tactical ballistic missile. Probably corresponds to first two stages of Shavit launch vehicle.
Jericho II.
Alternate designation for Jericho 2 intermediate range ballistic missile.
Jericho-1.
Alternate designation for Jericho 1 short range ballistic missile.
JL-1.
Chinese submarine-launched ballistic missile. Two stage vehicle consisting of 1 x DF-21 + 1 x DF-21 St2
JL-2.
Chinese intercontinental ballistic missile. DF-23, DF-31 are land based versions.
American sounding rocket. Five stage vehicle of the Argo series consisting of 2 x Recruit + 1 x Sergeant + 1 x Lance + 1 x Lance + 1 x Altair
American sounding rocket. Single stage vehicle.
Julang-1.
Popular Name of JL-1 submarine-launched ballistic missile.
Julang-2.
Popular Name of JL-2 intercontinental ballistic missile.
American gun-launched orbital launch vehicle. Following the failure of the US government to fund further development of the SHARP light gas gun, John Hunter founded the Jules Verne Launcher Company in 1996 in an attempt to fund commercial development of the concept.
French gun-launched orbital launch vehicle. Jules Verne's moon gun, as described in his 1865 novel From the Earth to the Moon, was located in Florida. Although some errors were made, Verne used real engineering analysis to arrive at the design of his cannon and manned moon projectile. As a result, at the time of Apollo 8 and 11 missions it was noted that Verne had made an astonishing number of correct predictions about the actual missions....
Juno.
Juno I.
Alternate designation for Jupiter C orbital launch vehicle.
American orbital launch vehicle. Satellite launcher derived from Jupiter IRBM. Basic 4 stage vehicle consisted of 1 x Jupiter + 1 x Cluster stage 2 + 1 x Cluster stage 3 + 1 x RTV Motor
American intermediate range ballistic missile. Three stage version consisting of 1 x Jupiter + 1 x Cluster stage 2 + 1 x Cluster stage 3
Juno V.
Alternate designation for Saturn I orbital launch vehicle.
American orbital launch vehicle. By 1958 the Super-Jupiter was called Juno V and the 4 E-1 engines were abandoned in favor of clustering 8 Jupiter IRBM engines below existing Redstone/Jupiter tankage. The A version had a Titan I ICBM as the upper stages. Masses, payload estimated.
American orbital launch vehicle. A proposed version of the Juno V for lunar and planetary missions used a Titan I ICBM first stage and a Centaur high-energy third stage atop the basic Juno V cluster. Masses, payload estimated.
American intermediate range ballistic missile. The Jupiter IRBM was developed for the US Army. By the time development was complete, the mission and the missile was assigned to the US Air Force, which had its own nearly identical missile, the Thor. Jupiters were stationed in Turkey and Italy in the early 1960's, but withdrawn in secret exchange for the withdrawal of Soviet R-5 missiles from Cuba. The Jupiter was used as the first stage of the relatively unsuccessful Juno II launch vehicle, and proposed for the Juno III and Juno IV. Jupiter tooling and engines were used to build the much larger Juno V / Saturn I launch vehicle.
American orbital launch vehicle. The Jupiter A was a modified Redstone missile fitted with Jupiter inertial navigation and control system elements. It also tested Hydyne fuel and other engine modifications for the Jupiter C re-entry vehicle test booster.
American orbital launch vehicle. Re-entry vehicle test booster and satellite launcher derived from Redstone missile. The Jupiter A version of the Redstone missile was modified with upper stages to test Jupiter re-entry vehicle configurations. Von Braun's team was ordered to ballast the upper stage with sand to prevent any 'inadvertent' artificial satellites from stealing thunder from the official Vanguard program. Korolev's R-7 orbited the first earth satellite instead. The Jupiter C was retroactively named the 'Juno I' by Von Braun's team.
American short range ballistic missile. Four stage orbital launch version consisting of 1 x Redstone + 1 x Cluster stage 2 + 1 x Cluster stage 3 + 1 x RTV Motor. The fourth stage allowed the Explorer payload to be placed into orbit.
American intermediate range ballistic missile. Version of Jupiter IRBM designed for launch of Mercury manned capsules on long suborbital flights. Cancelled early in the programme, with the decision being to proceed from Mercury Redstone suborbital flights directly to Mercury Atlas orbital missions.
K-1.
Alternate Designation of R-21 submarine-launched ballistic missile.
K-15.
K-15
K150.
Japanese sounding rocket. 1/1.6 subscale test rocket used in development of the Kappa 9L sounding rockets.
K245.
Japanese sounding rocket. Subscale test rocket used in development of the Kappa series of sounding rockets.
Russian orbital launch vehicle. Two stage vehicle for suborbital tests consisting of 1 x R-14 + 1 x S3M.
Russian orbital launch vehicle. Two stage vehicle for suborbital tests consisting of 1 x R-14 + 1 x S3M.
K65UP.
Article Number of Vertikal-4 orbital launch vehicle.
Kaiser Wilhelm Geschuetz.
Manufacturer's designation for Paris Gun gun-launched missile.
Kaituozhe-1.
Manufacturer's designation for KT-1 all-solid orbital launch vehicle.
Kaituozhe-2.
Manufacturer's designation for KT-2 all-solid orbital launch vehicle.
Kaituozhe-2A.
Manufacturer's designation for KT-2A all-solid orbital launch vehicle.
American sounding rocket.
Japanese SSTO VTOVL orbital launch vehicle. Kawasaki design for single stage to orbit reusable booster. Would carry 50 passengers to orbiting hotels or fast intercontinental flights.
Japanese sounding rocket. The Kappa series represented Japan's first large post-war indigenously-developed sounding rockets. They led eventually to the Lambda and Mu solid rocket satellite launchers.
Japanese sounding rocket. Single stage vehicle.
Japanese sounding rocket. 2-3 stage vehicle consisting of 1 x K420H + 1 x K420(1/3)
Japanese sounding rocket. Two stage vehicle consisting of 1 x K420H + 1 x K420(1/3)
Japanese sounding rocket. Three stage vehicle consisting of 1 x K420H + 1 x K420(1/3) + 1 x K10S
Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 3 Booster + 1 x Kappa 1
Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 3 Booster + 1 x Kappa 1
Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 4 Booster + 1 x Kappa 4
Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 4 Booster + 1 x Kappa 4
Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 6 + 1 x Kappa 6 St2
Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 6H + 1 x Kappa 6 St2
Japanese sounding rocket. Single stage vehicle.
Japanese sounding rocket. Two stage vehicle consisting of 1 x K420 + 1 x Kappa 8
Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 6H + 1 x Kappa 8L
Japanese sounding rocket. 2-3 stage vehicle consisting of 1 x K420H + 1 x K250 + optional upper stage.
Japanese sounding rocket. Three stage vehicle consisting of 1 x K420 + 1 x Kappa 6 + 1 x Kappa 6 St2
Japanese sounding rocket. Two stage vehicle consisting of 1 x K420H + 1 x K250
Russian surface-to-surface missile. Unguided rocket built in a variety of calibres and used by the Red Army from 1941 onward.
Kavoshgar.
Alternate designation for Safir-2 orbital launch vehicle.
KD2U-1.
Alternate designation for Regulus 2 intermediate range cruise missile.
KDU-1.
Alternate Designation of BQM-6C intermediate range cruise drone.
Russian intercontinental boost-glide missile. Soviet version of the Saenger antipodal bomber intensely studied on Stalin's direct orders in 1946-1947. The final study concluded that, given the fuel consumption of foreseeable rocket engines, the design would only be feasible using ramjet engines and greatly advanced materials. This meant that development could only begin in the late 1950's, when such technologies were available. By that time the design had been superseded by more advanced concepts.
Russian air-to-surface missile. Chelomei mobile-launched version of V-1
Russian air-to-surface missile. Chelomei mobile-launched version of V-1
American sounding rocket. Two stage vehicle consisting of 1 x Kisha + 1 x Judi III
American low-cost orbital launch vehicle. The Kistler K-1 was a reusable two-stage launch vehicle developed by a prestigious team of ex-Apollo managers, designed originally for launch of Iridium-class communications satellites to medium altitude earth orbit. Kistler began development but had to file for Chapter 11 protection before detailed hardware fabrication was completed. It emerged from bankruptcy in 2005, and merged with suborbital startup Rocketplane to form Rocketplane Kistler. On 8 November 2006, it was announced that Alliant Techsystems, as lead contractor, would complete the K-1 launch vehicle, with Rocketplane Kistler as a subcontractor, under NASA's Commercial Orbital Transportation Services (COTS) program.
American sounding rocket developed to measure winds aloft in support of nuclear tests.
American sounding rocket. Two stage vehicle consisting of 1 x Kiva + 1 x Hopi
Ukrainian intercontinental ballistic missile. Koltso was a Yuzhnoye advanced ICBM, subject of decrees of 29 September 1976 and 31 May 1984. Development was authorised by the project was cancelled after the collapse of the ICBM.
Australian sounding rocket. Two stage vehicle consisting of 1 x Lupus + 1 x Musca
Ukrainian intercontinental ballistic missile. Kopye-R was a Yuzhnoye advanced ICBM, subject of a draft project completed in February 1986. Development was authorised by the project was cancelled after the collapse of the ICBM.
Korea Sounding Rocket-I.
Manufacturer's designation for KSR-I sounding rocket.
Korea Sounding Rocket-II.
Manufacturer's designation for KSR-II sounding rocket.
Korea Sounding Rocket-III.
Manufacturer's designation for KSR-III sounding rocket.
Korea Space Launch Vehicle-I.
Manufacturer's designation for KSLV-I and KSLV-I 2002 orbital launch vehicles.
Korea Space Launch Vehicle-II.
Manufacturer's designation for KSLV-II orbital launch vehicle.
Korea Space Launch Vehicle-III.
Manufacturer's designation for KSLV-III orbital launch vehicle.
American surface-to-air missile. South Korea displayed a modification of the Nike Hercules with a new monolithic single-engine solid propellant stage of South Korean manufacture. The modification was believed to also have guidance changes allowing it to serve as a surface-to-surface missile.
Kosmos 1.
Alternate designation for Kosmos 65S3 orbital launch vehicle.
Ukrainian orbital launch vehicle. Series production version of satellite launcher based on Yangel R-12 IRBM. Succeeded 63S1M prototype from 1965, using same 'Dvina' launch complex. From March 16, 1967 orbital launches from Plesetsk were from the purpose-built 'Raduga' launch complex LC133. Total of 123 launches, of which 8 were failures.
Russian orbital launch vehicle. Initial serial production version was the Kosmos-3, built at the Krasnoryarsk Machine Factory. Flew only four times, with two failures, before being succeeded by the modernized production version under the responsibility of NPO Polyot.
Russian orbital launch vehicle. Definitive and prolific production version of satellite launcher based on Yangel R-14 IRBM. After further development at NPO Polyot (Omsk, Chief Designer A S Klinishkov), the modified Kosmos-3M added a restartable second stage with an orientation system. This booster was launched form two 'Cusovaya' launch complexes from 1967. The second stage used low thrust rockets using gas generator output to adjust the final velocity of the stage
Ukrainian orbital launch vehicle. In 1960 the Soviet government decreed development of a lightweight launch vehicle for launch of payloads not requiring R-7 family of boosters. A modification of the R-12 IRBM was selected as the first stage; a new high-performance second stage was developed using a unique Lox/UDMH propellant combination. After two failures, the first successful flight was on March 16, 1962.
Kosmos 2I.
Alternate designation for Kosmos 63S1 and Kosmos 11K63 orbital launch vehicles.
Kosmos 2M.
Alternate designation for Kosmos 63S1M orbital launch vehicle.
Kosmos 3.
Alternate designation for Kosmos 11K65 orbital launch vehicle.
Russian orbital launch vehicle. In 1961 Isayev and Reshetnev developed the Voskhod space launch system on the basis of the R-14 IRBM. The initial version of the two stage rocket was designated Kosmos-1. The first 'Voskhod' launch complex was at Baikonur, a modification of one of the pads at the R-16 ICBM launch complex 41.
Kosmos 3M.
Alternate designation for Kosmos 11K65M orbital launch vehicle.
Kosmos 3MP.
Alternate designation for Kosmos 65MP orbital launch vehicle.
Ukrainian orbital launch vehicle. The 63S1 initial production version was used through May 1966 for a total of 40 launches, of which 12 were failures. It was succeeded by the 63S1M prototype for the 11K63 production space launcher.
Ukrainian orbital launch vehicle. Modernized version of 63S1 initial configuration of the first Kosmos launcher and the prototype for the production 11K63 launch vehicle. Suborbital launches from Plesetsk from 1965 at from the modified R-12 silo 'Dvina'. Flown only a few times in 1965-1967. Succeeded by the 11K63 production model launched from the 'Raduga' complex.
Russian orbital launch vehicle. Adaptation of 11K65M launcher for suborbital and single orbit test of subscale prototypes of Spiral and Buran manned spaceplanes (BOR-4 and BOR-5).
Russian orbital launch vehicle. Prototype of light satellite launcher using as a first stage the Yangel R-14 (8K65) IRBM. The protoype system was launched eight times before production was handed over to the Krasnoryarsk Machine Factory.
KR.
Russian intercontinental boost-glide missile. The KR (winged rocket) was a three-stage unmanned boost-glide missile developed at the Tupolev's OKB-156. Work began in 1957. Two alternates were considered for the first stage: a conventional liquid rocket or a special manned aircraft launcher. The second stage was a conventional rocket. The final winged stage included a propulsion section and nuclear warhead. The glider would cut-off at an altitude of 50 km and a velocity of 20,000 km/hr. Planned-over target speed was 7,000 km/hr at 30 km altitude. Work on the project continued only about a year before it was abandoned in favour of the more conventional Tu-123 supersonic cruise missile. The KR would have had a gross weight of 240 tonnes, and delivered a payload of 3 to 5 tonnes over a range of 9,000 to 12,000 km.
KR-500.
Manufacturer's designation for R-500 surface-to-air missile.
Krug.
Russian surface-to-air missile. Ramjet-powered long-range surface-to-air missile, deployed by the Soviet Union and its allies.
KSLV.
South Korean launch vehicle family. Originally they were to be of completely indigenous design; but in 2005 it was announced that they would use the (in-development, unflown) Russian Angara booster module as the basis. The program, like that of the Angara, was subject to continuous funding shortages and schedule delays. In 2008 the Angara alternate was cancelled after Russia refused to transfer essential technologies and the total cost had increased from US$ 240 million to US$ 350 million. The Korean government went 'back to the drawing board'.
In 2005 it was announced that the KSLV-I would not fly until 2007. It was now a completely different vehicle, consisting of a first stage derived from the Russian Angara launch vehicle, and a solid propellant second stage of South Korean manufacture. First launch 2009.08.25.
South Korean orbital launch vehicle. In 2002 South Korea announced it was planning to develop a small satellite launch vehicle by 2005, based on technology flown on the KSR-III test vehicle. By 2005 this was replaced by a completely different design, based on the Russian Angara space booster.
South Korean launch vehicle, originally scheduled for first flight by 2010. Evidently it would have consisted of a Russian Angara first stage and a South Korean liquid-propellant second stage. In August 2006 it was reported in the Korean press that this launcher configuration was cancelled.
South Korean launch vehicle, to consist of a Russian Angara first stage, a South Korean liquid propellant second stage, and a South Korean solid propellant apogee kick motor. Scheduled for first flight by 2015. In August 2006 the Korean press reported that the first and second stages would both be Angara-UM modules... how this configuration would work (stacked versus parallel) was unclear.
KSR.
South Korean indigenous sounding and test rocket family, using solid rocket motors and a test vehicle with a liquid oxygen/kerosene motor. Further development of the latter into the KSLV satellite launch vehicle was abandoned in 2005 in favor of licensed Russian technology.
First South Korean sounding rocket, an unguided single solid propellant stage vehicle. Development began in 1990 and the rocket was flown two times in 1993.
Two-stage South Korean sounding rocket, using two of the solid rocket motors developed for the KSR-I in tandem. Flown twice in 1997-1998.
South Korean sounding rocket. Test bed for development of an orbital launch vehicle, powered by the liquid oxygen/kerosene engine planned for the KSLV-I. However flown only once in 2002.
KT.
Family of all solid-propellant Chinese launch vehicles, using the DF-31 ICBM as the basis with new upper or lower stages to achieve a range of payload performances. Following two unsuccessful launches in 2002-2003, the project may have been abandoned.
KT-1.
Chinese all-solid orbital launch vehicle. China's first solid propellant orbital launch vehicle was derived from the first and second stages of the DF-31 ICBM with a new solid third stage. The vehicle was named Kaituozhe-1 (Explorer-1) and was capable of putting 100 kg into polar orbits.
KT-2.
Intermediate all-solid propellant Chinese launch vehicle. Model first displayed at Wuzhai in the fall of 2002. Evidently consists of new large diameter first stage motor, topped by the first two stages of the basic KT-1 vehicle. All figures are rough estimates.
Heavy all-solid propellant Chinese launch vehicle. Model first displayed at Wuzhai in the fall of 2002. Consists of two parallel first-stage booster motors derived new the first stage motor of the KT-1, a larger-diameter core second stage motor like that of the KT-2, a new larger-diameter third stage motor, and an enormous new fairing. All figures are rough estimates.
Kub.
Mid-range integral rocket-ramjet Russian surface-to-air missile, widely deployed with Soviet forces and exported to 22 countries. The missile provided one of the great technological surprises in warfare in the October 1973 Arab-Israeli War.
Kumulus was a single-stage sounding rocket developed by the German Rocket Society in the late 1950's. It could carry meteorological, postal, or biological payloads up to a speed of 750 m/s and an altitude of 20 km. All launches were made from Cuxhaven, and discontinued when the German government prohibited civilian rocket launches in June 1964. The propellant was developed by the DRG and fabricated at Liebenau Company for Production of Chemical Materials (GmbH zur Verwertung chemischer Erzeugnisse Liebenau).
Russian orbital launch vehicle. The Kvant was the Soviet third generation light launch vehicle planned to replace the Kosmos and Tsyklon series. Unlike the vehicles it was to replace, the booster used non-toxic 'environmentally friendly' liquid oxygen/kerosene propellants. Although such a light launch vehicle was on Space Forces wish lists since 1972, full scale development was again deferred due to the crash effort on Soviet 'star wars' in the second half of the 1980's. RKK Energia marketed the vehicle design from 1994 to 2001, but could find no source for development funds.
Russian orbital launch vehicle. From 1996-2001 RSC Energia carried out design studies on the Kvant-1 light launch vehicle with a low earth orbit payload capability of 1.8 to 3.0 metric tons. Market surveys seemed to indicate a need for a new launch vehicle of this class but development funding was not forthcoming.
L-1.
L3S.
Manufacturer's designation for Ariane 1 orbital launch vehicle.
La-205.
Missile article number for 205 missile.
La-206.
Missile of 206 surface-to-air missile.
La-207.
Missile of 207 surface-to-air missile.
La-207A.
Missile of 207A surface-to-air missile.
La-207T.
Missile of 207T surface-to-air missile.
La-208.
Missile of 208 surface-to-air missile.
La-215.
Missile of 215 surface-to-air missile.
La-217.
Missile of 217 surface-to-air missile.
La-217M.
Missile of 217M surface-to-air missile.
La-218.
Missile of 218 surface-to-air missile.
La-350.
Manufacturer's designation for Burya intercontinental cruise missile.
American tactical ballistic missile. Nuclear-armed short-range ballistic missile briefly deployed by the U.S. Army in the late 1950s. Its rocket motor was the basis for the Doorknob sounding rocket.
Japanese all-solid orbital launch vehicle. All solid-propellant vehicle, Japan's first satellite launcher. The L-4S project simulated the procedures and demonstrated the capabilities required for orbital satellite launch essential to the follow-on Mu project.
Japanese test vehicle. 3-4 stage vehicle series.
Japanese test vehicle. Four stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x K420 + 1 x Kappa 8
Japanese test vehicle. Four stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500
First Japanese orbital launch vehicle.
Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S
Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S
Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S
Lance.
American short range ballistic missile, which replaced the Little John, Sergeant and Honest John rockets in US Army service in the 1970's. Retired in 1992.
American surface-to-air missile. Land based-version of Terrier surface-to-air missile. Development begun in 1951. Project cancelled in 1956.
Indonesian sounding rocket.
Lark.
American surface-to-air missile. Lark missile.
LART.
German winged orbital launch vehicle. MBB/ERNO airbreathing horizontal takeoff / horizontal landing single stage to orbit proposal from the mid-1980s. Largely similar to the BAe HOTOL.
LASM.
Land Attack Standard Missile, a derivative of the Standard Missile SM-2MR naval air-defense designed to provide surface-to-surface fire support for the US Marine Corps.
La-X.
Library of Congress Designation of Burya intercontinental cruise missile.
LCLV.
American low cost orbital launch vehicle. As a result of TRW's review of the Truax/Aerojet Sea Dragon, TRW became so interested in the concept that they undertook studies of their own, which resulted in a design that became known as the 'Big Dumb Booster'. They proposed structural approaches that were even more conservative than Aerojet's, e.g., the use of T-180 steel instead of maraging steel, which would result in even heavier and cheaper tankage. TRW finally obtained USAF funding for fabrication of stage sections and demonstration of scaled-up versions of the TRW pump-fed Apollo Lunar Module ascent engine. The design promised low cost access to space using low technology (steel stages built to low tolerances in shipyards, pressure-fed engines, and low cost storable propellants). But yet again neither NASA or USAF showed interest in true cheap access to space.
LEAP.
Standard warhead of Standard SM-3 anti-ballistic missile.
LEAP.
American anti-ballistic missile. Lightweight Exo- Atmospheric Projectile. SDIO/BMDO project
LEM-70.
Department of Defence Designation of Minuteman ERCS strategic communications missile.
Satellite launcher derived from planned Israeli Shavit-2 launch vehicle, but with rocket motors and major components built in USA to qualify for US contracts.
Israeli all-solid orbital launch vehicle. As Leolink LK-1, but with a Castor-120 motor as the first stage.
British test vehicle. Two stage aerodynamic test vehicle consisting of 1 x Rook + 1 x Gosling. Developed from the basic Rook vehicle for tests requiring higher velocities.
Lex.
French sounding rocket. Single stage vehicle.
LGM-118A.
Department of Defence Designation of Peacekeeper intercontinental ballistic missile.
LGM-134.
Department of Defence Designation of SICBM intercontinental ballistic missile.
LGM-25A.
Department of Defence Designation of Titan 1 intercontinental ballistic missile.
LGM-25C.
Department of Defence Designation of Titan 2 intercontinental ballistic missile.
LGM-30A.
Department of Defence Designation of Minuteman 1A intercontinental ballistic missile.
LGM-30B.
Department of Defence Designation of Minuteman 1B intercontinental ballistic missile.
American intercontinental ballistic missile. Mobile version of Minuteman. Development begun in 1955. Cancelled in 1962.
LGM-30F.
Department of Defence Designation of Minuteman 2 intercontinental ballistic missile.
LGM-30G.
Department of Defence Designation of Minuteman 3 intercontinental ballistic missile.
American low cost orbital launch vehicle. Private commercial launch vehicle.
Russian air-launched winged orbital launch vehicle. LII (the Gromov Experimental Flight Institute at Zhukoskiy) designed several alternate spaceplane concepts for air-launch from the An-225 transport. These were similar to the various MAKS concepts.
Unidentified American expermental silo-launched interceptor missile, probably the Sprint II concept.
LIM-49A.
Department of Defence Designation of Spartan anti-ballistic missile.
Unidentified American expermental silo-launched interceptor missile, possibly the Sprint ABM.
Little Joe was used to test the Mercury capsule launch escape system. The booster was designed by NASA Langley using existing components. Six to eight solid rocket motors were mounted in an aerodynamic finned fairing built by North American.
American test vehicle.
American test vehicle. Two stage vehicle consisting of 4 x Recruit + 2 x Pollux
American test vehicle. Two stage vehicle consisting of 4 x Recruit + 4 x Castor
American test vehicle. Two stage vehicle consisting of 4 x Recruit + 4 x Pollux
American test vehicle. Little Joe II was an enlarged version of the Little Joe concept used in the Mercury program, used to test the Apollo capsule launch escape system. The vehicle was designed by General Dynamics. Six to nine solid rocket motors were mounted in an aerodynamic finned fairing.
American test vehicle. Single stage vehicle consisting of 6 x Algol 1D motors.
American test vehicle. Single stage vehicle consisting of 4 x Recruit + 2 x Algol 1D fired in sequence.
American test vehicle. Single stage vehicle consisting of 5 x Recruit + 4 x Algol 1D fired in sequence.
American test vehicle. Single stage vehicle consisting of 6 x Recruit + 1 x Algol 1D fired in sequence.
American tactical ballistic rocket. The Little John was the smallest nuclear-capable rocket the U.S. Army ever deployed. Studies to develop a lightweight rocket based on the M31/MGR-1 Honest John to give airborne Army units a nuclear capability began in 1953 under the name Honest John Junior. After preliminary studies by Douglas during 1954, the development program - renamed as Little John - was officially started at Redstone Arsenal in June 1955.
Livermore Light Gas Gun.
Manufacturer's designation for SHARP gun-launched test vehicle.
LLV.
Manufacturer's designation for Athena-1 all-solid orbital launch vehicle.
LLV 2.
Manufacturer's designation for Athena-2 all-solid orbital launch vehicle.
LLV 3.
Manufacturer's designation for Athena-3 all-solid orbital launch vehicle.
LMLV.
Alternate designation for Athena-1 all-solid orbital launch vehicle.
LMLV 2.
Alternate designation for Athena-2 all-solid orbital launch vehicle.
LMLV 3.
Alternate designation for Athena-3 all-solid orbital launch vehicle.
American anti-ballistic missile. Low-Altitude Defense System, BTDS, SDIO/BMDO project
American surface-to-surface missile. In 1955 Convair undertook a small R&D program to develop a resupply missile that would deliver supplies and communications equipment to surrounded or isolated Army field units.
American sled-launched winged orbital launch vehicle. Lockheed's HTHL TSTO spaceplane concept from 1963, an outgrowth of an earlier USAF study with Hughes. The fully reusable orbiter would have been carried by a sled-launched booster rocket rocketplane.
Loki.
American unguided solid-propellant barrage anti-aircraft rocket adapted to use as a meteorological sounding rocket.
American sounding rocket. Single stage vehicle.
American sounding rocket. Balloon-launched Loki with larger fins for stability at high altitudes. The basic Loki was used in this manner on 23 September 1955, measuring cosmic rays.
Long March 1.
Alternate designation for CZ-1 orbital launch vehicle.
Long March 1C.
Alternate designation for CZ-1C orbital launch vehicle.
Long March 1D.
Alternate designation for CZ-1D orbital launch vehicle.
Long March 1M.
Alternate designation for CZ-1M orbital launch vehicle.
Long March 2A.
Alternate designation for CZ-2A orbital launch vehicle.
Long March 2C.
Alternate designation for CZ-2C orbital launch vehicle.
Long March 2D.
Alternate designation for CZ-2D orbital launch vehicle.
Long March 2E.
Alternate designation for CZ-2E orbital launch vehicle.
Long March 2E(A).
Alternate designation for CZ-2E(A) orbital launch vehicle.
Long March 2F.
Alternate designation for CZ-2F orbital launch vehicle.
Long March 3.
Alternate designation for CZ-3 orbital launch vehicle.
Long March 3A.
Alternate designation for CZ-3A orbital launch vehicle.
Long March 3B.
Alternate designation for CZ-3B orbital launch vehicle.
Long March 3B(E).
Alternate designation for CZ-3B(A) orbital launch vehicle.
Long March 3C.
Alternate designation for CZ-3C orbital launch vehicle.
Long March 4A.
Alternate designation for CZ-4A orbital launch vehicle.
Long March 4B.
Alternate designation for CZ-4B orbital launch vehicle.
Long March 4C.
Alternate designation for CZ-4C orbital launch vehicle.
Long March Next Generation Launch Vehicle Type A.
Alternate designation for CZ-NGLV-522-HO orbital launch vehicle.
Long March Next Generation Launch Vehicle Type B.
Alternate designation for CZ-NGLV-504-HO orbital launch vehicle.
Long March Next Generation Launch Vehicle Type C.
Alternate designation for CZ-NGLV-540-HO orbital launch vehicle.
Long March Next Generation Launch Vehicle Type D.
Alternate designation for CZ-NGLV-504 orbital launch vehicle.
Long March Next Generation Launch Vehicle Type E.
Alternate designation for CZ-NGLV-522 orbital launch vehicle.
Long March Next Generation Launch Vehicle Type F.
Alternate designation for CZ-NGLV-540 orbital launch vehicle.
Long March Next Generation Light Launch Vehicle.
Alternate designation for CZ-NGLV-200 orbital launch vehicle.
Long Tank Augmented Thrust Thor.
Alternate designation for Thorad SLV-2H Agena D orbital launch vehicle.
Long Tank Thor.
Alternate designation for Delta 0100, Delta L, Delta M, and Delta N orbital launch vehicles.
Australian sounding rocket. Two stage vehicle consisting of 1 x Long Tom + 1 x Mayfly
Loon.
American short range cruise missile, a copy of the German V-1 (Fieseler Fi 103).
Australian test vehicle. Two stage vehicle consisting of 1 x Dorado + 1 x Lupus
American orbital launch vehicle. This variant of the Shuttle C was envisioned for delivery of liquid hydrogen and liquid oxygen to orbit.
Low Cost Launch Vehicle.
Full name of LCLV low cost orbital launch vehicle.
American air-launched target rocket. Air-launched anti-ballistic missile target composed of two surplus SR19 states in tandem.
LS-A.
Japanese test vehicle. Early suborbital test version of the Lambda rocket series.
LS-C.
Japanese test vehicle. Two stage vehicle consisting of 1 x LS-C Booster + 1 x LS-C
Japanese test vehicle. Early suborbital test version of the Lambda rocket series.
American Naval Ordnance Test Station solid-propellant test vehicle to support development of ramjet-powered missiles. Flew in 1949 and was 4.5 m long.
Luna.
Luna.
Russian tactical ballistic rocket.
Russian orbital launch vehicle. R-7 ICBM with single-engine upper stage used for early Soviet unmanned lunar shots.
Luna-M.
Russian tactical ballistic rocket.
French tactical ballistic missile.
LV-109.
Manufacturer's designation for Millenium Express ssto vtovl orbital launch vehicle.
LV-2.
LV-2
LV-3A.
Department of Defence Designation of Atlas Agena D orbital launch vehicle.
LV-3B.
Department of Defence Designation of Atlas LV-3B - Mercury orbital launch vehicle.
American orbital launch vehicle. First operational version of Atlas ICBM and used as launch vehicle for Project Mercury.
LV-3C.
Department of Defence Designation of Atlas Centaur orbital launch vehicle.
M-1.
Alternate designation of S-25 missile.
Two-stage, solid propellant, fin stabilized, unguided Russian sounding rocket, fired in greater numbers than any other. At least 6,640 of all models were fired to the edge of space before the vehicle was discontinued in 1990. 4,908 of the basic M-100 model were fired from 1957-07-11 to 1983-09-28.
Russian sounding rocket.
Russian sounding rocket. Special modification, only fired twice on 1976-11-10 and 1976-12-22.
Russian sounding rocket. Model calibrated with Western sounding rockets and part of the World Meteorological Network. 1,730 launched from 1976-01-07 to 1990-12-.
M-11.
Alternate designation for DF-11 short range ballistic missile.
M14.
Alternate designation for Pershing 1 intermediate range ballistic missile.
M19.
Alternate designation for Pershing 1A intermediate range ballistic missile.
M-2.
Launch System of V-753 surface-to-air missile.
M-20.
Alternate designation for Sergeant missile.
M26.
Department of Defence Designation of MLRS tactical ballistic rocket.
M-28.
Department of Defence Designation of Davy Crockett M-28 tactical ballistic rocket.
M-29.
Department of Defence Designation of Davy Crockett XM-29 tactical ballistic rocket.
M-40.
Manufacturer's designation for Buran intercontinental cruise missile.
M47 + M32, M51 + M34, M15 motors.
Alternate designation for Little John tactical ballistic rocket.
M50.
Alternate designation for MGR-1B tactical ballistic rocket.
M-51.
Russian intercontinental cruise missile. Intercontinental cruise missile based on M-50 manned bomber. Subsonic cruise with Mach 2 dash into the target area.
American sounding rocket. Two stage vehicle consisting of 1 x M55E1 + 1 x SR19AJ1
M6, M30, M31.
Alternate designation for MGR-1A tactical ballistic rocket.
M-7.
Chinese short range ballistic missile. Surface-to-surface derivative of the HQ-2 air defense missile. US designation is CSS-8. Exported to Iran as Tamdar & Tondar in Iran.
M-9.
Export version of the DF-15 intermediate range ballistic missile.
Mace.
Popular Name of CGM-13A intermediate range cruise missile.
Mace.
Alternate Designation of Bulava intercontinental ballistic missile.
Mace.
American intermediate range cruise missile. Intermediate range cruise missile. Only Cape Canaveral launches are listed here, but over 30 launches were also conducted from Launch Area Able-51 by Det 1, 4504th CCTW at Holloman AFB, New Mexico from October 1959 throurgh 1963.
Mace-B.
Popular Name of CGM-13B intermediate range cruise missile.
Rudolf Nebel's subscale prototype for a man-carrying rocket was flown eight times in 1933. Further tests were prohibited by the Nazi government. This would be the largest German rocket launched until the A3 in 1937.
American heavy-lift orbital launch vehicle. Notional NASA/MSFC heavy lift booster design, using no shuttle components but instead new technologies from the EELV and RLV programs that supposedly would reduce launch cost by a large factor. A composite core vehicle powered by RS-68 engines was flanked by two shuttle liquid rocket boosters. Baseline launch vehicle used in most NASA manned lunar and Mars mssion studies 1996-2004.
MAKS.
Russian air-launched winged orbital launch vehicle. The MAKS spaceplane was the ultimate development of the air-launched spaceplane studies conducted by NPO Molniya. The draft project for MAKS was completed in 1988 and consisted of 220 volumes, generated by NPO Molniya and 70 sub-contractors and government institutes. Development of MAKS was authorised but cancelled in 1991. At the time of the cancellation, mock-ups of both the MAKS orbiter and the external tank had been finished. A 9,000 kgf experimental engine with 19 injectors was tested. There were 50 test burns proving the separate modes and a smooth switch between them. Since it was expected that MAKS could reduce the cost of transport to earth orbit by a factor of ten, it was hoped in the 1990's that development funding could be found. However this did not materialise. MAKS was to have flown by 1998.
Russian winged orbital launch vehicle. NPO Molniya, Antonov, and TsAGI proposed a spaceplane demonstrator project to the European Space Agency in 1993-1994 under the RADEM project. This would be a scaled-back version of the cancelled MAKS spaceplane using existing rocket engines. An unmanned prototype of the MAKS would be fitted out with RD-120 Lox/Kerosene engines. Launched from atop the An-225, the MAKS-D would reach an altitude of 80 to 90 km and a speed of Mach 14 to 15.
Russian winged orbital launch vehicle. Fully reusable unpiloted verion of MAKS, similar to Interim HOTOL. Air launched from An-225. MAKS was found to have superior payload, lower non-recurring cost and technical risk. MAKS-M would require new materials. Release conditions: Piggy-back, 275,000 kg, 38.0 m length x 24.0 m wingspan, 900 kph at 9,500 m altitude. Effective velocity gain compared to vertical launch 270 m/s. Payload bay 7.0 m long x 4.6 m diameter.
Russian winged orbital launch vehicle. All cargo version of MAKS. Air-launched heavy-lift launcher would use an expendable second stage with a payload container. Release conditions: Piggy-back, 275,000 kg, 38.0 m length x 24.0 m wingspan, 900 kph at 9,500 m altitude. Effective velocity gain compared to vertical launch 270 m/s. Payload bay 13.0 m long x 5.0 m diameter.
French tactical ballistic missile.
American sounding rocket. Single stage vehicle.
Mars.
Russian tactical ballistic rocket.
American winged orbital launch vehicle. Early two-stage-to-orbit shuttle study, using storable propellants, Dynasoar-configuration delta wing orbiter and booster.
American orbital launch vehicle. The Martin HATV 1946 design used a single Aerojet engine of unconventional design to achieve single-stage-to-orbit performance.
American orbital launch vehicle. The Martin Marietta Class I SDV would lead to the Shuttle-C, using the shuttle aft fuselage with SSME engines to power a cargo canister into orbit.
Martin Plan C.
Manufacturer's designation for Titan C orbital launch vehicle.
Canadian gun-launched orbital launch vehicle. In 1962-1967 Canada's Gerard Bull led development of the Martlet system for gun-launched access to space. The program was cancelled before the objective of gun launch to orbit was attained.
Canadian sounding rocket. The Martlet One Flight Vehicle was designed in mid-1962 as a first generation test vehicle for the HARP project. The primary role of the Martlet One was to test the fundamental technologies that were to be used in the Martlet Two vehicle. These included the internal ballistics of the 16" L45 smooth-bored gun system, the pusher plate/ laminated plywood sabot system and the ability to receive radio telemetry from a gun launched vehicle in flight.
Canadian sounding rocket. The Martlet 2 series were the primary 16" gun-launched sub-orbital flight vehicles used during the High Altitude Research Program (HARP). Martlet 2's were used to conduct extensive research at altitudes of up to 180 km with some 200 flights being conducted between 1963 and 1967. The very low cost per flight, about $3,000, made it ideal for a wide variety of applications.. Typical mission payloads included chemical ejection to produce an observable atmospheric trail and assorted sensors with multi-channel telemetry.
Canadian sounding rocket. This derivative of the Martlet 2 gun-fired suborbital space probe achieved a higher scientific payload through use of a lighter sabot. 12 were flown before the program was ended.
Canadian gun-launched orbital launch vehicle. The Martlet 2G-1 was the absolute minimum gun-launched satellite vehicle. Conceived when the HARP project was under threat, it was a seven-inch diameter, two-stage solid propellnat vehicle that would be sabot-launched from the HARP 16 inch gun. Its total payload in orbit would have been just two kilogrammes - ideal for today's planned nano-satellites. Unfortunately even this minimum orbital launch vehicle could not be demonstrated before the program was shut down.
Canadian sounding rocket. Single stage, gun-launched vehicle.
Canadian sounding rocket. The Martlet 3A was the first serious attempt to produce a sub-calibre, gun-launched, rocket-assisted, vehicle for the 16 inch gun system. The basic design criteria for the Martlet 3A was to gun launch a vehicle containing a rocket motor that could provide a velocity boost equal to or greater then the initial gun-launch velocity.
The theoretical performance of the Martlet 3A was for an 18 kg payload to be carried to an altitude of some 500 km at gun-launch accelerations of 12-14,000 g's and gun launch velocities in the range of 2100 m/sec (similar to the Martlet 2 series maximum launch parameters).
Canadian sounding rocket. Once the fundamental design flaws of the Martlet 3A vehicle were identified the system was redesigned and a new vehicle, the Martlet 3B, was created.
The Martlet 3B vehicle was similar in design to the 3A vehicle but sported several design changes intended to improve the system performance. The first major change was to replace the aluminium airframe with a alloy steel airframe in the hopes the stronger material would lead to higher mass fractions. Other improvements included the use of a larger diameter rocket motor (increasing the outer diameter to 8 inches / 20 cm) and the use of six fixed fins instead of the 3A's four fins.
Canadian sounding rocket. The Martlet 3D concept was intended to serve as a sub-orbital vehicle capable of lifting heavy payloads to satellite altitudes. The Martlet 3D was simply the first stage of the Martlet 4 vehicle ( Martlet 4A) with the two upper stages and the satellite payload being replaced with a single large payload.
Canadian sounding rocket. The Martlet 3E vehicle was designed to take advantage of the portability of the HARP 7 inch guns. Unlike the big fixed 16 inch guns the 7 inch HARP guns, were portable and could be relocated to conduct launches from a wide variety of sites. It was soon determined that a gun-launched rocket vehicle for the 7 inch gun would have a similar performance to the Martlet 2 glide probe launched from the fixed 16 inch guns. Launch costs would also be about the same.
Canadian gun-launched orbital launch vehicle. The Martlet 4 was ultimate goal of the HARP program - a gun-launched orbital launch vehicle. Two versions were considered: a preliminary version with two solid propellant upper stages, and a later model with two liquid propellant upper stages. Payload of the liquid propellant version would have reached 90 kg. The initial version was in an advanced stage of suborbital flight test when the HARP program was cancelled in 1967.
American intermediate range cruise missile. Glenn L. Martin Co. surface-to-surface cruise missile (Matador / Project MX-771).
German sounding rocket. Maul conceived of using powder rockets to launch film cameras for military reconnaissance in 1901, beginning an 11 year development process.
The MAXUS micrograviy program was a collaboration between Sweden and Germany. The single-stage vehicle developed for the program used a Castor 4B motor, the largest fired from Western Europe.
Ukrainian orbital launch vehicle. New family of modular medium-sized launch vehicles proposed by the Ukraine in 2005. No known development or production funding was forthcoming.
MB.
Brazilian sounding rocket.
Brazilian short range ballistic missile.
Brazilian short range ballistic missile.
Brazilian intermediate range ballistic missile.
MBR.
Russian intercontinental ballistic missile. 'Sealed unit' liquid propellant ICBM proposed by Reshetnev in 1960.
American winged orbital launch vehicle. The McDonnell-Douglas ILRV design featured fold-out wings for improved low-speed lift-to-drag ratio during final descent and landing. All of the vehicle's propellants were moved outside the orbiter into two large hydrogen tanks and two smaller oxygen tanks. The original concept was sized for an 11,340kg, 9.44m x 4.57m payload.
German winged rocketplane. The rocket-powered Messerschmitt Me-163 was the world's first and only operational pure rocket fighter and represented the culmination of Alexander Lippisch's years of research in rocketplanes, tail-less aircraft, and delta wings. As a weapon, the Me-163 had tremendous speed but very limited range. However the concepts developed by Lippisch contributed to the Space Shuttle and Buran orbiters of a quarter century later.
Medium Range Target Vehicle.
Popular Name of ait-2 target missile.
Indian sounding rocket. Related to RH-125.
MER-6.
Department of Defence Designation of Blue Scout ERCS strategic communications missile.
MERA.
Russian sounding rocket. Two-stage small meteorological sounding rocket, consisting of two identical solid rocket motors in tandem, stabilised by fins, topped by a payload dart with instrumentation.
Single stage solid propellant sounding rocket capable of reaching 95 km altitude.
French sounding rocket. Single stage vehicle.
French sounding rocket. Single stage vehicle.
Family of Polish sounding rockets developed by the Polish Aviation Institute for the Polish Hydro-Meteorological institute beginning in 1962.
Polish sounding rocket. Single stage vehicle.
Polish sounding rocket. Larger version of Meteor, capable of taking twice the payload to twice the altitude. Single stage vehicle.
The most powerful Polish rocket ever flown. 2 stage vehicle consisting of 2 x Meteor 1 + 1 x Meteor-2.
Polish sounding rocket. Development of the Meteor-3 began in 1967. The two stage vehicle consisted of two modified Meteor-1 stages in tandem. It was launched from a 12-m rail launcher and could take the 4.5 kg dart payload to 65 km.
Russian intermediate range cruise missile. Development of three variants of this cruise missile was authorised on 9 December 1976. The Meteorit-M strategic version would be deployed from 667M submarines with 12 launchers per boat. The air-launched Meteorit-A would be launched from Tu-95 bombers. The land-based version was designated Meteorit-N. The missile was also sometimes referred to by the code-name Grom. The first test launch, on 20 May 1980, was unsuccessful, as were the next three attempts. The first successful flight did not come until 16 December 1981. The first launch from a 667M submarine took place on 26 December 1983 from the Barents Sea. However all variants were cancelled in 1988 as a result of the INF Treaty.
Meteorit-M.
Launch System of P-750 intermediate range cruise missile.
MGM-1.
Department of Defence Designation of Matador intermediate range cruise missile.
MGM-140.
Department of Defence Designation of ATACMS short range ballistic missile.
MGM-140 Block 1.
Department of Defence Designation of Block 1 short range ballistic missile.
MGM-140 Block 1A.
Department of Defence Designation of Block 1A short range ballistic missile.
MGM-140 Block 2.
Department of Defence Designation of Block 2 short range ballistic missile.
MGM-164.
Department of Defence Designation of ATACMS II short range ballistic missile.
MGM-18A.
Department of Defence Designation of Lacrosse tactical ballistic missile.
American intermediate range cruise missile.
American intermediate range cruise missile.
American intermediate range cruise missile.
MGM-29A.
Department of Defence designation of Sergeant missile.
MGM-31.
Department of Defence designation of Pershing missile.
MGM-31A.
Department of Defence Designation of Pershing 1 intermediate range ballistic missile.
MGM-31B.
Department of Defence Designation of Pershing 1A intermediate range ballistic missile.
MGM-31C.
Department of Defence Designation of Pershing 2 intermediate range ballistic missile.
American intermediate range ballistic missile. Cancelled. Pershing II RR Reduced Range
MGM-5.
Department of Defence designation of Corporal missile.
MGM-52.
Department of Defence designation of Lance missile.
American short range ballistic missile.
American short range ballistic missile. Simplified inertial guided, nuclear or conventional warhead
American short range ballistic missile. First production version.
American short range ballistic missile. Second production version.
MGR-1.
Department of Defence designation of Honest John missile.
American tactical ballistic rocket.
American tactical ballistic rocket. Three different warhead sections were possible: M27, M47 and M-48 with yields 2-20-40 kt. M72 training warhead also used.
MGR-3.
Department of Defence Designation of Little John tactical ballistic rocket.
Swiss surface-to-air missile. The dual-thrust (45 kN then 22 kN) solid propellant motor providing a total impulse of 900 kN-sec.
Swiss sounding rocket. Sounding rocket using the motor developed for the Micon surface-to-air missile. The Cuckoo was used as a booster on the final two tests.
American sounding rocket. Single stage vehicle.
Midgetman.
Popular Name of SICBM intercontinental ballistic missile.
American intercontinental ballistic missile. Early 1960's two-stage version of Minuteman.
Russian sled-launched winged orbital launch vehicle. Sled-launched single stage to orbit vehicle with air-breathing propulsion to Mach 5 (subsonic combustion). The sled would accelerate the launch vehicle to Mach 0.8. Propellants wer slush hydrogen and liquid oxygen. The vehicle would have a 3000 km cross-range on re-entry.
Russian air-launched orbital launch vehicle. Orbital launch vehicle air-launched from a MiG-31 fighter.
Russian winged orbital launch vehicle. Turbojet/ramjet-powered two stage to orbit horizontal takeoff / horizontal landing vehicle. Mach 6 stage separation. The orbiter had a 2000 km cross-range capability with landing on airfields with runways of 3500 m length or more.
Mighty Mouse.
Popular Name of FFAR air-to-air rocket.
Russian intermediate range cruise missile. The 301 was designed as a military bomber, with a Mach 4 / 4,250 km/hr cruise capability at 25,000 to 27,000 m altitude. It was equipped with two turboramjets, had a gross takeoff mass of 80 tonnes, of which half was fuel. It may be related to the first stage of the MIGAKS two-stage vehicle.
American SSTO VTOVL orbital launch vehicle. General Dynamics Space Systems Division proposal for the 1990 SDIO competition was a VTOL SSTO named Millennium Express. The final vehicle was a 15 degree cone with a 20%-length Rocketdyne aerospike engine. Payload was specified as 4500 kg into a polar low earth orbit. The Express could carry on its nose a payload module, a small Apollo-type two-crew seperable manned capsule, or a six-crew module that remained attached to the vehicle for recovery. The similar Douglas Delta Clipper was selected by the USAF for further development.
MIM-104.
Department of Defence designation of Patriot missile.
MIM-104A.
Department of Defence Designation of PAC-3 anti-ballistic missile.
American surface-to-air missile. Command-guided / semi-active radar-homing. Range 160 km in PAC-1 with software changes. PAC-2 modification with bigger warhead.
MIM-14.
Department of Defence designation of Nike Hercules missile.
American surface-to-air missile. W31 Mod 2 warhead. Two different warhead sections were possible: M22 and M97, with yields of 1-20-40 kt.
American surface-to-air missile.
MIM-23.
Department of Defence designation of Hawk missile.
American surface-to-air missile.
American surface-to-air missile.
MIM-3A.
Department of Defence Designation of Nike Ajax surface-to-air missile.
American all-solid orbital launch vehicle. Minotaur was developed for the US Air Force's Orbital/Suborbital Program (OSP) as a low-cost, four-stage Space Launch Vehicle (SLV) using a combination of government-supplied surplus Minuteman II ICBM motors and proven Orbital space launch technologies. The Minotaur 4 version used surplus Peacekeeper rocket stages.
American all-solid orbital launch vehicle. Orbital launch vehicle consisting of a surplus Minuteman M55A1 first stage, Minuteman SR19 second stage, and new Orion 50XL third stage, Orion 38 fourth stage, and optional HAPS fifth stage for velocity trim and multiple payload deployment. Payload 580 kg to an 185 km, 28.5 degree orbit from Cape Canaveral; 310 kg to a 740 km sun-synchronous orbit from Vandenberg.
American all-solid orbital launch vehicle. Suborbital target vehicle consisting of an M55A1 first stage, SR19 second stage, and M57 third stage - essentially a Minuteman II with Orbital guidance and control systems. 440 kg payload on a 6700 km suborbital trajectory.
Orbital launch vehicle using surplus Peacekeeper rocket stages: an SR-118 first stage, SR-119 second stage, SR-120 third stage, new Orion 38 fourth stage and optional HAPS fifth stage. Payload 1720 kg to an 185 km, 28.5 degree orbit from Cape Canaveral; 1000 kg to a 740 km sun-synchronous orbit from Vandenberg.
American intercontinental ballistic missile. Mainstay of the US deterrent. 1,000 Minuteman silos were built in the early 1960's, and the missile was to remain in service to the mid-21st Century. As versions were retired and updated, they provided a plentiful source of surplus rocket motors for other projects.
Minuteman 1.
Popular Name of LGM-30C intercontinental ballistic missile.
American intercontinental ballistic missile. Initial production version, 3 stage vehicle. The Minuteman IA used exclusively the Mk.5 RV with the W59 (1 MT) warhead.
American intercontinental ballistic missile. Single stage test vehicle.
American intercontinental ballistic missile. Full production version. Minuteman IB used the Mk.5 RV with the W59 (1 MT), the Mk.11 with the W56 (1.2 MT) and the Mk.11A with the W56 as well.
American intercontinental ballistic missile. US ICBM. 3 stage vehicle. The LGM-30F Minuteman II used the W56 warhead exclusively with either the Mk. 11B or Mk. 11C re-entry vehicle.
American four-stage solid-propellant intercontinental ballistic missile. In the 21st Century, the sole remaining US ICBM.
American strategic communications missile.
Minuteman II.
Alternate designation of Midgetman missile.
Mirak - a 'Minimum Rocket' - was conceived by Rudolf Nebel to demonstrate the practicality of the liquid rocket, using the thrust chamber developed for the abandoned Oberth rocket. Mirak was realised not by Nebel, but talented engineer Riedel. It flew over 100 times in 1931-1932 and convinced the German Army of the practicality of the rocket as a weapon of war.
Mk. 1.
Standard RV of Jupiter intermediate range ballistic missile.
Mk. 11B or Mk. 11C.
Standard RV of Minuteman 2 intercontinental ballistic missile.
Mk. 12A.
Standard RV of Minuteman 3 and Peacekeeper intercontinental ballistic missiles.
Mk. 2.
Standard RV of Thor intermediate range ballistic missile.
Mk. 2/3.
Standard RV of Atlas C test vehicle.
Mk. 20A.
Standard RV of Polaris A1 missile.
Mk. 20B.
Standard RV of Polaris A2 missile.
Mk. 3.
Standard RV of Titan 1 intercontinental ballistic missile.
Mk. 4.
Mk. 400.
Standard RV of Trident C-4 intercontinental ballistic missile.
Mk. 5.
Standard RV of Minuteman 1A intercontinental ballistic missile.
Mk. 5, Mk.11, or Mk.11A.
Standard RV of Minuteman 1B intercontinental ballistic missile.
Mk. 500.
Standard RV of Trident D-5 intercontinental ballistic missile.
Mk. 6.
Standard RV of Titan 2 intercontinental ballistic missile.
Mk.100.
Standard RV of Polaris A3 missile.
Mk.300.
Standard RV of Poseidon submarine-launched ballistic missile.
MKR.
Russian intercontinental cruise missile. A wide range of MKR (intercontinental winged missiles) were studied in 1957-1960 in accordance with a decree of the General Staff. The trade-off studies encompassed long-range air-breathing aircraft, winged rockets, and aircraft launchers for air-breathing missiles.
MLLV.
American SSTO VTOVL orbital launch vehicle. Boeing study, 1969, for Saturn follow-on. Plug nozzle, single-stage-to-orbit launch vehicle could itself put 1 million pounds payload into orbit. By addition of up to 12 260 inch solid motors up to 3.5 million pounds payload into orbit with a single launch.
MLRS.
American tactical ballistic rocket. Multiple Launch Rocket System. US Army assault weapon.
American tactical ballistic rocket. In production.
MLRS Extended Range.
Alternate Designation of MLRS ER tactical ballistic rocket.
Russian sounding rocket. Soviet solid propellant sounding rocket, capable of lofting 5 to 11 kg to 60 km altitude. Launch mass 130 kg, 9 seconds burn time. Nose ejects at apogee. Flown in both conical nose and boosted dart configurations.
American surface-to-surface ballistic missile, development started in 1962. Program cancelled in 1964.
Engineer Ernst Mohr of Wuppertal, under the auspices of the German Rocket Society, developed a sounding rocket that was designed to reach altitudes of 50 km. A solid rocket motor with 7800 kgf would take the separable payload section to a speed of 1200 m/s. The booster had a diameter of 0.30 m, a length of 1.7 m, a total mass of 135 kg including 75 kg of solid propellant. The payload dart was 56 mm in diameter, 1.25 m long, and had a total mass of 15 kg.
Russian orbital launch vehicle. Four stage derivative of the R-7 ICBM developed on a crash-program basis in 1960 for Soviet lunar and planetary deep space probe missions. The third stage found later use in the Voskhod and Soyuz launchers. By the 1970's mature versions of the launch vehicle were used almost entirely for launch of Molniya communications satellites and Oko missile early warning spacecraft into elliptical, 12-hour earth orbits.
Russian orbital launch vehicle. Molniya adaptation for launch of E-6 lunar probes.
Russian orbital launch vehicle. The Molniya 8K78L was designed by Korolev's design bureau for launching a manned spacecraft on a flyby of the Moon and return to earth. To achieve this it would have used Lox/LH2 engines in the third and fourth stages. Preliminary design was completed on 8 July 1962, but such technology was years away in the Soviet Union and the project was not pursued further.
Russian orbital launch vehicle. Improved Molniya, in variants with Blocks ML, 2BL, or SO-L third stages according to payload.
Russian orbital launch vehicle. Improved Molniya variant with Blok-2BL upper stage for placement of Oko early-warning satellites into Molniya-class orbits with apogees of 38,000 km.
Russian orbital launch vehicle. Improved Molniya variant with Blok-ML upper stage for placement of communications satellites into Molniya-class orbits with apogees of 38,500 km.
Russian orbital launch vehicle. Improved Molniya variant with Blok SO-L upper stage for placement of Prognoz-class satellites in orbits with apogees of 200,000 km.
Molniya-M.
Alternate designation for Molniya 8K78M orbital launch vehicle.
Molodets.
Popular Name of RT-23U 15Zh60 and RT-23U 15Zh61 intercontinental ballistic missiles.
French low-cost, three-stage, solid-propellant sounding rocket developed in France in the 1950's in support of the International Geophysical Year.
French sounding rocket.
French sounding rocket.
Russian orbital launch vehicle. During UR-500 design studies, two variants of the first stage were considered: polyblock and monoblock. The monoblock approach was that the first stage be assembled from two separate modules with the same diameter: an upper oxidiser module and a lower fuel and engine block. In assembly trials of this design it proved difficult, because of the height of the first stage, to obtain access to the upper stages and payload atop the rocket. Although there was a payload advantage compared to the more compact polyblock design, this was relatively small and outweighed by the operational difficulties.
American surface-to-air drone. Drone version.
MR.
Russian intercontinental ballistic missile. Korolev studied this Multimodular Rocket (MR), based on stages already designed for the 8K74 and 8K77 (R-7 and R-9) missiles. As was the case of the 8K74, work on the design was stopped in September 1961.
Russian sounding rocket. The MR-12 sounding rocket was developed by the Soviet Union as a modern replacement for the MR-1 Meteo. It was a single stage solid rocket with a 170 kg payload. Payload section 1.55 m long, 0.445 m in diameter.
Russian sounding rocket. Upper atmosphere Soviet sounding rocket, improved version of MR-12, but capable of lofting 135 kg to 250 km altitude.
Russian sounding rocket. Version of the MR-20.
MRTV.
Manufacturer's designation for ait-2 target missile.
Ukrainian intercontinental ballistic missile. The Yangel MR-UR-100 was designed as a replacement for Chelomei's UR-100 at the end of its 10 year storage life. Although it could be installed in the same silos, it was 50% heavier. The competing design of Chelomei, the UR-100N, was also put into production when the Soviet hierarchy deadlocked and could not pick one design over the other.
MR-UR-100U.
Manufacturer's designation for MR-UR-100U 15A16 intercontinental ballistic missile.
Ukrainian intercontinental ballistic missile. Improved version of the MR-UR-100U loaded into the super-hardened 15P715U universal silo, with a modernised guidance system with better reliability and accuracy.
MR-UR-100UTTKh.
Alternate Designation of MR-UR-100U 15A16 intercontinental ballistic missile.
MRV.
MSBS.
French intermediate range ballistic missile.
French intermediate range ballistic missile.
French intermediate range ballistic missile.
French intermediate range ballistic missile.
French intermediate range ballistic missile. Two stage vehicle consisting of 1 x SEP 901 + 1 x Rita I
French intermediate range ballistic missile.
French intermediate range ballistic missile. Two stage vehicle consisting of 1 x SEP 904 + 1 x Rita II
French intermediate range ballistic missile.
French intermediate range ballistic missile. Submarine launched; MRV. Operational. 3 stage vehicle.
French intermediate range ballistic missile. Improved M-4.
French intercontinental ballistic missile.
French intercontinental ballistic missile.
Japanese sounding rocket. The MT-135 was a small single-stage sounding rocket designed to collect data on the middle atmosphere, such as ozone layer depletion.
Japanese sounding rocket.
Japanese sounding rocket. In 1969 the MT-135P was developed; featuring a parachute-equipped recoverable motor case for maritime safety.
Mu.
The Japanese Mu launcher series provided a flexible all-solid propellant launch vehicle for access to space. It was the first Japanese launch vehicle designed from the start as an orbital launch vehicle.
Mu-1.
Japanese test vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-20 + 1 x M-30 + 1 x M-40
Mu-3.
The Japanese Mu launcher series provided a flexible all-solid propellant launch vehicle for access to space.
Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-22TVC + 1 x M-3A
Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-20 + 1 x M-30 + 1 x M-40
Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-13 + 1 x M-22TVC + 1 x M-3A + 1 x KM-H
Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 8 x SB-310 + 1 x M-13TVC + 1 x M-22TVC + 1 x M-3A
Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 2 x SB-735 + 1 x M-13 + 1 x M-23 + 1 x M-3B
Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-20 + 1 x M-30 + 1 x M-40
The British Aircraft Corporation "Multi-Unit Space Transport And Recovery Device" design of 1964-1965 was a winged two-stage-to-orbit reuseable space shuttle using the 'triamese' concept. The three components of the design were lifting bodies with a configuration similar to the American HL-10 vehicle. BAC sought to reduce development cost by use of two boosters nearly identical to the orbiter vehicle.
M-V.
All-solid Japanese satellite launch vehicle.
Japanese all-solid orbital launch vehicle. Four stage version consisting of 1 x M-14 + 1 x M-24 + 1 x M-34 + 1 x KM-V1
MVKS.
Alternate designation for VKS ssto winged orbital launch vehicle.
MX.
Alternate designation for Peacekeeper intercontinental ballistic missile.
American orbital launch vehicle. The September 1951 design for the Atlas used seven main engines to hurl the 3600 kg nuclear warhead over a 9300 km range. CEP was 1850 m.
MX-770.
Alternate designation for Navaho SSM-A-2 intermediate range cruise missile.
MX-771.
Alternate designation for Matador intermediate range cruise missile.
American test vehicle. Project MX-774 inaugurated by AAF with Consolidated-Vultee to study rocket capabilities with an ICBM as a final objective. Limited funds permitted a few test launches. These rockets demonstrated technologies that woud later be applied to the Atlas.
American intercontinental cruise missile.
MX-776.
Alternate designation for Rascal air-to-surface missile.
N.
N
N1.
The N1 launch vehicle, developed by Russia in the 1960's, was to be the Soviet Union's counterpart to the Saturn V. The largest of a family of launch vehicles that were to replace the ICBM-derived launchers then in use, the N series was to launch Soviet cosmonauts to the moon, Mars, and huge space stations into orbit. In comparison to Saturn, the project was started late, starved of funds and priority, and dogged by political and technical struggles between the chief designers Korolev, Glushko, and Chelomei. The end result was four launch failures and cancellation of the project five years after Apollo landed on the moon. Not only did a Soviet cosmonaut never land on the moon, but the Soviet Union even denied that the huge project ever existed.
N-1.
Manufacturer's designation for N1 heavy-lift orbital launch vehicle.
N-1 11A52.
Alternate designation for N1 heavy-lift orbital launch vehicle.
Russian heavy-lift orbital launch vehicle. Final configuration of the N1 at the time of development go-ahead in 1962. The 75 tonne payload was to consist of the Raskat dispenser, which would have delivered 17 multi-megaton nuclear warheads, essentially destroying the United States in a single launch. The design also supported the OS-1 heavy space station and TMK manned Mars flyby requirements - as opposed to any manned lunar landing project.
Russian heavy-lift orbital launch vehicle. The N1 launch vehicle for the N1-L3 lunar landing mission as described in the draft project of 1964. Design requirement for the single-launch lunar-orbit-rendezvous lunar landing was 2750 tonnes liftoff mass and 95 tonnes low earth orbit payload. The actual N1 that flew in 1969 to 1972 had lighter first and third stages, but never demonstrated a full fuel load using superchilled propellants as planned in the draft project..
Russian heavy-lift orbital launch vehicle. The N1 launch vehicle, developed by Russia in the 1960's, was to be the Soviet Union's counterpart to the Saturn V. The largest of a family of launch vehicles that were to replace the ICBM-derived launchers then in use, the N series was to launch Soviet cosmonauts to the moon, Mars, and huge space stations into orbit. In comparison to Saturn, the project was started late, starved of funds and priority, and dogged by political and technical struggles between the chief designers Korolev, Glushko, and Chelomei. The end result was four launch failures and cancellation of the project five years after Apollo landed on the moon. Not only did a Soviet cosmonaut never land on the moon, but the Soviet Union even denied that the huge project ever existed.
Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle.
Russian nuclear orbital launch vehicle. A version of the N1 with a nuclear upper stage was studied by Korolev in 1963. It was concluded that the optimum design would allow a single N1 to launch a direct manned lunar landing and return. However for manned Mars missions, a nuclear electric engine was found to be much more efficient. This essentially killed further consideration of thermal nuclear upper stages within the bureau.
Russian nuclear orbital launch vehicle. A variant of the first alternative considered in the 1963 nuclear N1 study. This was a 'high thrust' version of the Type A engine - apparently with higher propellant rate, lower specific impulse, and lower engine weight. Due to the very low density of the enormous liquid hydrogen upper stages, these immense vehicles would have been very ungainly (and had interesting stress problems during ascent!)
Russian nuclear orbital launch vehicle. Second primary alternative considered for the 1963 nuclear N1 study. The immense liquid hydrogen tank of the second nuclear stage would have dwarfed the N1 first stage mounted below it in the shadows. The extremely poor thrust to weight ratio of the Type V engine design compared to that of the Type A remains unexplained.
Russian nuclear orbital launch vehicle. N1 with nuclear upper stage. This variant of the Type V nuclear engine used a very heavy radiation shield to protect the crew of any manned spacecraft payload.
N11.
Russian heavy-lift orbital launch vehicle. It was originally planned the N1 would form the basis of a family of launch vehicles that could replace existing ICBM-derived boosters. The N11 would use the second, third, and fourth stages of the N1. This would give it a lift-off mass of 700 tonnes and a 20 tonne payload into low earth orbit. It could replace Chelomei's Proton launch vehicle in the medium-lift role.
Russian heavy-lift orbital launch vehicle. A military variant of the N-11 which would use a powerful third stage, probably derived from the first stage of the 8K713 GR-1, to put up to 24 tonnes in low earth orbit. This was a competitor with Chelomei's UR-500K, which was selected instead for the heavy military payload mission.
N111.
Russian heavy-lift orbital launch vehicle. It was originally planned the N1 would form the basis of a family of launch vehicles that could replace existing ICBM-derived boosters. The N111 would use the third and fourth stages of the N1, and the second stage of Korolev's R-9 ICBM. This would result in a lift-off mass of 200 tonnes and a five tonne payload. It could replace the R-7 derived boosters (Vostok and Soyuz) in this payload category.
Russian orbital missile. This 1962 project was designed by Korolev's OKB as a competitor to Chelomei's UR-500 against the military GR-2 (Global Rocket 2) requirement. The N-11GR was an adaptation of the basic N-11, derived from the second and third stages of the N1 heavy booster. The GR-2 was to be a kind of enormous multiple-warhead FOBS (fractional orbit bombing system). Surrounding the top of the second stage of the rocket, like bullets in an enormous revolver, were six final stages derived from the 8K713 GR-1 last stage. Each stage had a 1,500 kg nuclear warhead.
N1F.
Russian heavy-lift orbital launch vehicle. The N1F would have been the definitive flight version of the N1, incorporating all changes resulting from the four flight tests of the vehicle, including the new Kuznetsov engines and 10% greater liftoff mass by using superchilled propellants in all stages. N1 8L would have been the first N1F configuration flight, with launch planned in the third quarter of 1975 at the time the project was cancelled.
Russian heavy-lift orbital launch vehicle. The final more modest version of the N1F replaced the fourth and fifth stages of the N1 with the single liquid oxygen/liquid hydrogen Block Sr stage. Development of the Sr stage was from May 1971 until cancellation of the N1 project in May 1974.
Russian heavy-lift orbital launch vehicle. The N1M was found to be too ambitious. The N1F of 1968 was instead pencilled in to be the first Soviet launch vehicle to use liquid oxygen/liquid hydrogen high energy cyrogenic propellants. The N1F would have only used the Block S and Block R fourth and fifth stages in place of the N1's Block G and Block D.
N1M.
Russian heavy-lift orbital launch vehicle. The N1M was to be the first Soviet launch vehicle to use liquid oxygen/liquid hydrogen high energy cyrogenic propellants. It was designed to launch payloads in support of the LEK lunar expeditions (two cosmonauts on the surface), the DLB (long-duration lunar base), and heavy unmanned satellites into geosynchronous and interplanetary trajectories. As originally conceived, the advanced propellants would be used in all upper stages. However due to delays in Kuznetsov development of a 200 tonne thrust Lox/LH2 engine, the final version used an N1 first stage, with a Block V-III second stage, and Blocks S and R third and fourth stages.
Russian heavy-lift orbital launch vehicle. Ultimate derivative of N1. Single-stage-to-orbit vehicle based on N1 Block A. Propellants changed to LH2/LOX, 16 x modified NK-33 engines + 4 Liquid Air Cycle Engine Liquid Air/LH2 boosters. All figures estimated based on tank volume of Block A and delivery of 90,000 kg payload to 450 km / 97.5 degree MKBS orbit. Briefly described in RKK Energia official history and in some detail in Peter James'
N-2.
Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle.
American orbital launch vehicle. Three stage version consisting of 9 x Castor 2 + 1 x ELT Thor N + 1 x AJ10-118FJ
NA-704.
Manufacturer's designation for Navaho SSM-A-2 intermediate range cruise missile.
North American's HATV proposal was an ogival single-stage-to-orbit vehicle, with tanks made from 18-8 stainless steel. In common with other HATV designs, the tanks had to be pressurized to maintain rigidity.
NASA awarded a "Reusable Ten Ton Orbital Carrier Vehicle" contract worth $342,000 to North American Aviation. The final concept from 1963 was quite similar to Lockheed's System III design. The launch capability was 11,340 kg (25,000 lb) and the standard payload would have consisted of a small lenticular 12-man orbital transfer vehicle spaceplane for space station logistics and crew transfer.
NAL.
Japanese test vehicle. Single stage vehicles.
Japanese test vehicle. Single stage vehicle.
Japanese test vehicle. Single stage vehicle.
Japanese test vehicle. Single stage vehicle.
Japanese test vehicle.
American low cost orbital launch vehicle. Two-stage, reusable, liquid oxygen/ethane propellant launch vehicle using aerospike engine technology and capable of delivering 10 kilograms to a 250-kilometer polar orbit. The NLV would provide low-cost, dedicated launch services to universities and other research organizations that traditionally depend on secondary payload opportunities to access space
National Aerospace Plane.
Popular Name of X-30 ssto winged orbital launch vehicle.
National Launch System.
As part of its effort to develop what started out as an American version of the A9 boost-glide rocket, North American Aviation built seven Nativ subscale technology demonstrators.
The Navaho intercontinental cruise missile project was begun just after World War II, at a time when the US Army Air Force considered ballistic missiles to be technically impractical. The Navaho required a large liquid propellant rocket engine to get its Mach 3 ramjet up to ignition speed. This engine, derived with German assistance from that of the V-2, provided the basis for the rockets that would later take Americans into space.
It turned out that mastering the guidance and materials technology needed for a Mach 3 cruise air vehicle was actually more difficult than for a Mach 22 ballistic missile. In the end, the Redstone, Thor, Jupiter, and Atlas rockets were flying before their equivalent-range Navaho counterparts. However the Navaho program provided the engine technology that allowed the US to develop these ballistic missiles rapidly and catch up with the Russians. Navaho also developed chem-milling fuel tank fabrication techniques, inertial and stellar navigation, and a host of other technologies used in later space vehicles. It put North American Aviation, and its Rocketdyne Division, in a leading position that allowed them to capture the prime contracts for the X-15, Apollo, and Space Shuttle projects, thereby dominating American manned spaceflight for the next seventy years.
American intermediate range cruise missile. The Navaho G-26 was a 2/3 scale test version of the operational Navaho G-38. The Navaho program was cancelled on 13 July 1957, but already-built G-26 test missiles were flown to the end of 1958.
American intercontinental cruise missile. The intercontinental-range Navaho G-38 was the ultimate development of the German A-9/A-10 concept. At the time the Navaho program was cancelled on 13 July 1957 missiles were in fabrication with first flight test planned by the end of 1958.
Navaho I.
Popular Name of Navaho SSM-A-2 intermediate range cruise missile.
Navaho II.
Popular Name of Navaho G-26 intermediate range cruise missile.
Navaho II SM-64.
Alternate designation for Navaho G-26 intermediate range cruise missile.
Navaho III.
Popular Name of Navaho G-38 intercontinental cruise missile.
American intermediate range cruise missile. The first version of the Navaho developed in 1946-1950 was a Mach-3 ramjet vehicle with an integral rocket booster. Completion of the vehicle was cancelled in 1950 but the engine was used to power the Redstone ballistic missile.
American intermediate range cruise missile. Reusable, conventional airfield takeoff-and-landing aerodynamic test vehicle for Navaho missile.
North American proposed several methods of taking the X-15 spaceplane to higher velocities and altitudes. One of these involved the use of one to three Navaho booster rockets, which could even place the X-15 into orbit. This incremental approach to manned spaceflight was not pursued - the Mercury and X-20 Dynasoar programs were favored instead.
American sea-launched orbital launch vehicle. Sea-launched stage-and-a-half liquid oxygen / liquid natural gas orbital launch vehicle for passengers or payloads of up to 4.5 tonnes.
American nuclear-powered orbital launch vehicle. Version of 1960's nuclear fission engine proposed in 1990's.
New Launch System.
American VTOVL test vehicle.
British gun-launched orbital launch vehicle. Isaac Newton discussed the use of a cannon to attain orbit in 1687 in his Principia Mathematica - the very book that defined classical physics and provided the theoretical basis for space travel and rocketry. Newton used the following 'thought experiment' to explain the principle of orbits around the earth (see illustration):
Imagine a mountain so high that its peak is above the atmosphere of the earth. Imagine on top of that mountain a cannon, that fires horizontally. As more and more charge is used with each shot, the speed of the cannonball will be grater, and the projectile will impact the ground farther and farther from the mountain. Finally, at a certain speed, the cannonball will not hit the ground at all. It will fall toward the circular earth just as fast as the earth curves away from it. In the absence of drag from the atmosphere, it will continue forever in an orbit around the earth.
NEXT.
American orbital launch vehicle. Conceptual next generation Delta booster beyond Delta IV Heavy, equalling Saturn V of the 1960's in payload capability. The booster would use two parallel 7-m-diameter booster stages, a notional RS-XXX Lox/LH2 rocket motor, and a 7 m diameter upper stage and fairing. Payload fairings of 7 m diameter could be accomodated. Introduction would require new launch pads and booster assembly infrastructure, and a new factory to handle the larger-diameter tooling.
American SSTO VTOVL orbital launch vehicle. Early 1960's recoverable launch vehicle proposed by Krafft Ehricke at General Dynamics. Perhaps the largest conventionally-powered launch vehicle ever conceived, it was designed to deliver 900 tonnes to low earth orbit.
Russian heavy-lift orbital launch vehicle. The N-IF would be the first follow-on version with increased performance. The first stage engines would be increased in thrust from an average of 150 tonnes to 175 tonnes, and those in the second stage from 150 tonnes to 200 tonnes. The second and third stages would be substantially enlarged.
Russian heavy-lift orbital launch vehicle. Then N-IFV-III would add the Block V-III cryogenic third stage to the first and second stages of the N-IF.
Russian heavy-lift orbital launch vehicle. N-IFV-II, III would use only the first stage from the N-1F, and use new cryogenic second and third stages. This cryogenic second stage seems not to have been pursued beyond the study phase.
NII-111 MSM.
Standard warhead of Variant S submarine-launched ballistic missile.
Nike.
American sounding rocket. Single stage vehicles consisting first of just the Nike booster were initially fired in the course of development of the Nike-Ajax surface-to-air missile. Later it was used occasionally as a sounding rocket, but much more often as the boost stage of a multi-stage sounding rocket.
American surface-to-air missile. Two stage vehicle consisting of 1 x Nike + 1 x Ajax
American sounding rocket. The most popular sounding rocket introduced during the early 1960's was this two-stage, solid-propellant vehicle consisting of a Nike booster and Apache upper stage.
American sounding rocket. Rail-launched vehicle consisting of an Asp plus a Nike booster. This product of the Cooper Development Corporation was designed to lift 27 kg to 260 km. An improved version, the Aspan 300, was also developed.The Nike-Asp was sometimes ship-launched.
American sounding rocket. Two stage vehicle sounding rocket consisting of a Nike booster together with a Cajun upper stage. Aside from the Soviet MMR-06, the Nike-Cajun was the most often launched sounding rocket. The Cajun motor was developed for NASA in the 1950's by Thiokol, providing a more modern but still affordable replacement for the World War II-era Deacon.
American test vehicle. Two-stage rocket using surplus Nike boosters and Deacon sounding rocket upper stage. The combination was much cheaper than Aerobee, and unlike Rockoon could be launched from fixed launchers in two and a half hours. It was used for 'falling sphere' air density studies, atmospheric soundings, and for heat transfer studies launched from NACA Wallops Island.
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x Hawk
Nike Hercules.
Popular Name of MIM-14A surface-to-air missile.
American surface-to-air missile. Two stage vehicle consisting of 1 x Hercules Booster + 1 x TX-30
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x Hydac
American sounding rocket. Aerojet developed the Nike-Iroquois (also called Niro) to fulfill a US Air Force requirement for a low-cost sounding rocket with roll control and high structural strength.
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x Javelin
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x Javelin 3
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x Malemute
American sounding rocket. 2-4 stage vehicle consisting of 1 x Nike + 1 x Nike + upper stages.
American sounding rocket.
Three stage vehicle consisting of 1 x Nike + 1 x Nike + 1 x Deacon
American test vehicle. Three stage vehicle consisting of 1 x Nike + 1 x Nike + 1 x HPAG
American test vehicle. Three stage vehicle consisting of 1 x Nike + 1 x Nike + 1 x T-40
American test vehicle. Four stage vehicle consisting of 1 x Nike + 1 x Nike + 3 x Deacon + 1 x T-40
American sounding rocket. Two stage vehicle. Payload 68 kg to 190 km or 204 kg to 90 km. The Nike motor had three equally spaced unmodified Ajax fins, and the Orion motor had four fins on the aft end arranged in a cruciform configuration to provide stability. The first stage Nike booster had an action time of 3.2 seconds. The second stage ignited 9 seconds after liftoff and had an action time of 32 seconds. Capability 68 kg payload to 190 kilometers or a 204 kg payload to 90 kilometers when launched from sea level at an 85 degree launch angle.
American sounding rocket.
American test vehicle. Two stage vehicle consisting of 1 x Nike + 1 x Recruit
American sounding rocket.
American test vehicle. Three stage vehicle consisting of 1 x Nike + 1 x T-40 + 1 x T-55
Four stage vehicle consisting of 1 x Nike + 1 x Nike + 1 x T-40 + 1 x T-55
American sounding rocket. Two stage vehicle consisting of a Nike booster and Tomahawk upper stage. Payload 45 kg to 370 km or 115 kg to 215 km.
American sounding rocket. Two stage vehicle consisting of 1 x Nike + 1 x Viper I
American sounding rocket.
American anti-ballistic missile. First anti-ballistic missile tested by US. Protoypes were deployed operationally from the mid-Pacific test base as nuclear-tipped ASAT missiles. Cancelled 1966; replaced by the Spartan missile.
American anti-ballistic missile. Three stage vehicle consisting of 1 x TX-135 + 1 x TX-238 + 1 x TX-239
American anti-ballistic missile. Two stage vehicle consisting of 1 x TX-135 + 1 x Zeus A
Nike-Black Brant.
Alternate Designation of Black Brant 8 sounding rocket.
Nike-Zeus.
Popular Name of Nike Zeus anti-ballistic missile.
Russian heavy-lift orbital launch vehicle. The N-IM would mark an tremendous increase in vehicle size and was the ultimate pure liquid oxygen/kerosene version considered. The first stage engines would be increased to 250 tonnes thrust, without reducing reliability, through use of higher engine chamber pressure. Propellant load in the first stage would be almost doubled. Second stage engine thrust would increase to 280 tonnes each and the second and third stages again enlarged.
Russian heavy-lift orbital launch vehicle. Then N-IMV-III would add the Block V-III cryogenic third stage to the first and second stages of the N-IM. This provided the second-highest performance of the variations considered and would certainly have been cheaper than the N-IFV-II, III.
Russian heavy-lift orbital launch vehicle. N-IMV-II, III was the ultimate conventionally-powered N1 ever considered. It paired the monster N-1M first stage with new cryogenic second and third stages. Both liftoff thrust and payload of this vehicle would have been double that of the American Saturn V.
N-IU.
Russian heavy-lift orbital launch vehicle. The N-IU would be the initial production version of the N1 following the mad rush to make the lunar landings. It would have essentially the same payload but would be substantially re-engineered for sharply improved reliability, most notably with autonomously operating engines. It is interesting to note that four years before the disastorous first flight Korolev already foresaw the potential engine problems that would be the downfall of the project.
Russian heavy-lift orbital launch vehicle. The N-IUV-III would replace the N-IU's conventional third stage with a LOX/LH2 cryogenic third stage. This was seen at the time as the first step in exploitation of cryogenic technology in Russia. Although pursued for some time, this large stage never went into development. The more modestly-sized Block R, Block S, and Block SR instead were put into development in the early 1970's.
NLS.
American heavy-lift orbital launch vehicle. New (or National) Launch System (NLS) joint NASA/USAF studies began in 1989, following the demise of the ALS. They proposed development of a family of launch vehicles using a new STME engine to replace the existing ‘high cost' boosters derived from 1950's missile designs. The $12 billion nonrecurring cost was nearly that estimated for ALS, and this cost could not be recouped at projected launch rates. NLS was terminated in 1991.
American heavy-lift orbital launch vehicle. NLS Heavy Lift Version. Lower cost expendable launch vehicle studied by NASA/USAF in late 1980's.
North Korean intermediate range ballistic missile. Single stage vehicle, basis for Iranian Shahab 3 and Pakistani Ghauri.
Russian winged orbital launch vehicle. Semi-reusable vertically launched two-stage-to-orbit vehicle. The flight profile featured a reusable flyback booster launched from a modular launch platform, an expendable second stage with a reusable orbiter that would have landed vertically. Development cost estimated at $13 billion.
North American Air Augmented VTOVL.
North American Aviation's air-augmented vertical takeoff & landing single-stage-to-orbit RLV from 1963 would have used external burning ramjets which, according to preliminary studies would reduce the gross liftoff mass of a VTVL SSTO by up to 30%.
American test vehicle. Two stage vehicle consisting of 1 x NOTS 401A + 1 x Sandhawk
Nova.
American heavy-lift orbital launch vehicle. Nova was NASA's ultimate launch vehicle, studied intently from 1959 to 1962. Originally conceived to allow a direct manned landing on the moon, in its final iteration it was to put a million-pound payload into low earth orbit to support manned Mars expeditions. It was abandoned in NASA advanced mission planning thereafter in favor of growth versions of the Saturn V.
American heavy-lift orbital launch vehicle. Earliest NASA Nova design, using only 4 F-1's, capability less than later Saturn designs.
American heavy-lift orbital launch vehicle. NASA Nova design using a cluster of 4 x 240 inch solid motors used as first stage; upper stages as Nova 7S and 8L.
American heavy-lift orbital launch vehicle. NASA Nova design using segmented solid motors in first and second stages. Five six segment motors in first stage; four four segment motors in second stage, equivalent to 9 x F-1 first stage and 4 x F-1 second stage.
American heavy-lift orbital launch vehicle. NASA Nova design using a cluster of 7 x 160 inch solid motors used as first stage; upper stages as Nova 4S and 8L.
American heavy-lift orbital launch vehicle. Most capable NASA Nova design, studied in June 1960 just prior to selection of Saturn for moon landing. Used a three stage configuration of eight F-1 engines in stage 1, two M-1 engines in stage 2, and one J-2 engine in stage 3. Similar to the Saturn C-8 except in the use of M-1 engines. Unlike other modular Nova designs of the time, this one had the unitary stage construction of Saturn.
American heavy-lift orbital launch vehicle. NASA Nova concept where first two stages use short Nova building blocks with 2 F-1's in each block. Four used in stage 1, one in stage 2. Typical of early Nova designs with F-1's in both first and second stages.
American heavy-lift orbital launch vehicle. NASA Nova design using clustered small diameter tanks; 9 x F-1 first stage and 4 x F-1 second stage; compared with solid Nova using five six segment solid motors in first stage and four four segment motors in second stage.
American heavy-lift orbital launch vehicle. Convair/Ehricke Nova design using standard tank/engine modules of 4.9 m diameter in both first and second stages; 4 F-1 engine/modules in first stage, 4 J-2 engine/modules in second stage.
American heavy-lift orbital launch vehicle. Convair/Ehricke Nova design using standard tank/engine modules of 4.9 m diameter in both first and second stages; 6 F-1 engine/modules in first stage, 6 J-2 engine/modules in second stage.
American nuclear orbital launch vehicle. General Dynamics Nova vehicle using Nova A as first two stages, nuclear spacecraft with jettisonable tanks as upper stage.
American nuclear orbital launch vehicle. General Dynamics Nova vehicle using Nova B as first two stages, nuclear spacecraft with jettisonable tanks as upper stage.
American heavy-lift orbital launch vehicle. Douglas/Bono design for Nova using LH2/Lox in both stages. Improved Specific Impulse chemical stage uses many engines feeding into single large nozzle.
American heavy-lift orbital launch vehicle. General Dynamics Nova design using existing engines. Recoverable engine package; separation at 3,398 m/s at 76,200 m altitude; splashdown using retrorockets under 7 30 m diameter parachutes 1300 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.
American heavy-lift orbital launch vehicle. General Dynamics Nova design using 325 inch solid motors as first stage, M-1 engines in second stage. Recoverable solid motors, separation at 1,972 m/s at 53,000 m altitude; splashdown using retrorockets under 3 61 m diameter parachutes 610 km downrange. Recovery of solid motors forshadowed same approach on shuttle 15 years later. Masses estimated based on tank volumes, total thrust, and first stage burnout conditions.
American heavy-lift orbital launch vehicle. General Dynamics Nova design using new 3.5 million kgf Lox/Kerosene engines in first stage. Recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.
American heavy-lift orbital launch vehicle. General Dynamics Nova design using 1 1/2 stage arrangement and new 2.4 million kgf Lox/LH2 engines. Recoverable booster 4 engine package would separate at 2,980 m/s at 87,800 m altitude; splashdown under 4 46 m diameter parachutes 1,000 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.
American heavy-lift orbital launch vehicle. General Dynamics Nova design using recoverable Lox/RP-1 stage of ballistic shape with 3 million kgf engines; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.
American heavy-lift orbital launch vehicle. Nova design using 4 300 inch solids as first stage, 5 M-1 in second stage. Operational date would have been April 1973
American heavy-lift orbital launch vehicle. Nova design using 4 280 inch solids as first stage, 4 M-1 in second stage. Operational date would have been February 1973
American heavy-lift orbital launch vehicle. Nova design using existing engines; 14 F-1A in the first stage, 2 M-1 in the second. Operational date would have been December 1972
American heavy-lift orbital launch vehicle. Nova design using existing engines; 18 F-1A in the first stage, 3 M-1 in the second. Operational date would have been February 1973
American heavy-lift orbital launch vehicle. Nova design using new high pressure LH2/Lox engines; 18 in the first stage in a plug nozzle arrangement, 2 in the second. Operational date would have been December 1974.
American heavy-lift orbital launch vehicle. Nova single stage to orbit design with 24 new high pressure LH2/Lox engines in the first stage in a plug nozzle arrangement. Operational date would have been April 1975.
American heavy-lift orbital launch vehicle. Nova 1 1/2 stage design with 4 new 3 million kgf LH2/Lox engines in the jettisonable booster section and a single 3 million kgf sustainer. Operational date would have been June 1976.
American heavy-lift orbital launch vehicle. Expendable version of most exotic Martin Nova vairant; single stage to orbit, 30 cd module air augmented engines in annular shroud. Operational date would have been October 1980.
American heavy-lift orbital launch vehicle. Reusable version of most exotic Martin Nova vairant; single stage to orbit, 30 cd module air augmented engines in annular shroud. Operational date would have been October 1980.
American heavy-lift orbital launch vehicle. Expendable single stage to orbit Nova using cylindrical shape, 24 CD module engines in zero-length plug nozzle. Operational date would have been October 1977.
American heavy-lift orbital launch vehicle. Expendable single stage to orbit Nova using conical shape, 30 CD module engines in zero-length plug nozzle. Operational date would have been November 1977.
American heavy-lift orbital launch vehicle. Reusable single stage to orbit Nova using cylindrical shape, 24 CD module engines in zero-length plug nozzle. Operational date would have been June 1978.
American heavy-lift orbital launch vehicle. Reusable single stage to orbit Nova using conical shape, 30 CD module engines in zero-length plug nozzle. Operational date would have been July 1978.
American heavy-lift orbital launch vehicle. Two stage Nova using CD modules; expendable first stage with 18 modules exhausting to a 10% length plug nozzle; expendable second stage with 2 CD module engines. Operational date would have been November 1976.
American heavy-lift orbital launch vehicle. Two stage Nova using CD modules; reusable first stage with 18 modules exhausting to a 10% length plug nozzle; expendable second stage with 2 CD module engines. Operational date would have been January 1977.
American heavy-lift orbital launch vehicle. Two stage Nova using CD modules; reusable first stage with 24 modules exhausting to a zero length plug nozzle; reusable second stage with a toroidal plug nozzle engine. Operational date would have been December 1976.
American heavy-lift orbital launch vehicle. Two stage Nova using CD modules; reusable first stage with 18 modules exhausting to a 10% length plug nozzle; reusable second stage with 2 CD module engines. Operational date would have been July 1977.
American heavy-lift orbital launch vehicle. The Nova vehicle most often illustrated in the popular press and histories. As in other early concepts, this NASA design of 1959/1960 used F-1 engine in both first and second stages. Resulting performance and total liftoff mass was equivalent to later Saturn V.
American heavy-lift orbital launch vehicle. Douglas/Bono design for Nova using Lox/RP-1 in first stage, existing engines.
American heavy-lift orbital launch vehicle. Douglas/Bono design for Nova using LH2/Lox in both stages.
NS20.
Alternate Designation of Pluton short range ballistic missile.
German sounding rocket. Rocket pioneer Hermann Oberth agreed to build and fly a liquid propellant rocket to publicise the Fritz Lang film Frau im Mond. Oberth's design was too ambitious and the rocket was never completed in time for the film's premiere. But the engine developed for it would be further refined and used in the Mirak rocket, flown in 1931-1933.
Object 350.
Article Number of Burya intercontinental cruise missile.
OBV.
American anti-ballistic missile. Suborbital booster for the US Missile Defense Agency's Ground-based Midcourse Defense system's EKV ballistic missile kill vehicle. The basic OBV consisted of the upper three stages and guidance system from the Taurus orbital launch vehicle (essentially a wingless Pegasus-XL). The OBV was launched from an open pad; the operational version was to be silo-launched.
Iranian unguided solid propellant artillery rocket, licensed production of Chinese Type 83. Entered service in 1986.
Oka.
Russian intercontinental range ballistic missile. Variant using a Glushko nuclear engine heating ammonia as a propellant.
Russian intercontinental range ballistic missile. Variant using a Bondaryuk nuclear engine heating mixed alcohol and ammonia as a propellant.
One stage Orbital Space Truck.
Russian orbital launch vehicle. Launch vehicle proposed for the 'Kliper' manned spaceplane in 2004. The 'Onega' was a hitherto-unrevealed massive improvement of the reliable Soyuz. It would deliver double the payload to a space station orbit, and could be available by 2010 if funding was made available.
OOST.
American SSTO VTOVL orbital launch vehicle. Bono's earliest design for an expendable single-stage-to-orbit LH2/Lox booster. The baseline version used conventional engines.
American SSTO orbital launch vehicle. Alternate version of OOST using Improved Specific Impulse approach: many engines feeding into single large nozzle.
French test vehicle. Original designation of the Antares test vehicle.
Opel.
Fritz von Opel sponsored early tests of rocket-powered automobiles and aircraft, popularizing the idea of rocket propulsion in Germany.
Orbital Boost Vehicle.
Alternate designation for OBV anti-ballistic missile.
American target missile. Three stage vehicle consisting of 1 x GEM-40 + 1 x Orbus 1 + 1 x Orbus 1
Orel.
In the late 1990's the Russian space industry undertook the Orel programme to evaluate technology for future launch vehicles. The goals included evaluation of possible concepts for a future Russian launcher, reusable launch vehicle key technology research and analysis of "X-vehicle" flight demonstrators for technology validation.
Russian winged orbital launch vehicle. This preferred near-term configuration was a semi-reusable vertical takeoff/horizontal landing two stage launch vehicle. It would use a flyback booster, expendable second stage, and a small manned spaceplane. This was preferred to the Orel V3, which was essentially the earlier MMKS/OK-M1 system with a flyback booster, expendable core tank, and small spaceplane with recoverable main engines.
Russian winged orbital launch vehicle. Fully reusable vertical takeoff, horizontal landing two stage to orbit concept. Abandoned in favor of Orel V6.
Russian winged orbital launch vehicle. Vertically launched two stage to orbit concept consisting of horizontal landing booster, vertical landing orbiter. Abandoned in favor of Orel V6.
Fully reusable vertical takeoff / horizontal landing single stage to orbit launch vehicle. The preferred long-term alternative of the Russian Orel launch vehicle study of the 1990's.
Russian VTOVL orbital launch vehicle. Fully reusable vertical takeoff / vertical landing single stage to orbit. Concept abandoned in favor of Orel V6 by 1998 due to engine reliability concerns. Version with Lox/LH2 propellants.
Russian VTOVL orbital launch vehicle. Fully reusable vertical takeoff / vertical landing single stage to orbit. Concept abandoned in favor of Orel V6 by 1998 due to engine reliability concerns. Tripropellant Lox/Kerosene (RG-1)/LH2 version.
Orient Express.
Manufacturer's designation for X-30 ssto winged orbital launch vehicle.
French design for a scramjet-powered horizontal takeoff / horizontal landing, single stage to orbit vehicle.
American nuclear pulse test vehicle. The modified test article for Project Orion had a total mass of 105 kg. The outer shell and upper shock absorber of the original design were deleted and a parachute recovery system added.
American nuclear-powered orbital launch vehicle. Nuclear-pulse drive launch vehicle seriously developed by General Atomics in the United States from 1955-1965. The design allowed vast payloads of hundreds of tons to be hurled to the planets. By 1958 the Orion team saw themselves in direct competition with Von Braun's chemical rockets. They hoped to a land a huge manned expedition on Mars by 1964 and tour the moons of Saturn by 1970. However politically NASA would not argue for the exception to the 1963 Nuclear Test Ban Treaty necessary to allow firing of nuclear explosions in space.
American nuclear pulse orbital launch vehicle. The baseline planetary version of Orion would have launched from the earth's surface. It would have been bullet-shaped, 41 m in diameter and about 50 m high.
American nuclear pulse orbital launch vehicle. The final iteration of the Orion design was a nuclear pulse propulsion module launched into earth orbit by a Saturn V. The 100 tonne unit would have had a diameter of 10 m to match that of the booster. This would limit specific impulse to 1800 to 2500 seconds, still two to three times that of a nuclear thermal system.
American sounding rocket. The Orion was a single stage, unguided, fin stabilized rocket system which used a surplus US Army Hawk surface-to-air-missile rocket motor having a dual thrust propellant grain. Three fins on the aft end of the motor were canted to roll the vehicle at four revolutions per second at burnout for stability. Improved performance could be obtained by using a Nike booster stage. Payload 38 kg to 88 km or 68 kg to 71 km.
American nuclear pulse orbital launch vehicle. The ablative version of Dyson's starship would be smaller and faster then the heat sink version. It would have a mass of 100,000 tons unloaded and be equipped with 300,000 one megaton bombs.
American nuclear pulse orbital launch vehicle. The heat sink version of Dyson's starship would have a pusher plate made of copper. This would require 5 million tonnes of exposed surface to absorb and then reradiate 1 megaton of bomb energy. The plate would have to be 20 km in diameter.
American nuclear pulse test vehicle. The original test article for Project Orion had a total mass of 133 kg including its bullet-shaped outer shell.
Argentinan sounding rocket. Technology test vehicle, used to verify rocket motor and technologies for Orion-2 sounding rocket.
Argentinan sounding rocket. Single-stage solid-propellant sounding rocket first launched in 1965. The rocket could reach a top speed of 548 m/s.
OTR-22.
OTR-23.
$200 million was spent from 1975-1987 by Lutz Kayer in a serious attempt to develop a low-cost satellite launcher using clusters of mass-produced pressure-fed liquid propellant modules. The project was finally squelched by the German government under pressure from the Soviet and French.
Russian intercontinental cruise missile. Family of sea- or silo- launched Mach 3.5 cruise missiles with ranges up to intercontinental distances.
Russian intermediate range cruise missile. Development of a family of long-range cruise missiles was begun in 1956 by Ilyushin. The P-205 was a land-based strategic cruise missile based on the P-20 antiship missile. The land-launch version was developed for the VVS in 1958-1960. There were two submarine projects for the missile, 627A and 653, both designed by OKB-143. Construction of the 627A submarine began at Severodvinsk, but the work on the submarine was cancelled in November 1961.
P-6.
Russian intermediate range cruise missile.
Russian intermediate range cruise missile. IOC in 1988 est 1992+. SS-C-5 GLCM banned in INF.
American anti-ballistic missile. In EMD. PAC-3 version has limited Theater Ballistic Missile Defense capability.
American sounding rocket. Two stage vehicle consisting of 1 x Paiute + 1 x Apache
American sounding rocket. Two stage vehicle consisting of 1 x Paiute + 1 x Tomahawk
Norwegian hybrid single stage sounding rocket based on Lockheed Martin's HYSR technology.
German gun-launched missile. The Paris Gun of World War I could hurl a 120 kg shell with 7 kg of explosive to a range of 131 km and an altitude of 40 km.
American air-launched winged orbital launch vehicle. Pioneer Rocketplane planned in the late 1990's to produce the Pathfinder aerial-refueled spaceplane. The two-seat fighter-bomber-sized aircraft was to be powered by two turbofan engines and one kerosene/oxygen-burning RD-120 rocket engine. After takeoff from a conventional airfield, it would rendezvous with a tanker, top off its liquid oxygen tanks, and then rocket to Mach 15 and 110 km altitude. There it would release an upper rocket stage that would boost a 2100 kg payload to orbit. Pathfinder itself would return to the airfield for refueling and reuse.
Patriot.
Popular Name of MIM-104A missile.
American surface-to-air missile. Standard Army surface-to-air missile. Later versions had anti-tactical missile capability.
American target missile. Launch vehicle using surplus missile motors. PLV was part of the Boeing Lead System Integration (LSI) effort on the National Missile Defense (NMD) program. Lockheed Martin was the manufacturer and prime integrator. PLV used elements first seen on the ERIS program.
PC-2.
Manufacturer's designation for Babylon Gun gun-launched orbital launch vehicle.
Peace-1.
Alternate designation for T-7A sounding rocket.
American intercontinental ballistic missile. 10 nuclear MIRV warheads. In service 1986-2004.
American sounding rocket. Air Launch Probe System (ALPS) and Fighter Launched Advanced Materials Experiment (FLAME) were both vehicles that used a Pedro first stage and a Recruit second stage. They were launched from an F-4 fighter aircraft.
French sounding rocket. 2 stage vehicle with larger booster and Belier upper stage. Evidently not flown.
American air-launched orbital launch vehicle. Privately-funded, air-launched winged light satellite launcher.
American air-launched orbital launch vehicle. Four stage vehicle consisting of 1 x L-1011 + 1 x Orion 50S + 1 x Orion 50 + 1 x Orion 38
American SSTO VTOVL orbital launch vehicle. Bono design for semi-single-stage-to-orbit ballistic VTOVL launch vehicle. Drop tanks were shed on the way to orbit. Pegasus could deliver either a Satun V-size payload to LEO or 172 passengers and their luggage the 12,000 km from Vandenberg to Singapore in 39 minutes.
American air-launched orbital launch vehicle. Uprated version of Pegasus air-launched winged light satellite launcher. 4 stage vehicle consisting of 1 x L-1011 + 1 x Pegasus XL stage 1 + 1 x Orion 50XL + 1 x Orion 38.
American air-launched orbital launch vehicle. Five stage version consisting of 1 x L-1011 + 1 x Pegasus XL stage 1 + 1 x Orion 50XL + 1 x Orion 38 + 1 x HAPS
American air-launched orbital launch vehicle. Five stage version consisting of 1 x NB-52 + 1 x Orion 50S + 1 x Orion 50 + 1 x Orion 38 + 1 x HAPS
Pekdosan-1.
Alternate designation for Taepodong 1 orbital launch vehicle.
American low cost orbital launch vehicle. Low cost commercial test vehicle. First test failed and satellite launch project sank for lack of further investors and customers.
Perimeter.
Alternate Designation of Perimetr 15A11 strategic communications missile.
Ukrainian strategic communications missile. Perimetr was developed for launch of a highly secret communications payload. This would be be put in orbit or on a long high-altitude trajectory to provide back-up command and control of the strategic forces in the event of nuclear war.
Pershing.
Popular Name of Pershing 1 intermediate range ballistic missile.
American US Army intermediate range ballistic missile.
American intermediate range ballistic missile.
American intermediate range ballistic missile.
Pershing 1B.
Popular Name of MGM-31D intermediate range ballistic missile.
American intermediate range ballistic missile. Cancelled
Pershing IA.
Popular Name of Pershing 1A intermediate range ballistic missile.
Pershing II.
Popular Name of Pershing 2 intermediate range ballistic missile.
Petrel.
Alternate designation for Petrel 1 sounding rocket.
British sounding rocket. Petrel was a larger sounding rocket built by Bristol Aerojet using the same tube-launch technique as Skua. A total of 240 Petrels were launched from 1967-1982 from many sites around the world.
British sounding rocket. Petrel was a larger sounding rocket built by Bristol Aerojet using the same launch technique as Skua. Three Chick rockets blasted the upper stage and payload out of a 10-m long launch tube. The 4.5 kN Lapwing second stage burned for 30 seconds. A unique aspect was that the Chick boosters could be recovered and reloaded with propellant.
British sounding rocket. Improved Petrel using four Chick boosters and a lengthened Lapwing second stage which provide 4.5 kN thrust for 40 seconds. Petrel 2's were also fired as targets for missile tests at Woomera.
PGM-11A.
Department of Defence Designation of Redstone short range ballistic missile.
PGM-16A.
Department of Defence Designation of Atlas A test vehicle.
PGM-16B.
Department of Defence Designation of Atlas B test vehicle.
PGM-17A.
Department of Defence Designation of Thor intermediate range ballistic missile.
PGM-19A.
Department of Defence Designation of Jupiter intermediate range ballistic missile.
Phoenix.
Popular Name of SLS A-388 orbital launch vehicle.
American SSTO VTOVL orbital launch vehicle. The larger 180 tonne Phoenix design of the 1980's was envisioned in two versions -- the Phoenix C (Cargo, unmanned) and Phoenix E (Excursion -- for use as a lunar or Mars lander and personnel transport to earth orbit). The earlier versions used liquid oxygen oxidiser and two fuels (hydrogen and propane) but later iterations used only oxygen and hydrogen (varying the oxidiser to fuel ration during ascent). The designs used an 'aeroplug' in place of the 'aerospike' of earlier SSTO designs. Gary Hudson and Maxwell Hunter spent several years trying to interest investors in the designs before the company folded.
American SSTO VTOVL orbital launch vehicle. The small Phoenix design of the 1980's was envisioned in two versions -- the Phoenix L (Light, cargo only) and Phoenix LP (Light-Prime, crewed). The earlier versions used liquid oxygen oxidiser and two fuels (hydrogen and propane) but later iterations used only oxygen and hydrogen (varying the oxidiser to fuel ratio during ascent). The designs used an 'aeroplug' in place of the 'aerospike' of earlier SSTO designs.
American SSTO VTOVL orbital launch vehicle. Intermediate versions of the Phoenix concept were sketched out in the mid-1980's. These more conservative vehicles used individual altitude-compensating bell nozzles rather than the aeroplug baseline. Composite materials were to be used in the aeroshell and, possibly, in the propellant tankage.
Pioner.
Launch System of 15Zh45 intermediate range ballistic missile.
Russian intermediate range ballistic missile. Mobile solid propellant intermediate range multiple warhead ballistic missile. Seen as an enormous threat to NATO. 405 launchers deployed by 1987 when the missile was banned by the INF Treaty.
Pioner UTTKh.
Launch System of 15Zh45UTTKh intermediate range ballistic missile.
Pioner-3.
Launch System of 15Zh53 intermediate range ballistic missile.
PL-04.
CIA Designation of RT-23 15Zh52 and RT-23U 15Zh61 intercontinental ballistic missiles.
US Army anti-ballistic missile, development started in 1951. Program cancelled in 1959.
Pluto.
Popular Name of SLAM intercontinental cruise missile.
French short range ballistic missile.
PLV.
Alternate designation for Payload Launch Vehicle target missile.
Pobeda.
German sounding rocket.
American test vehicle.
Polar Satellite Launch Vehicle.
Full name of PSLV all-solid orbital launch vehicle.
American submarine-launched ballistic missile. Probably the most technically innovative program in history, Polaris integrated solid-propellant, inertially-guided intermediate range ballistic missiles with nuclear submarines that could remain submerged for months at a time. All of these were new technologies, but the first ship was underway only three years after go-ahead.
American missile. Two stage vehicle consisting of 1 x A1P + 1 x A1P stage 2
Polaris A-1.
Popular Name of Polaris A1 missile.
American missile. In comparison to the A-1, the Polaris A-2 had a slightly longer first stage and a lighter second-stage motor casing. These features increased range to 2800 km (1500 nm), the performance originally envisioned by the Navy.
Polaris A-2.
Popular Name of Polaris A2 missile.
American missile.
American missile. Two stage vehicle consisting of 1 x A3P + 1 x X-260
Polaris A-3.
Popular Name of Polaris A3 missile.
American missile. Two stage test vehicle consisting of 1 x A3P + 1 x X-260
American missile. British version of Polaris A3.
American missile. 2 stage experimental vehicle
American missile. Single stage test vehicle to test thrust-vectoring system.
Russian orbital launch vehicle. UR-500 design studies considered two variants of the first stage: polyblock and monoblock. The polyblock variant consisted of a centre large diameter oxidizer tank surrounded by several smaller diameter fuel tanks. This version could be assembled in a special rig with the lateral blocks being sequentially mounted on the centre. In January 1962 this design was chosen as most advantageous, following studies that indicated improved wind loads and bending moment characteristics compared to the monoblock design. The developed version of the design would become known as the Proton.
Polyot.
Alternate designation for Sputnik 11A59 orbital launch vehicle.
French tactical ballistic missile. Operational and technical evaluation 1998-2002.
American submarine-launched ballistic missile. SLBM, 2 stages, inertial guided, nuclear MIRV warhead, range that of twice Polaris A-3.
Poseidon C-3.
Popular Name of Poseidon submarine-launched ballistic missile.
Poseidon C-4.
Alternate designation for Trident C-4 intercontinental ballistic missile.
Poseidon D-5.
Alternate designation for Trident D-5 intercontinental ballistic missile.
Russian short range ballistic missile. Short-range air-augmented ballistic missile. Tested concepts for Gnom ICBM.
Russian orbital launch vehicle. Launch vehicle using the 1st stage of the SS-N-20 SLBM topped by an SS-N-23 SLBM (RSM-52+RSM-54). Liftoff mass 104 tonnes. Can be launched from stationary or mobile platforms.
Indian single-stage short range ballistic missile. First units deployed in 1995.
American test vehicle. At request of Army Ordnance, Cal Tech's rocket laboratory developed the first US long-range missiles. Project ORDCIT resulted in development of the Private A and Corporal missiles. At Camp Irwin, Calif., 24 Private A rockets were launched by JPL, only 11 months after the start of Project ORDCIT. This rocket technology that led to later operational Corporal and Sergeant missiles.
Project 1059.
Alternate designation for DF-1 intermediate range ballistic missile.
Project 4211.
Manufacturer's designation for Eole test vehicle.
Project 4212.
Manufacturer's designation for Super V-2 intermediate range ballistic missile.
Project 4213.
Manufacturer's designation for Veronique sounding rocket.
German sounding rocket. Dornier project of the early 1960's for a recoverable, reusable sounding rocket. The liquid fueled rocket would use a paraglider for recovery, and could be reused up to six times. Drop tests were made of the paraglider system in Sardinia in 1965 but no flights of the rocket itself ever took place.
In 1992 Xiandong Bao of the Shanghai Astronautics Bureau revealed plans for a modular family of modern rockets to support future Chinese manned space activities. The entire family would be based on a Lox/Kerosene booster stage of 306 tonnes mass, and a Lox/LH2 upper stage of 57 tonnes mass.
American air-launched orbital launch vehicle. The US Navy's satellite launcher project competed with the Army's Jupiter-C, the Air Force Atlas, and the civilian Vanguard. Air-launched satellite launch vehicle, and anti-satellite versions, tested by the US Navy shortly after Sputnik. One may have achieved orbit.
American air-launched orbital launch vehicle. Ground-launched, 5 stage vehicle for Project Pilot.
American air-launched orbital launch vehicle. Six stage vehicle consisting of 1 x F4D-1 Skyray + 2 x HOTROC + 2 x HOTROC + 1 x X-241 + 1 x NOTS 8in + 1 x NOTS 3in Sph.
American orbital launch vehicle. The April 1953 design for the Atlas at the time of Convair's proposal used five main engines to power a 200 metric tone rocket able to send a 1400 kg nuclear warhead over a 10,200 km range. CEP was 1850 m.
American sounding rocket. Single stage vehicle.
The Proton launch vehicle has been the medium-lift workhorse of the Soviet and Russian space programs for over forty years. Although constantly criticized within Russia for its use of toxic and ecologically-damaging storable liquid propellants, it has out-lasted all challengers, and no replacement is in sight. Development of the Proton began in 1962 as a two-stage vehicle that could be used to launch large military payloads or act as a ballistic missile with a 100 megaton nuclear warhead. The ICBM was cancelled in 1965, but development of a three-stage version for the crash program to send a Soviet man around the moon began in 1964. The hurried development caused severe reliability problems in early production. But these were eventually solved, and from the 1970's the Proton was used to launch all Russian space stations, medium- and geosynchronous orbit satellites, and lunar and planetary probes.
Proton / Block D-1.
Alternate designation for Proton-K-D-1 orbital launch vehicle.
Proton / Block D-2.
Alternate designation for Proton-K-D-2 orbital launch vehicle.
Proton / Block DM.
Alternate designation for Proton-K-DM orbital launch vehicle.
Proton / Block DM-2M.
Alternate designation for Proton-K-DM-2M orbital launch vehicle.
Proton / Block DM-5.
Alternate designation for Proton-K-17S40 orbital launch vehicle.
Proton 2.
Alternate designation for UR-500 launch vehicle.
Proton 3.
Alternate designation for Proton-K orbital launch vehicle.
Proton 8K82K / Block DM-2.
Alternate designation for Proton-K-DM-2 orbital launch vehicle.
Proton KM.
Alternate designation for Proton-K-Briz-M orbital launch vehicle.
Proton M.
Alternate designation for Proton-M-Briz-M orbital launch vehicle.
Earlier 8K82K model Proton, but Briz M storable propellant upper stage replaced the Block D cyrogenic stage.
Improved Proton orbital launch vehicle. Improvements in lower stages to reduce structural mass, increase thrust, and fully utilize propellants (reducing release of toxic chemicals in stage impact areas). Briz M storable propellant upper stage replaces Block D cyrogenic stage.
Russian orbital launch vehicle. Development of a three-stage version of the UR-500 was authorised in the decree of 3 August 1964. Decrees of 12 October and 11 November 1964 authorised development of the Almaz manned military space station and the manned circumlunar spacecraft LK-1 as payloads for the UR-500K. Remarkably, due to continuing failures, the 8K82K did not satisfactorily complete its state trials until its 61st launch (Salyut 6 / serial number 29501 / 29 September 1977). Thereafter it reached a level of launch reliability comparable to that of other world launch vehicles.
Russian orbital launch vehicle. Version of Proton using Block DM-5 / 17S40 fourth stage. This stage has a new payload adapter for use with heavier paylods launched into sub-synchronous orbits. Used for launch of Arkon reconnaisance satellite.
Russian orbital launch vehicle. Version of the 17S40 with payload adapter for deployment of multiple LM 700 (Iridium) spacecraft into medium earth orbit.
Russian orbital launch vehicle. This four stage version of the Proton was originally designed to send manned circumlunar spacecraft into translunar trajectory. Guidance to the Block D stage must be supplied by spacecraft. The design was proposed on 8 September 1965 by Korolev as an alternate to Chelomei's LK-1 circumlunar mission. It combined the Proton 8K82K booster for the LK-1 with the N1 lunar Block D stage to boost a stripped-down Soyuz 7K-L1 spacecraft around the moon. The Korolev design was selected, and first flight came on 10 March 1967. The crash lunar program led to a poor launch record. Following a protracted ten year test period, the booster finally reached a level of launch reliability comparable to that of other world launch vehicles.
Russian orbital launch vehicle. This derivative of the original four stage Block D / 11S824 version of the Proton was used from 1978 to launch Lavochkin OKB planetary probes (Mars, Venera) and high earth orbit astronomical observatories (Astron, Granat). Guidance to the Block D-1 stage must be supplied by spacecraft. Equipped with N2O4/UDMH verniers for precise placement of payloads in high orbits or planetary trajectories.
Russian orbital launch vehicle. This four stage version of the Proton was a modification of the original Block D / 11S824M for launch of late 1980's Lavochkin OKB probes on missions to Mars. Guidance to the Block D-2 stage must be supplied by spacecraft.
Russian orbital launch vehicle. The original four stage Proton / Block D configuration was used until 1976, at which time it was replaced by a modernised version equipped with N2O4/UDMH verniers for precise placement of payloads in geosynchronous orbit and its own self-contained guidance unit. This was accepted into military service in 1978 with the first Raduga launch. The stage was first developed for launch of gesynchronous military communications and early warning satellites (Raduga, Ekran, Gorizont, Potok, SPRN). Its later versions continue in use for launch of MEO and geosynchronous comsats, and was Russia's most successful commercial launcher.
Russian orbital launch vehicle. This improved four stage version uses the Block DM-2 / 11S861 fourth stage, which has its own guidance unit. This reduces payload but does not require the spacecraft's guidance system to provide steering commands to booster. Replaced the original Block DM / 11S86 version from 1982 to 1995. Used for launch of Glonass navigation satellites into medium earth orbit; and launch of Luch, Ekran-M, Potok, Raduga, Gorizont, Raduga-1, Elektro, and Gals communications satellites into geosynchronous orbit. Commercial version with Saab payload adapter-seperation system for Western payloads was dubbed 'Block DM1'.
Russian orbital launch vehicle. Version of the 11S861 with adapter for Lockheed Martin AS 4000 bus spacecraft.
This four stage version uses the Block DM-2M / 11S861-01 upper stage, which has its own self-contained guidance unit. This reduces payload but does not require the spacecraft's guidance system to provide steering commands to booster. Used for launches of Russian geosynchronous satellites from 1994 on.
Russian orbital launch vehicle. Version of the 11S861-01 with Saab payload adapter-seperation system for insertion of Hughes HS-601 bus spacecraft into geosynchronous orbit.
Russian orbital launch vehicle. Version of the 11S861-01 with Saab payload adapter-seperation system for insertion of FS-1300 bus spacecraft into geosynchronous orbit.
Russian orbital launch vehicle. Improved Proton-M stages, mated to the older 11S861 upper stage for certain payloads.
Proton-M/DM-3
PSLV.
Indian third-generation launch vehicle, large enough to carry polar-orbiting earth resources satellites.
Indian all-solid orbital launch vehicle. Five stage vehicle consisting of 6 x PSOM + 1 x S139 + 1 x PS2 + 1 x PS3 + 1 x PS4
Core alone four stage vehicle consisting of 1 x S139 + 1 x PS2 + 1 x PS3 + 1 x PS4
Five stage vehicle consisting of 6 x PSOM-XL + 1 x S139 + 1 x PS2 + 1 x PS3 + 1 x PS4
PTV-N-4.
Department of Defence Designation of Cobra-BTV test vehicle.
Albert Puellenberg began construction of a series of increasingly sophisticated rockets in 1928. After further private rocketry development was prohibited in 1934, Puellenberg continued his work in secret, culminating with the extremely sophisticated VR12 rocket in 1938. This was the end of the line and the last privately-developed rocket built in Germany until 1956.
PWN-1.
Department of Defence Designation of Loki Dart sounding rocket.
American sounding rocket, equipping the Loki-Dart payload with a radar transponder, in turn requiring the larger Super Loki motor to reach the same altitude.
American sounding rocket. Version of the PWN-10 with a smaller payload dart without the transponder.
American sounding rocket. The was another sounding rocket using the Super Loki booster. It used a dart with a ROBIN (Rocket Balloon Instrument) Inflatable Falling Sphere payload.
PWN-2.
Department of Defence Designation of Aerobee 150 sounding rocket.
PWN-3.
Department of Defence Designation of Nike Cajun sounding rocket.
PWN-4.
Department of Defence Designation of Exos sounding rocket.
American sounding rocket. Produced by Marquardt for the Army, Roksonde meteorological sounding rockets first completed a series of tests at White Sands Missile Range and Pacific Missile Range. They were later successfully fired from Cape Canaveral, telemetered measurements of winds and temperatures at altitudes above 600,000 m.
PWN-6.
Department of Defence Designation of Kitty sounding rocket.
PWN-7.
Department of Defence Designation of Rooster sounding rocket.
American sounding rocket. In the early 1960s, the low-cost Loki-Dart sounding rockets could only carry a passive chaff payload to high altitude. For more sophisticated payloads like temperature transmitters, the USAF had to use the significantly more expensive Arcas. The Space Data Corporation (SDC) was founded in 1963 with the goal to develop a meteorological instrument package small enough to fit into the 3.5 cm (1.38 in) diameter darts of the Loki-Dart systems.
PWN-9.
Department of Defence Designation of Kangaroo sounding rocket.
American test vehicle. Single stage vehicle consisting of 4 Deacons fired in parallel.
American low cost orbital launch vehicle. Family of low-cost space boosters under development by AirLaunch LLC under DARPA and NASA contracts in 2007-2008.
American low cost orbital launch vehicle. Low-cost air-launched pressure-fed liqud oxygen/propane launch vehicle developed under DARPA's Falcon program.
American low cost orbital launch vehicle. Enlarged version of the Quick Reach launch vehicle proposed to launch the t/Space CXV manned spacecraft. The concept built on both Quick Reach and SpaceShipOne to produce a low-cost air-launched man-rated pressure-fed liqud oxygen/propane launch vehicle.
r.
Manufacturer's designation for Space Data LCLV sounding rocket.
R.04.
French post-war surface-to-air missile based on the German Wasserfall.
R-1.
Manufacturer's designation for GIRD-09 sounding rocket.
R-1.
Russian short range ballistic missile. Stalin did not decide to proceed with Soviet production of this copy of the German V-2 until 1948. Despite the threatening supervision of the program by Stalin's secret police chief, Beria, and the assistance of German rocket engineers, it took eight years for the German technology to be absorbed and the missile to be put into service. It was almost immediately superseded by later designs, but the effort laid the groundwork for the Soviet rocket industry. Surplus R-1's were converted to use as a sounding rockets for military and scientific research missions.
Russian short range ballistic missile. Initial production version.
R-10.
Alternate designation for G-4 intermediate range ballistic missile.
R-10.
Russian heavy-lift orbital launch vehicle. Glushko booster - 1500t, Korolev I evo delo p. 307
Post-war Russian version of German Wasserfall surface-to-air missile. Never put into production, but technology used for further surface-to-air and surface-to-surface missile developments in Russia.
Post-war Russian version of German Schmetterling surface-to-air missile. 16 test flights made at Kapustin Yar between 18 October and 19 December 1949. Not put into production, cancelled in favour of the R-112.
Post-war Russian version of German Taifun anti-aircraft barrage rocket. Developed and tested in 1947-1951 but abandoned in favour of the R-110.
Russian surface-to-air missile.
All-Russian second generation version of the R-101, itself a derivative of the German Wasserfall. Development began in May 1949 but the missile did not reach flight test stage before its cancellation in 1951.
Russian derivative of the German Wasserfall, an interim design between the R-101 and R-108. The missile did not reach flight test stage before it was cancellation in 1951.
R-11.
First Russian ballistic missile using storable propellants, developed from the German Wasserfall SAM by Korolev's OKB. The design was then spun off to the Makeyev OKB for development of Army (R-17 Scud) and SLBM (R-11FMA) derivatives.
Larger caliber Russian version of the German Taifun anti-aircraft barrage rocket. Developed and tested in 1948-1956 and reached the initial production stage, but cancelled due to the inability to produce an economical rocket with the necessary consistent range accuracy for the barrage role.
Russian surface-to-air missile. Soviet surface-to-air missile design of 1948-1951. Propulsion and guidance based on that of the R-102 (copy of German Schmetterling) but with new aerodynamics. Cancelled without ever flying in 1951 when decision was made to proceed with a new generation of SAM designs.
Russian surface-to-air missile. Soviet surface-to-air missile design of 1948-1950. Developed in competition with the R-112 (derrived from the German Schmetterling) but with new aerodynamics. Cancelled without ever flying in 1950 in favour of further development of the R-112.
Russian suborbital launch vehicle. Version of the R-11 'Scud' missile used as a sounding rocket. First launched in 1957, and capable of taking 250 to 400 kg of payload to 100 to 160 km altitude. The payloads were enclosed in a spherical re-entry capsule, which was gyro-stabilised to ensure instruments could be pointed precisely at the sun or other astronomical target.
Russian suborbital launch vehicle. Sounding rocket version of R-11 with increased payload.
First Russian submarine-launched ballistic missile. Following protracted testing the design was accepted by the military in 1959 but never put into operational service.
Russian submarine-launched ballistic missile. Improved production version of R-11, not retired until 1977.
R-12.
Manufacturer's designation for G-2 intermediate range ballistic missile.
R-12.
Ukrainian intermediate range ballistic missile. The R-12 was the first operationally effective intermediate range ballistic missile, the first Soviet missile deployed with a thermonuclear warhead, and the first mass-produced missile in history. 2,300 of the storable propellant rockets were built and deployed in both mobile and silo-based versions for thirty years, from March 1959 to June 1989. It was a primary element in the Soviet deterrent threatening Western Europe and China throughout the Cold War. Deployment of R-12's to Cuba in 1962 precipitated the Cuba Missile Crisis.
Ukrainian intermediate range ballistic missile. Universal version of the R-12U, for pad-launch or from the 'Dvina' silo complex.
R-13.
Manufacturer's designation for G-3 intermediate range cruise missile.
R-13.
Russian submarine-launched ballistic missile. Developed from 1956-1960. First nuclear-armed SLBM.
R-14.
Manufacturer's designation for G-4 intermediate range ballistic missile.
R-14.
Ukrainian intermediate range ballistic missile. The R-14, with a range of 3600 km, was the only missile of that range class to be fielded. A key element in the Cuba missile crisis, it thereafter was part of the nuclear deterrent targeted at NATO and China. Built in relatively limited numbers by Soviet standards, it was perhaps more important as the basis for the first stage of the R-16 ICBM and the Kosmos-3 launch vehicle. The latter continued in use into the 21st Century.
Russian intermediate range ballistic missile. Universal version, for pad-launch or from silo complex 'Chusovaya'.
R-15.
Russian submarine-launched ballistic missile. Yuzhnoye 1000-km range submarine-launched ballistic missile. According to Przybilski, it was related to the light ICBM later designated R-26/8K66.
R-16.
Ukrainian intercontinental ballistic missile. The Soviet Union's first practical ICBM, a two stage vehicle using storable propellants. Development began in 1956 and the missile was in service from 1962 to 1974. Peak deployment consisted of 186 launchers, about a third of them in missile silos, the rest in fixed 'soft' installations.
Ukrainian intercontinental ballistic missile. Standardised version of R-16, for either pad or silo launch.
R-17.
Russian short-range ballistic missile. The final refinement of the R-11 design, the R-17, was exported widely and became infamous around the world by its ASCC reporting name - "Scud". It was perhaps the most famous ballistic missile of the post-war period due to its use in the Iran-Iraq 'War of the Cities' and the Gulf War. This was the definitive production version of what was essentially a storable-propellant rocket with the performance of the V-2. The original design was by Makeyev but the missile itself was produced by the Votkinsk Machine Building Plant.
R-1A.
Russian short range ballistic test vehicle. Experimental missile for testing warhead separation.
R-1B.
Russian short range ballistic suborbital launch vehicle. The R-1B version was designed for scientific research at altitudes of up to 100 km, including study of cosmic rays; properties of the atmosphere; solar spectra; effects if zero-G and radiation on animals; and development of recovery of the entire missile using parachutes in order to reuse it for further experimental launches.
R-1D.
Russian short range ballistic suborbital launch vehicle. The R-1B version was designed for scientific research at altitudes of up to 100 km, including winds aloft, the ionosphere, and effects of spaceflight and recovery of living animals.
R-1E.
Russian short range ballistic suborbital launch vehicle. The R-1E version was designed for scientific research at altitudes of up to 100 km, including winds aloft, air composition, solar radiation, the ionosphere, ozone layer characteristics, and effects of spaceflight and recovery of living animals.
Russian short range ballistic suborbital launch vehicle.
R-1V.
Russian short range ballistic suborbital launch vehicle. The R-1V version was designed for scientific research at altitudes of up to 100 km, including study of cosmic rays; properties of the atmosphere; solar spectra; effects if zero-G and radiation on animals; and development of recovery of the entire missile using parachutes in order to reuse it for further experimental launches.
R-2.
Russian intermediate range ballistic missile. The Soviet R-2 ballistic missile was developed in 1947-1953, nearly in parallel with the R-1 from which it derived. It incorporated many detailed improvements, had double the range of the R-1 and V-2, and was equipped with a deadly radiological warhead. The ethyl alcohol used in the V-2 and R-1 was replaced by methyl alcohol in the R-2, eliminating the problem of the launch troops drinking up the rocket fuel. Versions of the R-2 for suborbital manned flight were studied by Korolev in 1956-1958, but it was decided instead to move directly to orbital flights of the Vostok. However some equipment tested on the R-2 found its way onto canine flights of Sputnik and Vostok. The R-2 design was transferred to China in 1957 to 1961, providing the technical basis of the Chinese rocket industry.
R-20.
Russian orbital launch vehicle. Glushko booster - 2000t, Korolev I evo delo p. 307
R-21.
Russian submarine-launched ballistic missile. First flight 1962. NATO code Serb may apply to SS-N-6 instead. First subsurface launched SLBM (development began at OKB- 586 and transferred to SKB-385).
Russian submarine-launched ballistic missile. Version of R-21 SLBM on Yankee submarines.
R-26.
Ukrainian intercontinental ballistic missile. Two stage light ICBM developed 1960-1962, but cancelled so that Yangel could concentrate his efforts on the R-36. After project cancellation, a mock-up of this missile was shown in Moscow parades and misidentified for years by Western analysts as the 'SS-8'.
R-27.
Russian submarine-launched ballistic missile. First flight 1967. Correct NATO code may be Serb; Sawfly was competitor. Development completed 1968.
Russian submarine-launched ballistic missile. First flight October 1972.
Russian submarine-launched ballistic missile. Development completed 1973.
R-29.
Russian submarine-launched ballistic missile. First intercontinental submarine-launched ballistic missile (range 7800 km). First flight 1969. Development completed 1973. The variants of this missile were given three different DoD designations over the years (SS-N-8, SS-N-18, and SS-N-23).
Russian submarine-launched ballistic missile. First flight 1976. Development completed 1974 according to Makeyev.
Russian submarine-launched ballistic missile. First flight 1977.
Russian submarine-launched ballistic missile. First flight 1975; Nov 1978 first sub launch. Developed 1973-1977. 3 MIRV
R-29R-2S.
Alternate Designation of R-29R submarine-launched ballistic missile.
Russian submarine-launched ballistic missile. First flight 1981. SLBM on Delta 2 subs. 7 MIRV
Russian submarine-launched ballistic missile. SLBM on Delta 4 subs. First flight June 1983. Developed 1973-1986.
R-2A.
Russian intermediate range ballistic suborbital launch vehicle. The R-2A was designed for scientific research at altitudes of up to 200 km, including properties of the atmosphere from 150-200 km; ultraviolet observations of the sun; recovery of animals from flights to 200 km altitude; and study of the ionosphere at altitudes of 150-200 km.
R-2E.
Russian intermediate range ballistic suborbital launch vehicle. The R-2E prototype tested technological innovations planned for the production R-2 missile. These included use of an integral fuel tank and a seperable warhead.
R-2R.
Russian intermediate range ballistic missile.
R-3.
Russian intermediate range ballistic missile. Development of the long-range R-3 missile was authorised at the same time as the V-2-derived R-1 and R-2 rockets in April 1947. Supplemental authorisation was contained in a government decree of 14 April 1948.The specification was an order of magnitude leap from the other vehicles - to deliver a 3 tonne atomic bomb to any point in Europe from Soviet territory - a required range of 3000 km. To achieve this objective innovative technology was needed in every area of the missile design. Korolev was again in direct competition with the design to the same specification of the captured Germans (Groettrup's G-4).
R-31.
Russian submarine launched ballistic missile. First Soviet submarine-launched ballistic missile to reach production using solid propellants. Deployed from 1980, but withdrawn in 1990 under the terms of the SALT-2 Treaty.
Ukrainian intercontinental ballistic missile. Initial ICBM version.
Ukrainian intercontinental ballistic missile.
Ukrainian intercontine