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Alternate designation for Raketoplan manned spaceplane.
r.
Manufacturer's designation for Space Data LCLV sounding rocket.
R-.
Rocket (designation numbering series) (Russian abbreviation)
R.04.
French post-war surface-to-air missile based on the German Wasserfall.
R/V.
Re-entry vehicle
R-1.
Manufacturer's designation for GIRD-09 sounding rocket.
R-1.
Lox/Alcohol propellant rocket stage. Loaded/empty mass 12,630/4,066 kg. Thrust 307.09 kN. Vacuum specific impulse 233 seconds. Payload 815 / 483 kg. Range 270 km. Maximum altitude 77 km. Time of flight 5 minutes. Max velocity at burnout 1465 m/s. Accuracy 8 km in range, 4 km laterally.
R-1.
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 It was almost immediately superseded by later designs, but the effort laid the groundwork for the Soviet rocket industry.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.
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 It was almost immediately superseded by later designs, but the effort laid the groundwork for the Soviet rocket industry.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.
Isayev Nitric acid/Amine rocket engine. R-101B/R-108 SAM. Developed 1950-51. Launch thrust 83.3 kN. Single chamber engine designed for use in the R-101B and R-108 (derivative of German Wasserfall).
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.
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.
Nitric acid/Kerosene propellant rocket stage. Loaded/empty mass 4,660/955 kg. Thrust 93.28 kN. Vacuum specific impulse 251 seconds. First Russian ballistic missile using storable propellants. Enlargement/elaboration of German Wasserfall SAM. Developed by Korolev OKB, then Makeyev OKB spun off to develop Army and SLBM derivatives. Range 270 km with 690 kg, accuracy 1.5 km/0.75 km. Maximum altitude 78 km. Time of flight 5.4 minutes. Max velocity at burnout 1430 m/s. Source: Wall chart, Russian Space Agency HQ, Moscow.
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.
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.
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.
Nitric acid/Kerosene propellant rocket stage. Loaded/empty mass 4,473/1,080 kg. Thrust 92.83 kN. Vacuum specific impulse 250 seconds. First Russian submarine-launched ballistic missile. Range 150 km with 967 kg warhead. Accuracy 1.5 km in range, 0.75 km lateral.
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.
Nitric acid/Kerosene propellant rocket stage. Loaded/empty mass 34,610/4,810 kg. Thrust 625.52 kN. Vacuum specific impulse 235 seconds. Payload 390 kg. Range 1500 km. Maximum altitude 398 km. Time of flight 11.8 minutes. Max velocity at burnout 3530 m/s. Accuracy 6 km in range, 5 km laterally. Source: wall chart, Russian Space Agency HQ, Moscow.
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-13.
Nitric acid/Amine propellant rocket stage. Loaded mass 13,700 kg.
R-13.
Dushkin Nitric acid/Solid hybrid rocket engine. Out of Production. Developed in the late 1950s by OKB Dushkin. It was a combined (powder+liquid) engine, characterized by a new technical approach conceived by Dushkin in the prewar design of the KRD-604.
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.
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.
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.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 110,000/10,000 kg. Thrust 2,609.50 kN. Vacuum specific impulse 289 seconds. Range 12,000 km. Tsniimash has 1:10 structural simulation model. Two stage ICBM with nitric acid oxidizer. Developed 1956-1961. Entered service 1961. Chief designer Yangel. Source: Placard, TsNIIMASH.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 27,000/3,000 kg. Thrust 882.10 kN. Vacuum specific impulse 293 seconds. Range 12,000 km. Tsniimash has 1:10 structural simulation model. Two stage ICBM with nitric acid oxidizer. Developed 1956-1961. Entered service 1961. Chief designer Yangel. Source: Placard, TsNIIMASH.
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-17.
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.
R-17.
Nitric acid/Kerosene propellant rocket stage. Loaded/empty mass 5,385/1,645 kg. Thrust 93.10 kN. Vacuum specific impulse 251 seconds. Developed from Russian storable fuel tactical missile. Original R-11 designed by Korolev OKB, subsequent developments by Makeyev OKB. Using calculations of Gerald Bull, stretched and clustered as basis of Iraqi ICBM/satellite launch vehicle.
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.
R-1E.
Marquardt N2O4/MMH rocket engine. 0.110 kN. In Production from 1981. Isp=280s. Thruster developed as the Space Shuttle Orbiter's vernier attitude control and orbit adjust thruster. There were six employed in conjunction with the 38 R-40 thrusters.
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.
Lox/Alcohol propellant rocket stage. Loaded/empty mass 19,632/4,592 kg. Thrust 404.11 kN. Vacuum specific impulse 237 seconds. Payload 1350 / 508 kg. Range 550 km. Maximum altitude 171 km. Time of flight 7.5 minutes. Max velocity at burnout 2175 m/s. Accuracy 8 km in range, 4 km laterally.
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-2.
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
Dushkin rocket engine. 9.8 kN. Out of Production. Thrust variable 0.8 tf -1.0 tf.
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).
R-21.
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).
N2O4/UDMH propellant rocket stage. Loaded mass 16,600 kg.
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'.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 60,300/3,000 kg. Thrust 1,451.00 kN. Vacuum specific impulse 310 seconds. Orevo has sectioned hardware. Tsniimash has 1:10 structural simulation model. All figures accurate except empty mass estimated. Source: Placard, TsNIIMASH, Orevo.
Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 25,200/2,500 kg. Thrust 428.06 kN. Vacuum specific impulse 308 seconds. Orevo has sectioned hardware. Tsniimash has 1:10 structural simulation model. All figures accurate except empty mass estimated. Source: Placard, TsNIIMASH, Orevo.
R-27.
First flight 1967. Correct NATO code may be Serb; Sawfly was competitor. Development completed 1968.
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.
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).
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).
N2O4/UDMH propellant rocket stage. Loaded mass 20,000 kg. Thrust 682.00 kN.
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.
Alternate designation for D-2 Lox-Kerosene rocket engine.
R-3.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 69,000/5,480 kg. Thrust 1,370.00 kN. Vacuum specific impulse 285 seconds. 3000 km range IRBM design to study problems of long-range rockets. Developed April 1947 to 1949 before cancellation.
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.
R-31.
Lyulka turbojet engine. 91.2 kN. MiG-25. Out of Production. Used in MiG-25. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=2073s.
Solid propellant rocket stage. Loaded mass 1,300 kg. Thrust 3.92 kN. Bus powered by four solid propellant motors mounted 90 degrees to each other, each 60 kg mass, 0.77 m long, 0.28 m diameter.
Solid propellant rocket stage. Loaded mass 17,500 kg. Thrust 578.00 kN.
Solid propellant rocket stage. Loaded mass 6,900 kg. Thrust 233.30 kN.
Ukrainian intercontinental ballistic missile. Initial ICBM version.
Ukrainian intercontinental ballistic missile.
Ukrainian intercontinental ballistic missile.
Ukrainian intercontinental ballistic missile. The R-36P was a version of the R-36 which could deploy three separate (but not independently-targeted) warheads instead of one. The concept was to ensure a wider zone of destruction and overpressure then a single warhead detonation would create.
Ukrainian intercontinental ballistic missile.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 125,000/8,500 kg. Thrust 2,640.00 kN. Vacuum specific impulse 301 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 48,000/5,000 kg. Thrust 955.99 kN. Vacuum specific impulse 317 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 122,300/6,400 kg. Thrust 2,651.70 kN. Vacuum specific impulse 301 seconds. Verniers 4 x RD-68M, 285 kN, maximum 42 degree gimbal angle.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 49,300/3,700 kg. Thrust 940.40 kN. Vacuum specific impulse 317 seconds. Verniers 4 x RD-69M, 54.3 kN, maximum 50 degree gimbal angle.
Ukrainian intercontinental ballistic missile. The R-36M replaced the R-36 in 288 existing silos and was additionally installed in 20 new super-hardened silos.
The super-heavy Ukrainian R-36M ICBM replaced the R-36 in 288 existing silos and was additionally installed in 20 new super-hardened silos. The fall of the Soviet Union ended production and the need for replacement. Nevertheless they remained in Russian service into the 21st Century, some being modified for use as space launchers.
N2O4/UDMH rocket stage. 4522.00 kN (1,016,586 lbf) thrust. Mass 210,000 kg (462,971 lb).
R-36M2.
Manufacturer's designation for R-36M2 15A18M intercontinental ballistic missile.
N2O4/UDMH rocket stage. 760.00 kN (170,855 lbf) thrust. Mass 49,000 kg (108,027 lb).
Ukrainian intercontinental ballistic missile. The R-36M2 was the Soviet Union's answer to the American 'Star Wars' anti-ballistic missile system. It was unusually named 'Voevoda' (an old Russian word for the leader of an army) in recognition of its planned role. In the end, it was only deployed in very limited numbers before the end of the Cold War.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 161,520/13,620 kg. Thrust 4,523.00 kN. Vacuum specific impulse 318 seconds. Surplus ICBMs; failures based on ICBM tests through 1994.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 41,114/4,374 kg. Thrust 760.00 kN. Vacuum specific impulse 340 seconds. Surplus ICBMs; failures based on ICBM tests through 1994.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 4,266/2,356 kg. Thrust 18.60 kN. Vacuum specific impulse 317 seconds. Main engine could be throttled to 800 kgf.
Ukrainian intercontinental ballistic missile. Improved version of the R-36M with a new ten warhead MIRV bus, better guidance system, increased throw-weight, and increased range.
R-36MUTTKh.
Manufacturer's designation for R-36MU 15A18 intercontinental ballistic missile.
Ukrainian orbital missile. The R-36-O was the only orbiting military nuclear weapon ever deployed, although in order to remain legal under international treaties it was a 'fractional orbital' weapon. Although American infrared early warning satellites invalidated the 'surprise attack' component of the concept, 18 missiles were operational from 1969 to 1983.
R-36O 8K69.
Alternate designation for R-36-O orbital missile.
Ukrainian orbital missile.
R-38.
Russian intercontinental ballistic missile. Small, economical ICBM studied by Yangel as an alternative to Chelomei's UR-100. Both one and two stage variants were considered. Work ended when Yangel was ordered to concentrate on R-36.
R-39.
Russian submarine-launched ballistic missile. SLBM developed for use on Typhoon subs.
R-39.
SLBM developed for use on Typhoon subs.
Makeyev N2O4/UDMH rocket engine.
Makeyev N2O4/UDMH rocket engine.
Solid propellant rocket stage. Loaded mass 53,700 kg. Thrust 2,060.00 kN.
Russian submarine-launched ballistic missile. Improved version.
Russian submarine-launched ballistic missile.
R-3A.
Russian intermediate range ballistic missile. So much new technology was involved for the R-3 that it was deemed necessary to build an R-3A intermediate experimental rocket, based on the R-2. This would be flown to test new construction methods, guidance systems, and high energy propellants. The R-3A was specified in 1949 to have a 900 to 1000 km range with a payload of 1530 kg; an unfuelled mass of 4100 kg; 20,500 kg of propellants; and a lift-off thrust of 40 tonnes. The R-3A could also serve as a prototype for a more modest IRBM. Flight tests of the R-3A were scheduled for October 1951.
R-3A.
Lox/Alcohol propellant rocket stage. Loaded/empty mass 19,900/3,500 kg. Thrust 434.40 kN. Vacuum specific impulse 235 seconds. Further incremental upgrade of R-2. Payload 500 kg. Range 935 km. Developed from 1949 to October 1951. Cancelled, work combined with 8K14 development.
R-4.
Alternate designation for G-1 missile.
R-40.
Marquardt N2O4/MMH rocket engine. Thruster developed for Shuttle Orbiter orbit control. The orbiter had 38 long scarf, short scarf, or no scarf configurations, depending on the location.
Marquardt N2O4/MMH rocket engine. 3.870 kN. In Production. Isp=306s. Thruster developed for Shuttle Orbiter orbit control. The orbiter had 38 long scarf, short scarf, or no scarf configurations, depending on the location.
Redmond N2O4/MMH rocket engine. 4 kN. In Production. Isp=293s.
R-42.
Redmond N2O4/MMH rocket engine. 0.890 kN. In Production. Isp=303s.
R-46.
Ukrainian intercontinental ballistic missile. Super-heavy ICBM designed by Yangel in 1963-1966. The original R-56 super-booster concept consisted of clustered R-46's.
R-4D.
Marquardt N2O4/MMH rocket engine. 0.490 kN. Isp=312s. Developed as attitude control thruster for the Apollo Service and Lunar Modules in 1960s. In production for numerous satellites for apogee / perigee maneuvers, orbit adjustment, and attitude control.
R-5.
Russian intermediate range ballistic missile. The R-5 was the first Soviet missile to be armed with a nuclear warhead, the first for which the new southern facility at Dnepropetrovsk took over full design and production responsibility. It was also the end of the road in being the ultimate extrapolation of German V-2 technology. Later missiles of both Yangel and Korolev would use other propellants and engine designs.
R-5.
The R-5 was the first Soviet missile to be armed with a nuclear warhead, and the first for which the new southern facility at Dnepropetrovsk took over full design and production responsibility. The R-5 could deliver a 1425 kg warhead over a range of 1200 km, doubling the performance of the R-2. It was also the end of the road in being the ultimate extrapolation of German V-2 technology. Later missiles of both Yangel and Korolev would use other propellants and engine designs.
R-5.
Lox/Alcohol propellant rocket stage. Loaded/empty mass 27,250/3,250 kg. Thrust 479.22 kN. Vacuum specific impulse 244 seconds.
Russian intermediate range ballistic missile. Vertical launch version of the R-5 missile for geophysical experiments using the High-Altitude Automatic Geophysical Station nose cone originally flown on the R-11, equipped with a parachute recovery system. . Experiments carried in the gyro-stabilised payload included solar ultraviolet spectroscopes and x-ray pinhole cameras.
Russian surface-to-air missile. MiG design for an equivalent to the US Bomarc extremely long-range surface-to-air missile. Never got beyond the design stage.
R-56.
Ukrainian heavy-lift orbital launch vehicle. The R-56 was Yangel's ultimate superbooster design. Trade studies begun in 1962 resulted in a conventional tandem stage design capable of being transported on the Soviet canal system from the factory to the launch site, while still placing 40 metric tons into low earth orbit. However various Soviet government factions favored the much larger (and less practical) Korolev N1 or Chelomei UR-700 designs. Yangel made one last attempt to convince the government to sponsor a common approach to the lunar program, with different design bureaus concentrating on just one part of the mission, as the American's were doing. But his practical solutions obtained no traction, and further work on the R-56 was abandoned.
R-56.
The R-56 was Yangel's ultimate superbooster design. Trade studies begun in 1962 resulted in a conventional tandem stage design capable of being transported on the Soviet canal system from the factory to the launch site, while still placing 40 metric tons into low earth orbit. However various Soviet government factions favored the much larger (and less practical) Korolev N1 or Chelomei UR-700 designs. Yangel made one last attempt to convince the government to sponsor a common approach to the lunar program, with different design bureaus concentrating on just one part of the mission, as the American's were doing. But his practical solutions obtained no traction, and further work on the R-56 was abandoned.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 1,162,000/162,000 kg. Thrust 1,608.00 kN. Vacuum specific impulse 316 seconds.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 213,000/13,000 kg. Thrust 1,980.00 kN. Vacuum specific impulse 325 seconds.
N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 9,400/700 kg. Thrust 117.00 kN. Vacuum specific impulse 350 seconds. Empty mass estimated (rounded figures given in source material indicates impossible 9 tonnes gross with 8.7 tonnes propellant).
N2O4/UDMH propellant rocket stage. Loaded/empty mass 32,000/2,000 kg. Thrust 544.20 kN. Vacuum specific impulse 327 seconds. Empty mass estimated (rounded figures given in source material indicates impossible 31 tonnes gross with 30 tonnes propellant).
Notional Nitric acid/Kerosene rocket engine. 4412 kN. R-56 Blok A. Notional engines for polyblock R-56, immense booster/ICBM; planned range 16,000 km. payload 35,000 kg. Tsniimash has 1:10 structural simulation model. Isp=320s.
Notional Nitric acid/Kerosene rocket engine. 784 kN. R-56 Blok B. Notional engines for polyblock R-56, immense booster/ICBM; planned range 16,000 km. payload 35,000 kg. Tsniimash has 1:10 structural simulation model. Isp=330s.
Ukrainian heavy-lift orbital launch vehicle. One design approach considered for Yangel's R-56 superbooster of the 1960's was a polyblock design limited to rail transport restrictions (4 x 3.8 m diameter stages clustered together). Although a dynamic test model was built and tested at Tsniimash, Yangel finally reached the conclusion that a monoblock design was clearly superior to polyblock versions. Further work on the polyblock design was abandoned. Tsniimash exhibits in its small museum the 1:10 structural simulation model of the 3.8 m diameter polyblock design.
Ukrainian intercontinental ballistic missile. Tsniimash has 1:10 structural simulation model. Three stage carrier rocket with consecutive first and parallel second stages. Range indicated on placard; possibly considered as monster ICBM in competition with UR-500. Work began in 1961.
Nitric acid/Kerosene propellant rocket stage. Loaded/empty mass 222,000/18,000 kg. Thrust 4,410.00 kN. Vacuum specific impulse 320 seconds. Range 16,000 km. Payload 35,000 kg. Tsniimash has 1:10 structural simulation model. Three stage carrier rocket with consecutiveively divided first and paraell divided second stages. Work began in 1961. Chief designer Yangel. Source: Placard, TsNIIMASH.
Nitric acid/Kerosene propellant rocket stage. Loaded/empty mass 55,500/5,000 kg. Thrust 784.00 kN. Vacuum specific impulse 330 seconds.
R-5A.
Russian intermediate range ballistic missile. Vertical launch version of the R-5 missile for geophysical experiments retaining the nose cone of the IRBM, but equipped with a parachute recovery system. Experiments carried included solar ultraviolet spectroscopes, mass spectrometers for atmospheric composition studies, and capsules carrying dogs for zero-gravity biologically research.
R-5B.
Russian intermediate range ballistic missile.
R-5M.
Russian intermediate range ballistic missile. The R-5M was the first Soviet missile to be armed with a nuclear warhead, and the first to launch a live nuclear warhead in test. The technical characteristics were virtually the same as those of the R-5 basic model, except for an increase in the propellant load. 48 launchers were deployed from 1956 to 1968, tipped with nuclear warheads of 80 kiloton, 300 kiloton, or 1 megaton.
R-5V.
Russian intermediate range ballistic missile. Vertical launch version of the R-5 missile for geophysical experiments under the Vertikal international program, equipped with a spherical re-entry capsule and a parachute recovery system. A wide range of international astrophysics and geophysics instruments were carried.
R-6.
Alternate designation for G-2 intermediate range ballistic missile.
Chelomei N2O4/UDMH rocket engine. 132 kN. LK-1 Blok A. Developed 1964-66. Developed in cooperation with OKB-117 on the basis of the latter's main engine for the UR-100 stage II.
R-65.
Russian tactical ballistic rocket.
R-6C.
Marquardt N2O4/MMH rocket engine. 0.033 kN. In Production. Isp=290s.Derivative of Advent communications satellite thruster for Insat 1, Arbasat 1, and Olympus and HS-393 satellites.
R-7.
The world's first ICBM became the most often used and most reliable launch vehicle in history. The original core+four strap-on booster missile had a small third stage added to produce the Vostok launch vehicle, with a payload of 5 metric tons. Addition of a larger third stage produced the Voskhod/Soyuz vehicle, with a payload over 6 metric tons. Using this with a fourth stage, the resulting Molniya booster placed communications satellites and early lunar and planetary probes in higher energy trajectories. By the year 2000 over 1,628 had been launched with an unmatched success rate of 97.5% for production models. Improved models providing commercial launch services for international customers entered service in the new millenium, and a new launch pad at Kourou was to be inaugurated in 2011. It appeared that the R-7 could easily still be in service 70 years after its first launch.
R-7.
Russian intercontinental ballistic missile. The world's first ICBM and first orbital launch vehicle. The 8K71 version was never actually put into military service, being succeeded by the R-7A 8K74.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 43,100/3,500 kg. Thrust 970.00 kN. Vacuum specific impulse 306 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 95,300/7,500 kg. Thrust 912.00 kN. Vacuum specific impulse 308 seconds.
R-70.
Standard Russian tactical artillery rocket.
R-75.
Russian tactical ballistic rocket.
R-7A.
Russian intercontinental ballistic missile. The R-7A was an improved version of the R-7 first ICBM, and the one actually deployed to pads in Baikonur and Plesetsk. The missile saw service from 1960 to 1968. Four pads at Plesetsk, and one reserve pad at Baikonur, were operational at the peak of deployment in 1962. These were the Soviet Union's only strategic missile deterrent during the Cuban Missile Crisis.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 42,800/3,200 kg. Thrust 995.30 kN. Vacuum specific impulse 313 seconds.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 101,700/7,300 kg. Thrust 940.40 kN. Vacuum specific impulse 315 seconds.
R-8.
Alternate designation for G-3 intermediate range cruise missile.
R-8.
Russian intercontinental ballistic missile. Glushko project 1956 for multistage 650t ICBM powered by Lox/UDMH.
R-9.
Russian intercontinental ballistic missile. ICBM developed by Korolev OKB using liquid oxygen/kerosene propellants. The Soviet military favoured storable propellants as advocated by Glushko and implemented by Yangel and Chelomei. Development of the R-9 was protracted and it was deployed in only very limited numbers between 1964 and 1974.
R-9.
ICBM developed by Korolev OKB using liquid oxygen/kerosene propellants. The Soviet military favoured storable propellants as advocated by Glushko and implemented by Yangel and Chelomei. Development of the R-9 was protracted and it was deployed in only very limited numbers between 1964 and 1974.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 61,600/4,000 kg. Thrust 1,595.83 kN. Vacuum specific impulse 311.4 seconds. Payload 3,500 kg. Range 13,000 km. Accuracy (90%) 8 km in range and 5 km in dispersion with radio guidance; 20 km / 10 km with inertial guidance. Empty mass estimated.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 15,900/2,500 kg. Thrust 304.00 kN. Vacuum specific impulse 330 seconds. Empty mass estimated. Developed into Molniya/Soyuz second stage.
R-9A-N.
Manufacturer's designation for Desna intercontinental ballistic missile.
R-9M.
Russian intercontinental ballistic missile. Improved version with Kuznetsov engines in first and second stages. Development undertaken, but cancelled in favour of basic version with RD-111/RD-0106 engines.
RACE.
French agency. RACE, France.
Rachuk, Vladimir Sergeyevich Russian engineer. From 1993 General Director and Chief Designer of KBKhA. Designer of liquid propellant rocket engines.
rad.
Unit of absorbed dose of radiation equal to an energy of 100 ergs per gram of irradiated material
American logistics spacecraft. One launch, 1965.08.21, Gemini 5 REP. The Radar Evaluation Pod was a small reflecting target released from Gemini spacecraft to test the rendezvous radar.
Canadian earth resources radar satellite. Two launches, 1995.11.04 (Radarsat) and 2007.12.14 (Radarsat). Canada's Radarsat was a radar satellite featuring variable resolution, and different view angles at a number of preset positions.
American military target satellite. One launch, 1993.06.25. Radar calibration.
American military technology satellite. 2 launches, 1968.08.16 (Radcat) and 1972.10.02 (RADCAT). Space craft engaged in investigation of spaceflight techniques and technology.
French winged orbital launch vehicle. Two stage to orbit horizontal takeoff / horizontal landing vehicle. Booster would be powered by scramjets to Mach 12 separation before second stage separated.
Radiation Experiment.
Alternate designation for REX earth ionosphere satellite.
Radiation Meteoroid.
Alternate designation for RM earth micrometeoroid satellite.
Russian amateur radio communications satellite. 9 launches, 1978.10.26 (Radio Sputnik 1) to 1994.12.26 (Radio-ROSTO RS-15).
Radio Astronomy Explorer.
Alternate designation for RAE radio astronomy satellite.
Category of spacecraft.
American tracking network technology satellite. One launch, 1961.11.01, Mercury-Scout 1. Small satellite was to have verified the readiness of the worldwide Mercury tracking network
Russian communications satellite. Study 1991. The Radiobook network would utilize from 24 to 36 micro-satellites (10 kg or less) in a packet radio network, which could be launched with small boosters, including air-launched missiles.
An instrument for detecting and measuring radiant energy.
American manufacturer of rockets. Radioplane, USA.
American earth magnetosphere satellite. One launch, 1963.06.15. Radiation dosimeter measurements.
Radovskiy, Viktor Petrovich (1920-) Russian engineer. Deputy Chief Designer of OKB-456. Specialised in rocket engines and succeeded Glushko 1989.
American military technology satellite. One launch, 1972.10.02. Space craft engaged in investigation of spaceflight techniques and technology.
Raduga.
Code name for DS-P1-Yu military target satellite.
First Soviet geosynchronous communications satellite. Operational, first launch 1974.03.26. A single orbital group of two Radugas could handle all communications of the Russian eastern regions.
Russian manufacturer. Raduga Machine Design Bureau, Russia.
Russian communications satellite. 8 launches, 1989.06.21 (Raduga 1-1) to 2007.12.09 (Raduga-1). The Raduga-1 geosynchronous communications satellite was to have been the basis for the YeSSS-2 second generation Unified Satellite Communication System.
RAE.
American radio astronomy satellite. 2 launches, 1968.07.04 (Explorer 38) to 1973.06.10 (Explorer 49).
RAE.
British agency overseeing development of rockets and spacecraft. Royal Aerospace Establishment, UK.
British manned spaceplane. This Royal Aircraft Establishment Orbital Fighter proposal of the 1960's envisioned a two stage vehicle. A ramjet powered first stage would release a second stage orbiter similar to, but smaller than, the US Dynasoar.
British winged orbital launch vehicle. The Royal Aircraft Establishment Orbital Fighter proposal of the 1960's envisioned a two stage vehicle. A ramjet powered first stage would release a second stage orbiter similar to, but smaller than the U.S. X-20 Dyna-Soar. The spaceplane would utilise a gliding re-entry to return to earth.
British winged orbital launch vehicle. The Royal Aircraft Establishment Two Stage To Orbit (TSTO) Concept of the 1960's consisted of a hypersonic air-breathing first stage and rocket powered second stage.
RAF.
American agency. Royal Air Force, USA.
At this location the 8th RAF Strategic Missile Squadron operated 15 Thor IRBM launchers from 22 December 1959 to April 1963. They were withdrawn as part of the secret agreement between Kennedy and Khrushchev ending the Cuban missile crisis, under which all Thor missiles were to be removed from Europe.
At this location the 77th RAF Strategic Missile Squadron operated 15 Thor IRBM launchers from 15 June 22 1959 to 1 July 1963. They were withdrawn as part of the secret agreement between Kennedy and Khrushchev ending the Cuban missile crisis, under which all Thor missiles were to be removed from Europe.
At this location the 7th RAF Strategic Missile Squadron operated 15 Thor IRBM launchers from 11 Sept. 1959 to 15 May 1963. They were withdrawn as part of the secret agreement between Kennedy and Khrushchev ending the Cuban missile crisis, under which all Thor missiles were to be removed from Europe.
British pressure suit, operational 1955. The RAF Jerkin System comprised a pressure vest used with a P/Q mask and anti-G suit. Several variations included unsleeved, sleeved and integrated garments proven for short term protection to 18 km.
At this location the RAF No. 144 (Strategic Missile) Squadron operated 15 Thor IRBM launchers from 29 April 29 1960 to September 1963. The other units in the North Luffenham Thor complex were No. 218 (SM) Sqn at Harrington, Northamptonshire, No. 223 (SM) Sqn at Folkingham, Lincolnshire, No. 130 (SM) Sqn at Polebrook, Northamptonshire and No. 254 (SM) Sqn at Melton Mowbray, Leicestershire. They were withdrawn as part of the secret agreement between Kennedy and Khrushchev ending the Cuban missile crisis, under which all Thor missiles were to be removed from Europe.
Israeli manufacturer. Rafael Armaments (IAI), Israel.
Rafikov, Mars Zakirovich (1933-2000) Tatar-Russian pilot cosmonaut, 1960-1962.
Air-launched rocket drop zone known to have been used for 2 launches in 1968, reaching up to 81 kilometers altitude.
Raimann, Alfred German expert in aircraft and rockets during World War II. As of January 1947, living at Dresden-Neustadt, Hospitalstr. 15, Engg.
RAKA.
Russian agency overseeing development of spacecraft. Russian Aviation and Space Agency (Rosaviakosmos), Moscow, Russia.
The world's first rocket port, an abandoned German Army storage facility in the northern suburbs of Berlin. Used for 6 launches from 1931 to 1931, reaching up to 1 kilometer altitude.
Russian manned spaceplane. Developed from 1959, including suborbital hardware tests, before cancellation in 1964.
RAM.
Radio attenuation measurement (reentry communications blackout research); or Research and Applications Module (Spacelab forerunner)
RAM.
Family of launch vehicles.
RAM.
American all-solid orbital launch vehicle.
American all-solid orbital launch vehicle. Employed by NACA-Langley for accelerating aerodynamic models. Could lift 34 kg to 1271 km. 5 stage vehicle.
American all-solid orbital launch vehicle. Three stage vehicle consisting of 1 x Castor + 1 x Antares + 1 x Alcor
Sounding rocket launch site used in support of high-altitude monitoring after Project Argus nuclear tests. Six launches in 1958 reached up to 825 kilometers altitude.
Category of engines.
Ramon, Ilan (1954-2003) Jewish-Israeli pilot payload specialist astronaut. Flew on STS-107. First Israeli astronaut. Perished in Columbia shuttle disintegration during re-entry.
Rand.
American manufacturer of rockets and spacecraft. Rand, Santa Monica, CA, USA.
Ranger was originally to be a program of five unmanned lunar crasher spacecraft, intended to quickly obtain information on the lunar surface. The scientific objective would be to acquire and transmit a number of images of the lunar surface prior to impact, and to obtain data from a survivable package incorporating a lunar seismometer. The resulting spacecraft was much too ambitious for its period. After five consecutive failures, a simpler, picture-return-only spacecraft made three successful flights, returning the first closeup pictures of the lunar surface years behind schedule.
American lunar impact probe. 2 launches, 1961.08.23 (Ranger 1) to 1961.11.18 (Ranger 2).
American lunar lander. 3 launches, 1962.01.26 (Ranger 3) to 1962.10.18 (Ranger 5).
American lunar impact probe. 4 launches, 1964.01.30 (Ranger 6) to 1965.03.21 (Ranger 9). After a series of failures with the more ambitious early Ranger spacecraft, the design was simplified and the lander was deleted.
Rapp.
German manufacturer. Rapp, Germany.
Sounding rocket launch location known to have been used for 5 launches in 1965, reaching up to 270 kilometers altitude.
RAS.
Royal Astronomical Society
RASA.
Second Owner of RAKA
RASC.
Royal Astronomical Society of Canada
American air-to-surface missile, development started in 1946. Program cancelled in 1958. Project originated as Bell Aircraft Corp / AAF / Project MX-776. Requirement for a 160 km range air-launched guided missile was overcome by other technology during its protracted development.
American air-launched orbital launch vehicle. Expendable rocket air-launched from a supersonic aircraft with engines modified using a technology called Mass Injected Pre-Compressor Cooling (MIPCC), where a coolant such as water or liquid oxygen was added to the air at the engine inlet, allowing the engine to operate at higher altitudes than normally possible.
RascomStarQAF, Mauritius.
Russian manufacturer of rockets. Rashkov Design Bureau, Korolev, Russia.
Rashkov, Semen Yuvelevich Soviet Engineer. Soviet rocket engineer.
Raspletin, Aleksandr Andreyevich (1908-1967) Russian chief designer. Chief Designer 1953-1967 of KB-1. Contributed to the RORSAT, EORSAT, and ASAT programs.
A geometric pattern followed by the sending element of a detector system or by the electron beam of a television transmitter or receiver.
A gyroscope with one free gimbal axis ( precession axis ) . Motion around this axis is constrained by a spring. The second gimbal axis is tied to the spacecraft. An angular motion of the spacecraft around this axis produces an angular excursion of the precession axis against the spring force; the angle of excursion is proportional to the rate of angular rotation in radians per second.
American earth rover. Tested 1995. Robotic All Terrain Lunar Exploration Rover demonstrated the use of existing technology for lunar exploration missions.
RATO.
Rocket-assisted takeoff
Rau.
Rau, Hans German expert in aerodynamics during World War II. As of January 1947, working at Darmstadt.
Raushenbakh, Boris Viktorovich (1915-) Russian engineer. Department Chief 1960-1973 of Korolev design bureau. Specialised in guidance systems.
RO solid rocket engine family.
American sounding rocket. Single stage vehicle.
RO solid rocket engine. 44.5 kN.
RO solid rocket engine. 105 kN.
RO solid rocket engine. 44.5 kN.
RO solid rocket engine. 44.5 kN.
RO solid rocket engine. 52.5 kN.
RO solid rocket engine. 44.5 kN.
RO solid rocket engine. 50.1 kN.
Raynor, Harold American engineer, at North American 1945-1963. Under his leadership the Apollo manned spacecraft was taken through the crucial first 18 months of design and development.
American manufacturer of rockets and spacecraft. Raytheon, USA.
Rolls Royce turbofan engine. 29.4 kN. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=9900s. Used on L1011 launch aircraft for Pegasus, Pegasus XL. First flight 1990.
Rolls Royce air augmented rocket engine. 367.7 kN. Used Liquid Air/Lox/LH2. Development ended 1985. Isp=700s. Used on HOTOL launch vehicle.
RBCC.
Rocketdyne lox/lh2 rocket engine. Launch thrust 111.158 kN. Isp>400s. Rocket Based Combined-Cycle A5 Development Engine; integrated rocket, air-augmented rocket, ramjet, and sramjet propulsion elements into a single flowpath.
RBSS.
American winged orbital launch vehicle. The Recoverable Booster Space System was a plan circulated in the early 1960's to use the XB-70 as a recoverable supersonic first stage for a range of systems. The XB-70 would be capable of orbiting a 6800 kg payload, or an X-20 manned space glider.
RBV.
Return-beam-vidicon camera
Royal Canadian Artillery, Canada.
RCA.
American manufacturer of spacecraft. RCA, USA.
American agency. RCA Alas, USA.
American agency. RCA Amer, USA.
RCA Astro Electronics (1958-1986).
First Owner of East Windsor
RCAF.
RCAF.
RCI.
Rodent Cage Interface (for SLS mission)
RCS.
Reaction Control System
RD-.
Rocket engine (designation numbering series) (Russian abbreviation)
SKB-385 N2O4/UDMH rocket engine.
Makeyev N2O4/UDMH rocket engine.
Makeyev N2O4/UDMH rocket engine. 682 kN.
Makeyev N2O4/UDMH rocket engine.
Makeyev N2O4/UDMH rocket engine. 682 kN.
Makeyev N2O4/UDMH rocket engine.
Makeyev N2O4/UDMH rocket engine.
Makeyev N2O4/UDMH rocket engine.
OKB-1 solid rocket engine. 240 kN.
OKB-1 solid rocket engine. 500 kN.
MITT solid rocket engine.
MITT solid rocket engine.
MITT solid rocket engine. 245 kN.
Kosberg Lox/Alcohol rocket engine. 39.2 kN. E-50A aircraft by Mikoyan. Out of Production. Chamber pressure 42,7 - 22,1 bar. Specific impulse 255 - 248,5 sec. Isp=255s.
Kosberg Lox/Kerosene rocket engine. 39.2 kN. Yak-27V aircraft by Yakovlev. Out of Production. Based on RD-0101. Two ignitions possible. Chamber pressure 41,2 - 16,4 bar. Isp=260s.
Kosberg Lox/Kerosene rocket engine. 34.6 kN. T-3, P-1 aircraft by Sukhoy. Out of Production. Based on RD-0102. Chamber pressure 37.3 - 15.7 bar. Isp=277s.
Kosberg Lox/Kerosene rocket engine. 49.4 kN. Luna 8K72, Vostok 8K72 upper stage. Out of production. Isp=316s. Developed jointly with OKB-1 in nine months on the basis of OKB-1'ssteering chamber from the RD-107 engine. First flight 1958.
Kosberg Lox/Kerosene rocket engine. 304 kN. R-9 stage 2. Gas generator cycle. Isp=330s. First flight 1961.
Kosberg Lox/Kerosene rocket engine. 297.9 kN. R-9, Molniya 8K78, Voskhod 11A57 stage 3. Out of Production. Gas generator cycle. Isp=326s.
Kosberg Lox/Kerosene rocket engine. 297.9 kN. Voskhod 11A57, Molniya 8K78 stage 3. Isp=326s. First flight 1960.
Kosberg Lox/Kerosene rocket engine. 54.520 kN. 8A92 Vostok stage 3, 8K72K stage 3 (block E-Vostok). Out of production. Developed in 15 months. Isp=323s. First flight 1960.
Kosberg Lox/Kerosene rocket engine family. Soyuz 11A511, Molniya-M 8K78M. Precursor RD-0107 used in 11A57 Voskhod stage 2.
Kosberg Lox/Kerosene rocket engine. 297.9 kN. Soyuz 11A511, Molniya-M 8K78M. Precursor RD-0107 used in 11A57 Voskhod stage 2. Modified to increase reliability. Isp=326s. First flight 1964.
Kosberg Lox/LNG rocket engine. 245 kN. Developed 1994-on. Prototype engine for tests with propellants LOX/liquified natural gas. Tests performed from 30 April 1998 on, test duration 20s.
Kosberg lox/lh2 rocket engine family. Energia core stage. First operational Russian cryogenic engine system, built to the same overall performance specifications as America's SSME, but using superior Russian technology.
Kosberg lox/lh2 rocket engine. 1961 kN. Energia core stage. Design 1987. Isp=455s. First operational Russian cryogenic engine system, built to the same overall performance specifications as America's SSME, but using superior Russian technology.
Kosberg Lox/LCH4 rocket engine. 1576 kN. Design concept 1990's. Proposed variant of the RD-0120 engine using liquid methane instead of hydrogen as propellant. Isp=363s.
Kosberg lox/lh2 rocket engine. 1961 kN. Energia-M core stage. Development ended 1993. Isp=455s. From 1987 KBKhA worked on upgrading the 11D122 (RD-0120) engine for Energia-M launcher, including the possibility to throttle the engine down to 28% thrust.
Kosberg Lox/LCH4 rocket engine. 1720 kN. Design concept 1990's. Proposed variant of the RD-0120M engine using liquid methane instead of hydrogen as propellant. Isp=372s.
Kosberg tri-propellant (lox/lh2/kerosene) rocket engine. 1317 kN. Developed 1990's. Isp=419 / 452s. Experimental version of the RD-0120 engine. Tested by supply of high-pressure kerosene from test bench or adapted existing kerosene pump for tests.
Kosberg lox/lh2 rocket engine. 2313 kN. Energia-M core stage. Planned for Angara central stage. Developed 1990-. Isp=460s. Upgrade of RD-0120 engine for Energia-M launcher with increased thrust. Prototype from RD-0120 hardware.
Kosberg Lox/Kerosene rocket engine family. Engine to succeed RD-0110 in second stage of Soyuz. Proposed for small launcher Kvant-1 by RKK Energia for stage 1 steering engine. Also proposed by RKK Energia in initial studies in 1993 for Angara upper stage.
Kosberg Lox/Kerosene rocket engine. 294.3 kN. In development. Isp=359s. Engine to succeed RD-0110 in second stage of Soyuz. Used staged combustion; chamber pressure increased from 70 to 160 bar, specific impulse from 326 to 359 seconds First flight 2001.
Kosberg Lox/Kerosene rocket engine. 298.640 kN. Propoed in 1993 for Angara stage 2 verniers, Kvant-1 stage 1 vernier. Designed 1986-1990. Isp=331s. Variant of RD-0124 with shortened nozzle for sea-level operation.
Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber. Isp=348s.
Kosberg Lox/Kerosene rocket engine. 294.3 kN. Developed 1998-. Proposed single chamber variant of RD-0124. Obviously same turbopumps, but one single chamber with larger nozzle extension compared to RD-0124M. Isp=359s.
Kosberg lox/lh2 rocket engine family. Space tugs or upper stage for Onega or Yastreb versions of Soyuz.
Kosberg lox/lh2 rocket engine. 39.2 kN. Space tugs or upper stage for Onega or Yastreb versions of Soyuz. Isp=476s. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Design concept 1993. Hot-tests in 1998.
Kosberg lox/lh2 rocket engine. 98 kN. Upper stages. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump. Isp=476s.
Kosberg lox/lh2 rocket engine. 39.2 kN. Upper stages. Design concept 1998-. Concept for a cryogenic engine for upper stages. Single annular chamber with straight expansion nozzle, common turbopump. Isp=472s.
Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. One single chamber with bell nozzle, separate turbopumps. Isp=474s.
Kosberg Lox/LCH4 rocket engine. Developed 1990s.
Bondaryuk ramjet engine. 76 kN. Burya. Out of production. 1.2 m diameter ramjet to be used in Burya cruise missile. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1500s. First flight 1957.
Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump. Isp=467s.
Kosberg lox/lh2 rocket engine family. Concept for a cryogenic engine for upper stages.
Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Derived from RD-0131, but four chambers with bell nozzles, common turbopump. Isp=469s.
Kosberg Lox/LNG rocket engine. 98 kN. Vozdushnyy Start stage 2. Design concept 1998-. Proposed variant of RD-0132, replacing hydrogen by liquid natural gas. Initially selected for stage 2 of Vozdushnyy Start project by Kompomash.
Kosberg lox/lh2 rocket engine. 98 kN. upper stage. Design concept 1996-. Concept for a cryogenic engine for upper stages. Four chambers with bell nozzles, common turbopump. Isp=467s.
Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle variant of RD-0139. Isp=358s.
Kosberg Lox/LNG rocket engine. 2038 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=341s.
Kosberg Lox/LNG rocket engine. 2086 kN. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Gas generator cycle with turbine gas injection into supersonic nozzle. Isp=349s.
Kosberg Lox/LNG rocket engine. 2251 kN. stage 1. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle. Isp=353s.
Kosberg Lox/LNG rocket engine. 2353 kN. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle. Isp=369s.
Kosberg Lox/LNG rocket engine family. Vozdushnyy Start stage 2.
Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 2. Design concept 1998-. Proposed variant of RD-0124, replacing kerosene by liquid natural gas. Selected for stage 2 of Vozdushnyy Start project by Kompomash. Isp=372s.
Kosberg Lox/LNG rocket engine. 343 kN. Vozdushnyy Start stage 1. Design concept 1998-. Proposed single chamber variant of RD-0143. Selected for stage 1 of Vozdushnyy Start project by Kompomash. Isp=370s.
Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Radiation cooled nozzle extension. Isp=374s.
Kosberg Lox/LNG rocket engine. 147 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Four-chamber variant of RD-0144. Isp=374s.
Kosberg lox/lh2 rocket engine. 98.1 kN. Centaur upper stage (Atlas); high performance upper stages for Onega, Proton, Angara launch vehicles. Design concept 1998-. Isp=463s.
Kosberg Lox/LNG rocket engine. 49 kN. upper stage. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Variant of RD-0141 with larger nozzle. Isp=370s.
Kosberg Lox/Kerosene rocket engine. 294.3 kN. Design concept 2007. Engine proposed to replace RD-110 in Avrora improved version of Soyuz launch vehicle. The single chamber engine had a deployable nozzle extension for improved vacuum specific impulse.
Kosberg Lox/Kerosene rocket engine. Design concept 2007. Launch thrust 902.5 kN. Engine proposed to replace RD-107 in Onega and Avrora versions of the Soyuz launch vehicle.
Bondaryuk ramjet engine. 98 kN. Buran missile, early version. Out of Production. Isp=1500s. 1.8 m diameter ramjet engine initially considered for Buran M-42. RD-020 adpopted later during development.
Bondaryuk ramjet engine. 103 kN. Buran M-42. Development ended 1957. Isp=1500s. Ramjet for Buran cruise missile. 8,500 km cruise at Mach 3.1 at 18-20 km altitude.
Kosberg Nitric acid/Amine rocket engine. 58.8 kN. Lavochkin SAM, flew 1960. Out of Production. First liquid rocket engine by OKB-154, evolution of Isayev S2.1200 transferred to Kosberg. Thrust range 59 - 5.9 kN. Sea level specific impulse 230 - 166 sec
Kosberg Nitric acid/Amine rocket engine. 58.060 kN. SAM V1100 by Grushin stage 3. Out of Production. Thrust range 59 - 28 kN. Isp=260s. First flight 1960.
Kosberg N2O4/UDMH rocket engine. 2236 kN. UR-200 stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0204 for tank pressurization and three RD-0203. Isp=311s. First flight 1963.
Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. DU consisting of 4 RD-0204 gimballed motors. Staged combustion cycle. Isp=311s. First flight 1964.
Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. Diameter is per chamber. Staged combustion cycle. Variant of RD-0203 with additional pressure sensor. Isp=311s. First flight 1964.
Kosberg N2O4/UDMH rocket engine. 606.4 kN. UR-200 stage 2. Engine unit consisting of 1 RD-0206 maine engine and 4 RD-0207 vernier/steering engines. Version of 8D44 and 8D45 with extended nozzle. Developed 1961. Isp=322s. First flight 1963.
Kosberg N2O4/UDMH rocket engine. 575.5 kN. UR-200 stage 2. Developed 1961-64. Staged combustion cycle. Isp=326s. First flight 1964.
Kosberg N2O4/UDMH rocket engine. 30.9 kN. UR-200 stage 2 vernier. Developed 1961-64. Gas generator cycle. Four vernier thrusters. Isp=297s. First flight 1964.
Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Stage 1 had three RD-0208 plus one RD-0209. Further developed into RD-0210.
Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Engine unit consisting of 1 RD-0211 for tank pressurization and three RD-0210. Modification of RD-0208 with tank pressurization. Further developed into RD--0211. First flight 1965.
Kosberg N2O4/UDMH rocket engine family. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210).
Kosberg N2O4/UDMH rocket engine. 582.1 kN. Isp=326s. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle. First flight 1965.
Kosberg Lox/Kerosene rocket engine. 592 kN. Design concept 1990's. Proposed variant of RD-0210 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=342s.
Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 2. Out of Production. Variant of RD-0210 providing tank pressurization. Staged combustion cycle. Isp=326s.
Kosberg N2O4/UDMH rocket engine. 613 kN. Proton stage 3. Engine unit consisting of 1 RD-0213 maine engine and 4 RD-0214 vernier/steering engines. 8D48 essentially similar to 8D411 and 8D412 and has the same combustion chamber. Isp=324s. First flight 1967.
Kosberg N2O4/UDMH rocket engine. 582.1 kN. Proton stage 3. Design 1962. Version of RD-0210. Staged combustion cycle (Oxidizer pre-burner gas routed to main chamber after driving turbine). Main engine for Proton Stage 3 in system RD-0212. Isp=326s.
Kosberg N2O4/UDMH rocket engine. 30.980 kN. Proton stage 3 vernier. In Production. Based on RD-0207. Four used as steering engines for Proton Stage 3 in system RD-0212. Isp=293s. First flight 1967.
Kosberg N2O4/UDMH rocket engine. 2450 kN. Developed 1962-65 for heavy Chelomei launcher (UR-900?) stage 1. Isp=310s. Engine unit consisting of 1 RD-0217 for tank pressurization and three RD-0216. Hardware not hot-tested.
Kosberg N2O4/UDMH rocket engine. 219 kN. UR-100 stage 1. Isp=313s. Staged combustion cycle. Includes tank pressurization system (RD-0217 without tank press.). First launch November 1963, manufactured until 1974, operational until 1991. First flight 1965.
Kosberg N2O4/UDMH rocket engine. 219 kN. UR-100, UR-100K stage 1. Out of Production. Staged combustion cycle. Version of RD-0216 without tank pressurization system. Manufacturing until 1974, operational use until 1991. Isp=313s.
Kosberg N2O4/UDMH rocket engine. 78 kN. upper stage of unnamed missile by Mishin. Developed 1965-70. Isp=330s.
Kosberg N2O4/UDMH rocket engine. 3.923 kN. Almaz space station orbital maneuvering. Hardware. Originally designed for UR-100 follow-ons spaceships. Two engines used on Almaz space station for orbital maneuvering, Pressure fed. Isp=287s. First flight 1974.
Kosberg N2O4/UDMH rocket engine. 755 kN. R-36M / RS-20A (SS-18 mod-1) stage 2. Out of Production. Comprises single-chamber main engine RD-0229 plus four-chamber steering engine RD-0230. Further developed to RD-0255.
Kosberg N2O4/UDMH rocket engine family. R-36M / Ikar launch vehicle.
Kosberg N2O4/UDMH rocket engine. R-36M / RS-20A (SS-18 mod-1) stage 2. Out of Production. Main engine. Staged combustion cycle. Used on Ikar launch vehicle. First flight 1974.
Kosberg Lox/LNG rocket engine. 883 kN. Vozdushnyy Start stage 1. Developed 1997. Derivative of RD-0229 for the propellants LOX and liquid natural gas (methane). Initial candidate for stage 1 propulsion of Vozdushnyy Start project by Kompomash.
Kosberg N2O4/UDMH rocket engine. R-36M / RS-20A (SS-18 mod-1) stage 2 vernier. Out of Production. Vernier engine. Gas generator cycle. First flight 1974.
Kosberg N2O4/UDMH rocket engine. 29 kN. P-700 Granit. Out of Production. Staged combustion cycle. Isp=275s. First flight 1970.
Kosberg N2O4/UDMH rocket engine. UR-100N / Rokot Stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0234 for tank pressurization and three RD-0233. First flight 1972.
RD-0232?.
Manufacturer's designation of RD-0232 N2O4-UDMH rocket engine.
Kosberg N2O4/UDMH rocket engine. 520 kN. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. Isp=310s. First flight 1974.
Kosberg N2O4/UDMH rocket engine family. UR-100N.
Kosberg N2O4/UDMH rocket engine. 520 kN. UR-100N / RS-18 (SS-19) stage 1. Out of Production. Staged combustion cycle. Modification of RD-0233 including tank pressurization system. Isp=310s. First flight 1974.
Kosberg Lox/LCH4 rocket engine. 442 kN. Developed 1996-. Proposed variant of RD-0234 engine using LOX-liquid methane instead of N2O4/UDMH as propellants. Isp=343s.
Kosberg Lox/Kerosene rocket engine. 516 kN. Developed 1996-. Proposed variant of RD-0234 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=331s.
Kosberg N2O4/UDMH rocket engine. 240 kN. UR-100N / RS-18 (SS-19) stage 2. Main engine based on RD-0217 with larger nozzle for altitude operation. Staged combustion cycle. Isp=320s. First flight 1972.
Kosberg N2O4/UDMH rocket engine. 15.760 kN. UR-100N / RS-18 (SS-19) stage 2 vernier. Out of Production. Developed in 1969-1974 / problems not solved until 1978. Vernier engines. Gas generator cycle. Isp=293s.
Kosberg N2O4/UDMH rocket engine. 4.9 kN. UR-100N / RS-18 (SS-19) stage 3. MIRV service block. Open cycle. Analogous to RD-0225, pressure fed. Steering engine for space vehicles gimbaling +/- 45 degree. Isp=200s. First flight 1972.
Kosberg N2O4/UDMH rocket engine family. Sea-based missile booster stages developed 1977-83.
Kosberg N2O4/UDMH rocket engine. 123.6 kN. sea-based missile booster stage developed 1977-83. Isp=302s. First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. Single ignition, 297 development tests. 50 engines for sale.
Kosberg Lox/Kerosene rocket engine. 125 kN. Developed 1998-. Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=312s.
Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998-. Isp=335s. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH. Reusable for 6 ignitions total. Throttling to 80%.
Kosberg N2O4/MMH rocket engine. 98.1 kN. Design concept 1998-. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market ?). Reusable for 6 ignitions total. Throttling to 80%. Isp=343s.
Kosberg N2O4/UDMH rocket engine. 825.8 kN. R-29RM stage 1. Out of Production. Isp=300s. Consisted pf single-chamber main engine RD-0244 plus four-chamber steering engines RD-0245 driven by turbine exhaust gas. Engine submerged in propellant tank.
Kosberg N2O4/UDMH rocket engine family. R-29RM stage 1. Submerged in propellant tank.
Kosberg N2O4/UDMH rocket engine. 682 kN. R-29RM / RSM-54 (SS-N-23) stage 1. Out of Production. Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank. Isp=310s. First flight 1985.
RD-0244 KD.
Alternate designation for RD-0244-HC Lox-Kerosene rocket engine.
Kosberg Lox/Kerosene rocket engine. 690 kN. Design concept 1990's. Proposed variant of RD-0244 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=332s.
Kosberg N2O4/UDMH rocket engine family. R-29RM stage 1 vernier.
Kosberg N2O4/UDMH rocket engine. 211 kN. R-29RM / RSM-54 (SS-N-23) stage 1 vernier. Out of Production. Four-chamber steering engine in system RD-0243 driven by turbine exhaust gas. Isp=300s. First flight 1985.
Kosberg Lox/Kerosene rocket engine. 214 kN. Design concept 1990's. Proposed variant of RD-0245 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=320s.
Kosberg N2O4/UDMH rocket engine. Design concept. Project for further development of RD-0243.
Kosberg N2O4/UDMH rocket engine. Further development of RD-0235 main engine for projected modification of stage 2 of classified Chelomei rocket. Development ceased during study phase. Staged combustion cycle.
Kosberg N2O4/UDMH rocket engine. Further development of RD-0236 steering engine for projected modification of stage 2 of classified Chelomei rocket. Development ceased during study phase. Gas generator cycle.
Kosberg N2O4/UDMH rocket engine. 755 kN. R-36M2 / RS-20V (SS-18 Mod-4) stage 2. Comprises of single-chamber main engine RD-0256 plus four-chamber steering engines RD-0257. Development based on RD-0228 with thrust increase by 11%. First flight 1986.
Kosberg N2O4/UDMH rocket engine family. R-36M2 stage 2.
Kosberg N2O4/UDMH rocket engine. R-36M2 / RS-20V (SS-18 Mod-4) stage 2. Out of Production. Main engine of system RD-0255. Staged combustion cycle. First flight 1987.
Kosberg Lox/Kerosene rocket engine. 820 kN. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-kerosene instead of N2O4/UDMH as propellants. Isp=344s.
RD-0256-Methan.
Manufacturer's designation of RD-0256-Methane Lox-LCH4 rocket engine.
Kosberg Lox/LCH4 rocket engine. 836 kN. Design concept 1996-. Proposed variant of RD-0256 engine using LOX-liquid methane instead of N2O4/UDMH as propellants. Isp=353s.
Kosberg N2O4/UDMH rocket engine. R-36M2 / RS-20V (SS-18 Mod-4) stage 2 vernier. Out of Production. Steering engine of system RD-0255. Gas generator cycle. First flight 1987.
Kosberg nuclear/lh2 rocket engine. 35.3 kN. Experimental nuclear engine, propellant LH2. Developed 1965-94. Isp=910s. Tested at Semipalatinsk test range in 1980s and was "the only operational nuclear engine in the USSR". First flight 1985.
Kosberg nuclear/lh2 rocket engine. 392 kN. Full-size nuclear thermal engine. Design concept 1965-94. Planned full-size nuclear thermal engine for Mars expeditions. Never progressed beyond study stage. Isp=900s.
Kosberg laser rocket engine. Space station "Skif". Developed 1970-85. Gas dynamic laser. Working medium gaseous carbon monoxide + air + nitrogen + ethanol. Flow rate up to 100 kg/s. Tests were performed at NII TP.
RD-0650TF.
Alternate designation for RD-0750 Lox-Kerosene-LH2 rocket engine.
Kosberg lox/lh2/kerosene rocket engine. 1412 kN. Alternative for Angara central stage, MAKS. Developed 1997-. Isp=455s. Tripropellant derivative of RD-0120. Some components tested in RD-0120TD technology demonstration in cooperation with Aerojet.
RD-1.
Glushko Nitric acid/Kerosene rocket engine family. Take-off acelleration of Pe-2, La-7, Yak-3, Su-6 airplanes. Developed 1941-45. First Russian liquid propellant rocket engine family. Production 1944-45.
RD-1.
Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. Take-off acelleration of Pe-2, La-7, Yak-3, Su-6 airplanes. Developed 1941-45. First Russian liquid propellant rocket engine. Production 1944-45. Ignition was by an ethane-air mixture. Isp=200s.
Glushko Lox/Alcohol rocket engine. 304 kN. R-1, V-1A. Isp=237s. Russian copy of the V-2 engine using Russian materials - which made it very difficult! German rocket scientists assisted in its development. First flight 1948.
Glushko Lox/Alcohol rocket engine. 404 kN. R-2 and V-2A. Isp=237s. Developed simultaneously with the RD-100 but with no German involvement. More compact, increased thrust, increased chamber pressure and higher alcohol concentration. First flight 1949.
Glushko Lox/Alcohol rocket engine. 428 kN. R-3A. Development ended 1951. Project for R-3A experimental missile. Stopped in favor of RD-103. Isp=235s.
RD-102?.
Alternate designation for RD-3A rocket engine.
Glushko Lox/Alcohol rocket engine family. Final extrapolation of the V-2 rocket engine in Russia. First flight 1953. Designer at OKB-456 was V A Vitkin.
Glushko Lox/Alcohol rocket engine. 500 kN. R-5. Out of Production. Isp=243s. Final extrapolation of the V-2 rocket engine in Russia. First flight 1953.
Glushko Lox/Alcohol rocket engine. 500.1 kN. R-5M 8K51. Isp=248s. First flight 1953.
Glushko Lox/Alcohol rocket engine. M5RD. Out of Production.
Glushko Lox/Kerosene rocket engine. 627.6 kN. R-7 ICBM stage 1 (strap-on) initial project. Out of Production. Isp=302s. Single chamber engine intended for the R-7 strap-ons in mid-1950s. Subsequently replaced by the 4 chamber RD-107.
Glushko Lox/Kerosene rocket engine. 645.3 kN. R-7 ICBM stage 2 (core) initial project. Out of Production. Isp=310s. Single chamber engine intended for the R-7 sustainer. Version of RD-105 with larger nozzle. Subsequently replaced by the 4 chamber RD-108.
Glushko Lox/Kerosene rocket engine family used on R-7 and subsequent booster stages (including Molniya, Soyuz in 21st Century). First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's.
Glushko Lox/Kerosene rocket engine. 992 kN. Soyuz 11A511-0, Soyuz 11A511U-0. Design 2000. Diameter is per chamber. Isp=314s. First flight 1965.
Glushko Lox/Kerosene rocket engine. 996.4 kN. Soyuz 11A511U2-0. Out of production. OKB Glushko. Used on 11A511U2 Stage 0. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=314s. First flight 1982.
Glushko Lox/Kerosene rocket engine. 996 kN. Molniya 0, Molniya 8K78M-0. OKB Glushko. Used on Molniya 8K78M and 11A57 Stage 0. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=314s. First flight 1964.
Glushko Lox/Kerosene rocket engine. 971 kN. R-7 8K71, Vostok 8K72, Vostok 8K72K strap-ons. Isp=306s. First flight 1957. Used four combustion chambers fed by single turbopump to circumvent combustion instability problems with larger chambers 1950's.
Glushko Lox/Kerosene rocket engine. 996 kN. Luna 8K72-0. Out of production. Diameter is per chamber. Isp=312s. First flight 1958.
Glushko Lox/Kerosene rocket engine. 996 kN. Out of production. Diameter is per chamber. Isp=313s. Used on Vostok 8K72K launch vehicle. First flight 1960.
Glushko Lox/Kerosene rocket engine. 996 kN. Developed in 1957-1960. Used in strap-ons for Molniya 8K78, R-7A 8K74, Voskhod 11A57, Vostok 8A92, Vostok 8A92M. Isp=313s. Fuel T-1 or RG-1 kerosene. First flight 1959.
Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8K71PS-0. Out of Production. OKB Glushko. Used on 8K71PS Stage 0. Developed in 1956-1957. Flown 1957-1958. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=306s.
Glushko Lox/Kerosene rocket engine. 971 kN. Sputnik 8A91-0. Out of Production. OKB Glushko. Used on 8A91 Stage 0. Developed in 1956-1957. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=310s. First flight 1958.
Glushko Lox/Kerosene rocket engine family.
Glushko Lox/Kerosene rocket engine. 997 kN. Soyuz 11A511-1, Soyuz 11A511U-1. Design 2000. Diameter is per chamber. Isp=315s. First flight 1965.
Glushko Lox/Kerosene rocket engine. 1011 kN. Soyuz 11A511U2-1. Out of production. Isp=319s. A 1-2 second specific impulse increase was made possible by the use of synthetic fuel Sintin and a modified mixing head. First flight 1982.
Glushko Lox/Kerosene rocket engine. 977 kN. Molniya 1, Molniya 8K78M-1. OKB Glushko. Used on Molniya 8K78L, 8K78M and 11A57 Stage 1. Propellants kerosene (RG-1 or T-1) / Lox. Diameter is per chamber. Isp=316s. First flight 1964.
Glushko Lox/Kerosene rocket engine. 976 kN. Molniya 8K78-3. Out of Production. Isp=316s.
Glushko Lox/Kerosene rocket engine. 912 kN. R-7 8K71-1, Vostok 8K72-1, Vostok 8K72K-1. OKB Glushko. Used on 8K71 R-7 Stage 1. Developed in 1954-1955. Propellants kerosene (RG-1) / Lox. Diameter is per chamber. Isp=308s. First flight 1957.
Glushko Lox/Kerosene rocket engine. 941 kN. Luna 8K72-1. Out of production. Diameter is per chamber. Isp=315s. First flight 1958.
Glushko Lox/Kerosene rocket engine. 941 kN. Out of production. Further development of 8D74-1958, 1958-1959. Diameter is per chamber. Isp=315s. Used on Vostok 8K72K launch vehicle. First flight 1960.
Glushko Lox/Kerosene rocket engine. 941 kN. Molniya 8K78-1, R-7A 8K74-1, Voskhod 11A57-1, Vostok 8A92-1, Vostok 8A92M-1. Diameter is per chamber. Isp=315s. First flight 1959.
Glushko Lox/Kerosene rocket engine. 912 kN. Sputnik 8K71PS-1. Out of Production. Diameter is per chamber. Isp=308s. First flight 1957.
Glushko Lox/Kerosene rocket engine. 804 kN. Sputnik 8A91-1. Out of Production. Diameter is per chamber. Isp=315s. First flight 1958.
Glushko lox/udmh rocket engine. 101.6 kN. Developed 1957-60. Isp=334s. Intended for second stage of Lox/UDMH 8K73 version of R-7. Abandoned because of Korolev's refusal to use such a toxic fuel. Later basis for RD-119 used on the Kosmos space launcher.
Glushko Lox/Kerosene rocket engine. 1374 kN. Development ended 1949. Isp=285s. For R-3 IRBM, 19 ED-140 7 tonne chambers used as preburners to feed a main mixing chamber, a scale-up of the V-2 production motor. Tested, but technical problems too severe.
Glushko Lox/Kerosene rocket engine. 1628 kN. R-9 stage 1. Isp=317s. Developed for R-9 ICBM. It had special flexible pipelines and gimbals, allowing lox loading in 20 minutes. First flight 1961.
Glushko lox/udmh rocket engine. 1089 kN. ICBM stage 1 (stage 2 was RD-113). Developed 1960. Isp=344s.
Glushko lox/udmh rocket engine. 1138 kN. ICBM stage 2 (stage 1 was RD-112). Developed 1960. Upper stage version of RD-112 with larger nozzle. Isp=360s.
Glushko lox/udmh rocket engine. 1653 kN. Used in ICBM stage 1 (stage 2 was RD-115). Developed 1961-65. Isp=341s.
Glushko lox/udmh rocket engine. 1726 kN. ICBM stage 2 (stage 1 was RD-114). Developed 1961-65. Upper stage version of RD-114 with larger nozzle. Isp=357s.
Glushko Lox/Kerosene rocket engine family. Update of RD-107. Little performance change from RD-107, changes may mainly relate to use of all-Russian components.
Glushko Lox/Kerosene rocket engine. 1021.097 kN. Soyuz ST stage 1. In production. Update of RD-107. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. Isp=310s. First flown 2001.
Glushko Lox/Kerosene rocket engine. manned Soyuz-launcher stage 1. Design concept. Update of RD-107. Probably version using Sintin instead of kerosene.
Glushko Lox/Kerosene rocket engine. 999.601 kN. In production. Isp=311s. Update of RD-107, used in Soyuz ST launcher. Little performance change from RD-107, changes may mainly relate to use of all-Russian components. First flight 2001.
Glushko lox/udmh rocket engine. 105.5 kN. Kosmos 1 stage 2. Out of production. Isp=352s. Derived from RD-109 motor originally intended for the second stage of a Lox/UDMH version of the R-7. First flight 1961.
Glushko Lox/Kerosene rocket engine family. High altitude engine used in the Zenit second stage.
Glushko Lox/Kerosene rocket engine. 833 kN. Zenit stage 2. In production. Isp=350s. High altitude engine used in the Zenit second stage. First production Russian engine to be test fired in the United States (3 test burns were made). First flight 1985.
Glushko Lox/Kerosene rocket engine. 784 kN. Design concept. Isp=329s.
Glushko Lox/Kerosene rocket engine. 882 kN. Design concept. Isp=353s.
Glushko Lox/Kerosene rocket engine. 873 kN. Soyuz M stage 1, 2. Proposed for X-34. Isp=336s. Sea-level variant of RD-120. As of 1996 RD-120 prototype with 1.8 m diameter had been built, development time estimated for three years.
RD-120M.
Alternate designation for RD-182 Lox-LCH4 rocket engine.
Glushko Lox/Kerosene rocket engine. 850.4 kN. PacAstro-2 stage 1. Out of Production. Sea-level variant of RD-120 engine, similar to RD-120K. Gimbaling +/- 6 degree in two planes. Isp=330s.
RD-123.
Yuzhnoye solid rocket engine. Maneuvering vehicle bang-bang propulsion, consisted of 25 small solid-propellant motors, probably for homing vehicles or multiple warhead dispensing applications.
Glushko Lox/Kerosene rocket engine family. Proposed upper stage engine.
Glushko Lox/Kerosene rocket engine. 343 kN. upper stage. Design concept. Isp=357s. Proposed upper stage kerosene engine. Gimbaling +/- 3 degree in two planes. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400.
Glushko Lox/Kerosene rocket engine. 343 kN. Angara stage 2 vernier. Design concept 1993-on. Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG-1.
Glushko lox/lh2 rocket engine. upper stage. Developed -1976. Experimental cryogenic engine. (Ref. May be not correct.)
Glushko Lox/Kerosene rocket engine. 883 kN. Angara stage 2. Design concept 1993-on. Sea-level variant of RD-120 engine. Proposed in initial study for Angara by RKK Energia in1993. Kerosene RG-1.
Glushko Lox/LCH4 rocket engine. 19.6 kN. Upper stage. Developed 1993-1996. Isp=380s. Methane version of lox / kerosene upper stage engine RD-161. Gimbaling +/- 6 degree in two planes.
Glushko H2O2/Kerosene rocket engine. Proposed for use on Soyuz M-3.
RD-161 (1).
Manufacturer's designation of RD-161-1 Lox-Kerosene rocket engine.
RD-161 (2).
Manufacturer's designation of RD-161-2 Lox-Kerosene rocket engine.
Glushko Lox/Kerosene rocket engine. 19.6 kN. Development ended 2000. Proposed for use on Soyuz M-3. Basic version. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=360s.
Glushko Lox/Kerosene rocket engine. 19.9 kN. Design concept 1990's. Proposed for use on Soyuz M-3. Version with uncooled nozzle extension. Engine Cycle: closed gas generator. Feed Method: turbopump. Isp=365s.
Glushko H2O2/Kerosene rocket engine. 24.5 kN. Soyuz M stage 3 (block LM). Developed 1993-. Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%. Isp=319s.
Glushko Lox/LCH4 rocket engine. 353 kN. Upper stage. Design concept 1990's. Isp=379s. Proposed upper stage engine, a methane variant of RD-134. Gimbaling +/- 3 degree in two planes. Four chambers with one common turbopump.
Glushko Lox/LCH4 rocket engine. 167 kN. Riksha-0 stage 1. Design concept 1990's. Isp=351s. LOX/Methane engine derived from RD-120. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead.
Glushko Lox/Kerosene rocket engine. 7903 kN. Energia strap-on. Developed 1973-1985. Isp=337s. First flight 1987. Used one-plane gimablling versus the two-plane gimablling required on the RD-171 of the Zenit launch vehicle. Designed for 10 reuses.
Glushko Lox/Kerosene rocket engine. 7903 kN. Zenit stage 1. In production. Isp=337s. RD-171 used two-plane gimablling versus one-plane gimablling on RD-170 developed in parallel for Energia. First flight 1985.
Glushko Lox/Kerosene rocket engine. 8354 kN. Zenit-3 stage 1 (?). Developed -1994. Uprated version of RD-171. To have been qualified for flight 1994. Isp=337s.
Glushko Lox/Kerosene rocket engine. 8181 kN. Zenit-3 stage 1 (?). Design concept 1990's. Uprated version of RD-171 with 4 chambers, 1 turbo-pump and 2 gas generators. Intended for uprated Zenit named Zenit 3 Isp=337s.
Glushko Lox/Kerosene rocket engine. 7905 kN. Angara stage I. Developed 1995-.
Glushko Lox/Kerosene rocket engine. 4152 kN. Atlas III, Atlas V stage 1. In production. Isp=337s. First flight 2000. Two-thrust-chamber derivative of the four-chamber RD-170 used on Zenit.
Glushko Lox/LCH4 rocket engine family. Methane variant of RD-120K engine.
Glushko Lox/LCH4 rocket engine. 902 kN. Riksha (-1, -2) stage 1. Developed 1994-. Isp=353s. Methane variant of RD-120K engine. Thrust range and Isp range due to throat diameter and chamber pressure. Gimbaling +/- 6 degree in two planes.
Glushko Lox/LNG rocket engine. 882 kN. Vozdushnyy Start stage 1. Developed 1998-. Variant of RD-182 engine for liquid natural gas (mainly CH4). Proposed initial candidate for project Vozdushnyy Start of Kompomash.
Glushko Lox/LCH4 rocket engine. 9.8 kN. Developed 1996-. Isp=360s. Main engine for apogee stage of Riksha-1 launcher project. Gimbaling +/- 10 degree in two planes. Nozzle expansion ratio is 75/0.055=1364.
Glushko Lox/LCH4 rocket engine. Developed 1996-on. Isp=322s. Attitude correction engine for apogee stage of Riksha-1 launcher project (together with RD-183). Gimbaling +/- 20 degree in two planes.
Glushko Lox/LCH4 rocket engine. 179 kN. Riksha-0 stage 2. Developed 1996-. Isp=378s. Upper stage version of RD-169 with larger nozzle. Gimbaling +/- 4 degree in two planes.
Glushko Lox/LCH4 rocket engine. 1000 kN. Riksha-0 stage 1. Developed 1996-. The RD-190 consists of 6 RD-169 engines. Each chamber can be gimbaled individually in two planes by +/- 8 degree. Isp=351s.
Glushko Lox/Kerosene rocket engine family. Proposed for stage 1 of Angara. Single chamber from 4-chamber RD-170 would have been cheap and fast to develop. Only reached the draft project stage by 2003.
Glushko Lox/Kerosene rocket engine. 2079 kN. Isp=337s. Proposed for stage 1 of Angara. Single chamber from 4-chamber RD-170 would have been cheap and fast to develop. Only reached the draft project stage by 2003. Gimbaling +/- 8 degree in two planes.
Glushko Lox/Kerosene rocket engine. 1976 kN. Angara stage I. Developed 1996-. Single chamber version of the RD-170 / RD-171. Isp=337s.
Glushko Lox/LCH4 rocket engine family. Proposed methane-variant of RD-191.
Glushko Lox/LCH4 rocket engine. 2138 kN. Isp=356s. Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. Nozzle expansion ratio is 262/0.75=349.
Glushko Lox/LCH4 rocket engine. 1942 kN. Developed 1996-on. Isp=354s. Proposed variant of RD-192. Staged combustion cycle with fuel-rich gas generator. Gimbaling +/- 8 degree in two planes.
Glushko Lox/LCH4 rocket engine. 2089 kN. Developed 1996-on. Proposed variant of RD-192. Gas generator cycle. Gimbaling +/- 8 degree in two planes. Status 1998 was project based on RD-191 protoype, development estimated for four years. Isp=341s.
Glushko Lox/LCH4 rocket engine. 2128 kN. Developed 1996-on. Isp=371s. Proposed variant of RD-192. Staged combustion cycle with oxidizer-rich gas generator. Gimbaling +/- 8 degree in two planes.
Glushko Nitric acid/Kerosene rocket engine. 2.940 kN. take-off acelleration of Pe-2R, La-7R, Yak-3, Su-6, Su-7, La-120R airplanes. Developed 1941-46. The RD-1KhZ was a variant of the RD-1 engine with chemical ignition. Production 1944-45. Isp=200s.
RD-2.
Glushko Nitric acid/Kerosene rocket engine family. Developed 1945-47. The RD-2 was based on the RD-1 engine.
RD-2.
Glushko Nitric acid/Kerosene rocket engine. 6 kN. experimental. Developed 1945-47. The RD-2 was based on the RD-1 engine. Used chemical ignition. Isp=200s.
Glushko Nitric acid/Kerosene rocket engine. 98.508 kN. vertical sounding rocket. Developed -1951. Isp=234s.
Glushko Nitric acid/Kerosene rocket engine. 29.850 kN. vertical sounding rocket. Developed -1954. Isp=241s.
Glushko Nitric acid/Kerosene rocket engine. 642.3 kN. long-distance missile. Developed 1952-55. Original four-chamber engine design planned for use on the R-12 IRBM. Abandoned due to limited thrust and the RD-214 was developed in its place. Isp=261s.
Glushko Nitric acid/Kerosene rocket engine. 623 kN. Developed 1952-56. Isp=253s. Original four-chamber engine design planned for the booster stage of the Buran intercontinental ramjet missile. Abandoned due to limited thrust; RD-213 was developed instead.
Glushko Nitric acid/Kerosene rocket engine. 755 kN. Winged rocket M-40 (2). Development ended 1957. Two thrust levels. Ignition with propellant TG-02. Chamber pressure 233,8 / 46,6 bar. Specific impulse 223 / 231 sea level. Isp=254s.
Glushko Nitric acid/Kerosene rocket engine. 730 kN. R-12, Kosmos 11K63 stage 1. Isp=264s. Single turbopump driven by H2O2 gas generator feeding four fixed chambers. Ignition with propellant TG-02. First flight 1957.
Glushko Nitric acid/UDMH rocket engine. 864 kN. R-14, Kosmos 11K63 stage 1. Out of Production. Original intended use unknown. Two RD-215 clustered to make RD-216. Isp=291s. First flight 1966.
Glushko Nitric acid/UDMH rocket engine family. RD-216 was an assembly of 2 RD-215's with 2 combustion chambers and 2 turbines. Two sets of these were in turn used in the first stage of the R-14.
Glushko Nitric acid/UDMH rocket engine. 1728 kN. R-14, Kosmos 11K65 stage 1. Isp=291s. RD-216 was an assembly of 2 RD-215's with 2 combustion chambers and 2 turbines. Two sets of these were in turn used in the first stage of the R-14. First flight 1964.
Glushko Nitric acid/UDMH rocket engine. Kosmos-3M stage I. Out of Production.
Glushko Nitric acid/UDMH rocket engine. 865 kN. R-16 stage 1. Out of Production. Original intended use unknown. Three RD-217 clustered to make RD-218. Isp=289s. First flight 1961.
Glushko Nitric acid/UDMH rocket engine. 2592 kN. R-16 stage 1. Isp=289s. Consisted of three RD-217; had 6 combustion chambers and 3 turbines; powered the R-16 ICBM. First flight 1960.
Glushko Nitric acid/UDMH rocket engine. 883 kN. R-16 stage 2. Isp=293s. Derivative of RD-217 with a truss and piping changes. Despite higher expansion ratio, engine was shorter than first stage version, with relatively low performance. Flown 1960-1972.
Glushko Nitric acid/UDMH rocket engine. 1074 kN. missile stage 1 (stage 2 used RD-221). Developed 1960-. Isp=306s.
Glushko Nitric acid/UDMH rocket engine. 1118 kN. missile stage 2 (stage 1 used RD-220). Developed 1960-. Isp=318s.
Glushko Nitric acid/UDMH rocket engine. 1634 kN. missile stage 1 (stage 2 used RD-223). Developed 1960-61. Precursor to RD-253. Isp=302s.
Glushko Nitric acid/UDMH rocket engine. 1697 kN. missile stage 2 (stage 1 used RD-222). Developed 1960-61. Precursor to RD-253. Isp=314s.
Glushko Nitric acid/UDMH rocket engine. 1778 kN. R-26 stage 1. Out of production. RD-224 is a block of 2 RD-225s. An upper stage thrust chamber was developed under designation U102-000. Isp=294s. First flight 1961.
Glushko Nitric acid/UDMH rocket engine. 889 kN. R-26 stage 1. Out of Production. Two clustered together to make RD-224. Isp=294s. First flight 1961.
RD-226 ?.
Alternate designation for U102-000 Nitric acid-UDMH rocket engine.
Glushko N2O4/UDMH rocket engine. 881 kN. R-36-0 stage 1, Tsyklon 2 stage 1. Out of Production. Assembly of 3 RD-250 units make RD-251. Isp=301s.
Glushko N2O4/UDMH rocket engine. 2643 kN. R-36-0 stage 1, Tsyklon 2 stage 1. In production. Assembly of 3 RD-250-type units. Isp=301s. First flight 1965.
Glushko N2O4/UDMH rocket engine. 940.5 kN. R-36-0 stage 2; Tsyklon 2 stage 2. In production. Used modified chamber from RD-219, nozzle is conventional, so performance is higher. Isp=317s. First flight 1965.
Glushko N2O4/UDMH rocket engine family. Development went rather quickly but there were problems transitioning to production.
Glushko N2O4/UDMH rocket engine. 1745 kN. In Production. Version of RD-253 with thrust increased by 7%. Included an additional gas generator for tank pressurization. First flight 1986.
Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle. First flown in 1965.
Glushko N2O4/UDMH rocket engine. 1746 kN. Proton KM-1. In production. Developed in 1990s. Isp=317s. First flight 1999.
Glushko N2O4/UDMH rocket engine. 1745 kN. Designed 1964-1968. UR-700 Stage 3. Development of RD-253 with increased expansion ratio for upper stage use.
Glushko N2O4/UDMH rocket engine. 1716 kN. N-1 upper stage, UR-700 stage 3. Study 1961. Proposed for use in N-1. High altitude version of RD-253 for 2nd stages. First flight 1974.
Glushko N2O4/UDMH rocket engine. 3032 kN. Tsyklon 3 stage 1. In production. Based on RD-251 Isp=301s. First flight 1977.
Glushko N2O4/UDMH rocket engine. 941 kN. Tsyklon 3 stage 2. In production. Based on RD-252 Isp=317s. First flight 1977.
Glushko N2O4/UDMH rocket engine family. Four RD-263 engines combined into RD-264 system.
Glushko N2O4/UDMH rocket engine. 1155 kN. R-36M / RS-20A (SS-18 Mod 1) stage 1. Out of Production. Four RD-263 engines combined into RD-264 system. Isp=318s.
Glushko N2O4/UDMH rocket engine. Developed 1980. Project to upgrade RD-263. Upgrade was realized in RD-273 engine.
Glushko N2O4/UDMH rocket engine. 4521 kN. R-36M / RS-20A (SS-18 Mod 1) stage 1. Consists of four RD-263 engines. Isp=318s. Used on Dnepr launch vehicle. First flight 1986.
Glushko N2O4/UDMH rocket engine. 1236 kN. MR-UR-100 / RS-16 (SS-17) stage 1. Out of Production. First flight 1976. Modification of RD-263 engine. Isp=319s. First flight 1990.
Glushko N2O4/UDMH rocket engine family. Developed 1962-1971, largest rocket engine ever built in the Soviet Union, answer to F-1. Tested but cancelled before combustion instability problems solved.
Glushko N2O4/UDMH rocket engine. 6713 kN. UR-700, R-56 stage 1. Development ended 1968. Isp=322s. Developed 1962-1971, largest rocket engine ever built in the Soviet Union, answer to F-1. Tested but cancelled before combustion instability problems solved.
Glushko exotic N2O4/Pentaborane rocket engine. 7159 kN. Isp=365s. In 1962-1970 Glushko studied use of Pentaborane 'zip' propellants in his monster RD-270 engine. Created immense toxicity problems but increased specific impulse of the engine by 42 seconds.
Glushko N2O4/UDMH rocket engine. 1238 kN. Developed 1975-82. Upgrade of RD-263 in 1982 based on RD-263F project.
Glushko N2O4/UDMH rocket engine. 4952 kN. Developed 1975-85. Upgrade of RD-264 engine with increased chamber pressure and thrust. Development stopped due to problems with turbopump shaft balance.
RD-275.
Manufacturer's designation of RD-253 rocket engine.
Glushko N2O4/UDMH rocket engine. 1745 kN. Proton stage 1. In Production. Uprated version of RD-253, developed in the 1980's. Isp=317s. First flight 1986.
Glushko N2O4/Aerozine-50 rocket engine. 117.6 kN. Experimental engine. Study 1961. Experimental engine using Aerozine 50 (50% UDMH + 50% hydrazine) as fuel. Isp=350s.
Yuzhnoye rocket engine. Maneuvering vehicle axial maneuvering.
Dushkin Nitric acid/Kerosene rocket engine. 13.7 kN. I-270. Developed 1944-47. Thrust variable 0.1-0.3 tf / 0.35-1.4 tf.
Dushkin Nitric acid/Kerosene rocket engine. 19.6 kN. Samolet 5. Developed 1946.
RD-3.
Glushko Nitric acid/Kerosene rocket engine. 9 kN. experimental. Developed 1950's. The RD-3 was a cluster of three RD-1 engines with a new common turbopump. Ignition was by an ethane-air mixture. Isp=190s.
Russian space tug. Study 1975. Upper stage / space tug using high energy propellants. To have been launched by Proton; ground tested but never flown.
Glushko exotic LF2/Ammonia rocket engine. 96.670 kN. Proton K stage 4. Developed 1965-77. Developed by Glushko beginning in 1965. Planned for use in Proton K-4H high energy upper stage. Motor tested but never flown. Isp=400s. First flight 1977.
Glushko exotic LF2/Ammonia rocket engine. 98 kN. Developed 1960-69. Successor to RD-303 and predecessor to RD-301. Staged combustion cycle. Isp=405s.
Glushko exotic LF2/Ammonia rocket engine. Developed 1960-65. Predecessor to RD-302 and RD-301.
Glushko exotic LF2/LH2 rocket engine. 98 kN. Design concept 1963-. Studied by Glushko as engine concept with high-energy propellants. Isp=464s.
Lyulka turbojet engine. 158.4 kN. T-4. Out of Production. Used in Sukhoi March 3 aircraft. Thrust is maximum sea level thrust; specific impulse is sea level value at that thrust. Isp=1980s.
RD-3A.
Alternate designation for RD-102 Lox-Alcohol rocket engine.
Glushko Lox/Alcohol rocket engine. R-3A. Out of Production. Project for R-3A experimental missile. Stopped in favour of RD-103.
Glushko nuclear/lh2 rocket engine. 68 kN. UR-700M concept. Developed 1960s.
RD-448, RO-7.
Alternate designation for RD-0109 Lox-Kerosene rocket engine.
RD-461.
Alternate designation for RD-0110 Lox-Kerosene rocket engine.
RD-461, 11D55, 8D715K, RO-8.
Alternate designation for RD-0108 Lox-Kerosene rocket engine.
RD-461, RO-9.
Alternate designation for RD-0107 Lox-Kerosene rocket engine.
RD-465, 8D49.
Alternate designation for RD-0210 N2O4-UDMH rocket engine.
RD-468.
Alternate designation for RD-0211 N2O4-UDMH rocket engine.
RD-473.
Glushko H2O2/Pentaborane rocket engine. 98.1 kN. Experimental upper stage engine. Developed 1960-66. Isp=380s. Experimental upper stage engine. Program stopped due to toxicity of propellants. Intended for Proton upper stage. First flight 1966.
Glushko H2O2/CxHy rocket engine family. Developed 1965-75.
Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975.
Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975.
Glushko H2O2/CxHy rocket engine. Developed 1965-75. First flight 1975.
Lyulka lox/lh2 rocket engine. 392 kN. N1 concept stage III. Developed 1960-75. Isp=440s.
Glushko exotic rocket engine. 98.060 kN. Experimental upper stage engine. Developed 1963-70. Isp=400s. Propellants Lox/30% Beryllium+Pentaborane in 70% Hydrazine.
Isayev lox/lh2 rocket engine family. Original application N1 block R. Development ended 1971. Design sold to India in 1990's for GSLV.
Isayev lox/lh2 rocket engine. 69.6 kN. N1 block R. Development ended 1971. Oxygen-hydrogen engine for cryogenic upper stage. Developed but never flown. Design sold to India in 1990's for GSLV. Isp=462s.
Isayev lox/lh2 rocket engine. 73.580 kN. Proton and Angara upper stage KVRB, 12KRB upper stage for GSLV (India). In development. Isp=461s. First flight 2001.
Isayev Lox/LNG rocket engine. 73.5 kN. Vozdushnyy Start stage 2. Developed 1996-. Variant of RD-56M using liquid natural gas in place of hydrogen. First engine tests performed in 1998.
Lyulka lox/lh2 rocket engine family. One to have been used in N1 Block S in 1970's. Cancelled, sold to India in 1990's.
Lyulka lox/lh2 rocket engine. 392 kN. N1 Block S (N-1M). Study 1965. One to have been used in N1 Block S. In fixed chamber version, 3 to 6 to have been used in N1 Block V-III. Engine system includes roll control thruster with 1.29 kN thrust. Isp=456s.
Lyulka lox/lh2 rocket engine. 395 kN. Developed 1995-98. Isp=460s. New version of RD-57M for SSTO-demonstrator proposed by Aerojet. Optimized nozzle contour for performance increase, new chamber material for weight reduction.
Lyulka lox/lh2 rocket engine. 397 kN. Vulkan Blok V. Development ended 1976. Isp=461s. Version with extendible nozzle. Length 4.06 / 2.61 m. Specific impulse 461 / 448 sec. Area ratio 170 / 87.6.
Korolev Lox/Kerosene rocket engine family. High-performance upper-stage engine developed for N1 lunar crasher stage, but saw general use as restartable Block D upper stage of Proton launch vehicle. First flight 1967. Also proposed for N12RA, Proryv, LM, 315GK for Zenit, Angara, Energia-M.
Korolev Lox/Kerosene rocket engine. 83.4 kN. Isp=349s. High-performance upper-stage engine developed for N1 lunar crasher stage, but saw general use as restartable Block D upper stage of Proton launch vehicle. First flight 1967.
Korolev Lox/Kerosene rocket engine. 83.4 kN. Proton 8K824K / 11S824M; 11S824F; 11S86; 11S861; 17S40 stage 4 (block DM). In production. Isp=353s. First flight 1974.
Korolev Lox/Kerosene rocket engine. 83.4 kN. In Production. Isp=353s. Multi-function variant of RD-58 for uprated upper stages applications (Zenit stage 3, Angara). Block-DM-SL for Sea-Launch may have used RD-58M.
Korolev Lox/Kerosene rocket engine. 86.3 kN. Proton 8K82K / 11S861-01 stage 4 (block DM). Version 17D12 for Buran OMS. Version uses synthetic kerosene ('Sintin') for higher specific impulse. Isp=361s. First flight 1994.
Korolev Lox/Kerosene rocket engine. 71 kN. Zenit stage 3. Developed 1981-1990. Isp=361s.
Glushko nuclear/lh2 rocket engine. 1960 kN. Isp=2000s. Gas core nuclear engine worked developed 1962-1970 for use in second stage of two-stage interplanetary rockets.
Yuzhnoye Nitric acid/UDMH rocket engine family. R-16 stage 1 attitude control engine.
Yuzhnoye Nitric acid/UDMH rocket engine. 380 kN. R-16 stage 1 attitude control engine. Out of Production.
Yuzhnoye N2O4/UDMH rocket engine. 285 kN. R-36 stage 1 attitude control engine. Out of Production. 4 nozzles, maximum 42 degree gimbal angle.
Yuzhnoye Nitric acid/UDMH rocket engine family. R-16 stage 2 attitude control engine.
Yuzhnoye Nitric acid/UDMH rocket engine. 49.2 kN. R-16 stage 2 attitude control engine. Out of Production.
Yuzhnoye N2O4/UDMH rocket engine. 54.3 kN. R-36 stage 2 attitude control engine. Out of Production. 4 nozzles, maximum 50 degree gimbal angle.
Glushko lox/lh2/kerosene tripropellant rocket engine for air-launched MAKS spaceplane. 4003 kN. Development ended 1988. Isp=415 / 460s. First flight 2001.
Glushko Lox/Kerosene/LH2 tripropellant engine. 1966 kN. Developed 1990's. Isp=407 / 452 s. Tripropellant engine, single chamber, derived from RD-701 project. Chamber pressure 294 / 124 bar. First flight 1999.
RD-8.
Yuzhnoye Lox/Kerosene rocket engine. 78.4 kN. Zenit stage 2 attitude control engine. In Production. Isp=342s. Four-chamber pump-fed single-run engine operated in a staged combustion scheme with afterburning of the generator gas. Development began in 1976.
Yuzhnoye Lox/Kerosene rocket engine. 19.6 kN. Upper stages. Design concept 2007. Isp=344s. Derivative of the RD-8 Zenit-2 second stage vernier thrust engine combustion chamber for use in launch vehicle upper stages.
Yuzhnoye Lox/Kerosene rocket engine. 88 kN. Upper stages. Isp=345s. 2007 design concept for a four-chamber restartable main engine for launch vehicle upper stages.
Yuzhnoye Nitric acid/UDMH rocket engine. 32.480 kN. R-16 (SS-7) stage 1 attitude control engine . Out of Production. Four thrusters are each gimbaled in one single axis. Isp=279s.
Yuzhnoye Nitric acid/UDMH rocket engine. 48.250 kN. R-16 (SS-7) stage 2 attitude control engine. Out of Production. Four thrusters are each gimbaled in one single axis. Isp=255s.
Yuzhnoye Nitric acid/UDMH rocket engine. 467.6 kN. Stage 2, no application. Developed 1960-63. Designed for second stage, no application. Two thrust levels. Thrust 467.6 kN + 11.8 kN / 7.65 kN. Isp=300s.
Yuzhnoye N2O4/UDMH rocket engine. 75.5 kN. R-36orb (SS-X-10) orbital stage. Out of Production. Thrust vector control by 4 nozzles fed from gas generator. Isp=312s.
Yuzhnoye N2O4/UDMH rocket engine. 328 kN. Tsyklon stage 1 attitude control engine. Out of Production. Isp=292s. Four-chamber pump-fed single-run engine burned hypergolic propellants in a gas generator scheme.
Yuzhnoye N2O4/UDMH rocket engine. 54.230 kN. Tsyklon stage 2 attitude control engine. Out of Production. Isp=280s. Autonomous four-chamber pump-fed single-run engine burned hypergolic propellants in a gas generator scheme.
Yuzhnoye N2O4/UDMH rocket engine. 137.3 kN. RT-20P missile stage 2. Out of production. Isp=329s. Designed for second stage of mixed propulsion missile, only flight tests. Thrust vector control by secondary gas injection into nozzle. First flight 1967.
Yuzhnoye N2O4/UDMH rocket engine. 20.1 kN. Isp=315s. Primary engine for LK manned lunar lander. Propulsion cluster provided the variable thrust needed for a soft landing onto the lunar surface, then restarted for injection into lunar orbit. Flown 1970.
Yuzhnoye N2O4/UDMH rocket engine. 20.050 kN. LK lunar lander reserve engine. Hardware. Isp=312s. Backup engine for the LK manned lunar lander in the event the primary RD-858 engine failed. Restart within three seconds after shut down. Flight tests 1970.
Yuzhnoye N2O4/UDMH rocket engine. 5.9 kN. Upper stages. Developed 1972. Isp=320s. Engine used a novel scheme combining an existing proven combustion chamber but using a pneumatic pump for propellant supply.
Yuzhnoye N2O4/UDMH rocket engine family. Tsiklon 2 and 3 stage 3; Ikar. Based on RD-854.
Yuzhnoye N2O4/UDMH rocket engine. 78.710 kN. Tsyklon 2 and 3 stage 3; Ikar. In production. Isp=317s. Based on RD-854. Thrust vector control by 4 nozzles (thrust 98 N each) fed from a gas generator. First flight 1965.
Yuzhnoye, Fiat Avio N2O4/UDMH rocket engine. 76.453 kN. Vega upper stage. Developed 1996-. Isp=325s. Proposed uprate of RD-861 engine. Thrust vector control by gimbal, roll control by 4 nozzles (thrust 29 N each).
Yuzhnoye N2O4/UDMH rocket engine. 77.630 kN. Tsyklon 2 and 3 stage 3; Ikar. Developed 2005. Isp=330s. High pressure fuel was used to gimbal the engine in two planes, replacing four thrust vector engines on the basic RD-861.
Yuzhnoye N2O4/UDMH rocket engine. 142.630 kN. MR-UR-100 / RS-16 (SS-17) stage 2. Out of Production. Based on RD-857. Thrust vector control by secondary gas injection into nozzle. Roll control via special small jet nozzles. Isp=331s.
Yuzhnoye N2O4/UDMH rocket engine. 276.840 kN. MR-UR-100 / RS-16 (SS-17) stage 1 attitude control engine. Out of Production. Isp=301s.
Yuzhnoye N2O4/UDMH rocket engine. 20.2 kN. R-36M vehicle bus. Out of Production. Isp=309s. Two thrust levels. The four thruster swing out of the stage housing before use. Chamber pressure 41 / 17 bar. Specific impulse 309 / 298 sec.
Yuzhnoye N2O4/UDMH rocket engine. 5.2 kN. RT-23 MIRV-bus. Out of Production. Isp=305s. Engine consisted of two turbopumps with gas generators and two feeders; a single chamber main engine; and 16 liquid thrusters for attitude control and translation.
Yuzhnoye N2O4/UDMH rocket engine. 23.250 kN. Apogee stage. Developed 1983-. Isp=325s. In development in 1996. One main and an unknown number of control thrusters. 23.25 + 0.03 kN. Chamber pressure 91.5 / 6.9 bar. Specific impulse 325 / 230 sec.
Yuzhnoye N2O4/UDMH rocket engine. 8.580 kN. R-36M2 vehicle bus. Based on RD-864. Two thrust levels. The four thrusters swing out of the stage housing before use. Chamber pressure 41 / 17 bar. Diameter 3,0 / 4,02 m. Isp=313s. First flight 1986.
RDD.
Russian tactical ballistic missile. The RDD - Long range rocket - was assigned to Korolev in November 1944 in response to the German V-2. Korolev was given charge of a team of 60 engineers and required to provide a draft project in three days. The resulting two-stage design used Lox/Alcohol propellants and an autopilot for guidance. It was proposed that a 5 tonne thrust rocket, 110 mm in diameter, would be available by 1945. A 250 tonne thrust, solid fuelled, 280 mm diameter, 4 m long rocket would be ready by 1949. These designs evolved into the more refined D-1 and D-2 before being overtaken by the post-war availability of V-2 technology.
Russian rocket engine. Developed End 40's. Single chamber with turbopump propellant feed.
Dushkin Lox/Kerosene rocket engine. 980 kN. Sanger. Developed 1946-51. Isp=285s.
NII Mash N2O4/UDMH rocket engine. 400 mN. In Production. Experimental low-thrust thruster. Chamber from niobium alloy. Chamber pressure 41 / 17 bar. Specific impulse 313 / 302,3 sec. Isp=290s.
NII Mash nitrogen+helium cold gas thruster. 800 mN. Kosmos satellites. In Production. Low-thrust cold-gas thruster. Specific impulse 70 / 160 sec. Isp=70s.
NII Mash N2O4/UDMH rocket engine. 0.100 kN. Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites. In Production. Low-thrust attitude control thruster. Isp=260s.
NII Mash N2O4/UDMH rocket engine. 12 N. Almaz, Kvant, Kristall, Spektr, Priroda. In Production. Low-thrust attitude control thruster. Predecessor was RDMT-400. Used in Isayev 17D58E engine. Isp=279s.
NII Mash N2O4/UDMH rocket engine. 0.135 kN. Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites. In Production. Low-thrust attitude control thruster. Isp=260s.
NII Mash N2O4/UDMH rocket engine family. Low-thrust attitude control thruster.
NII Mash N2O4/UDMH rocket engine. 0.200 kN. Almaz. In Production. Low-thrust attitude control thruster. Isp=255s.
NII Mash GOX/Kerosene rocket engine. 0.200 kN. Buran. Out of Production. Low-thrust attitude control thruster. Mass in ref. NIIMash 95 given as only 2.5 kg. Isp=265s.
NII Mash GOX/Alcohol rocket engine. 2.6 kN. Developed 1980's. Experimental low-thrust thruster. Isp=270s.
NII Mash N2O4/UDMH rocket engine family. Low-thrust attitude control thruster. Used in Isayev 11D458 engine.
NII Mash N2O4/UDMH rocket engine. 0.400 kN. Almaz, Kvant, Kristall, Spektr, Priroda. In Production. Low-thrust attitude control thruster. Used in Isayev 11D458 engine. Isp=255s.
NII Mash N2O4/UDMH rocket engine. 0.400 kN. Developed 1980's. Experimental low-thrust thruster. Carbon combustion chamber. Mass may be chamber only. Isp=296s.
NII Mash N2O4/UDMH rocket engine. 0.400 kN. Developed 1980's. Experimental low-thrust thruster. Niobium combustion chamber with coating. Isp=290s.
NII Mash air cold gas thruster. 5 N. MMK. In Production. Low-thrust cold-gas thruster. Isp=70s.
NII Mash N2O4/UDMH rocket engine. 0.050 kN. Kosmos satellites. In Production. Low-thrust attitude control thruster. Isp=255s.
NII Mash N2O4/UDMH rocket engine. 8 N. Developed 1980's. Experimental low-thrust thruster. Isp=296s.
RDMT-XX.
Alternate designation for NII 612 kgf N2O4-UDMH rocket engine.
RDS-37.
Standard RV of R-7A missile.
RDX.
Nitramine
Marquardt hydrazine monopropellant rocket engine. 890 mN. In Production.
Marquardt hydrazine monopropellant rocket engine. 0.020 kN. In Production.
Marquardt hydrazine monopropellant rocket engine family.
Marquardt hydrazine monopropellant rocket engine. 4.45 N. In Production.
Marquardt hydrazine monopropellant rocket engine. 2.22 N. In Production.
Marquardt hydrazine monopropellant rocket engine. 0.556 kN. In Production.
Marquardt hydrazine monopropellant rocket engine family.
Marquardt hydrazine monopropellant rocket engine. 0.130 kN. In Production.
Marquardt hydrazine monopropellant rocket engine. 0.178 kN. In Production.
Marquardt hydrazine monopropellant rocket engine. 0.090 kN. In Production.
Marquardt hydrazine monopropellant rocket engine. 0.050 kN. In Production.
Marquardt hydrazine monopropellant rocket engine. 2.22 N. In Production.
American manufacturer of rocket engines. Reaction Motors Incorporated, USA.
Readdy, William Francis 'Bill' (1952-) American test pilot astronaut. Flew on STS-42, STS-51, STS-79.
Reagan, Ronald (1911-2004) American politician, president of the USA 1981-1989. Initiated 'Star Wars' strategic defences and Space Station Freedomt. Confronted the Soviet Union with a heavy aerospace buildup which they could not match, contributing to their collapse.
Rebrov, Mikhail Fedorovich (1931-1998) Russian journalist cosmonaut, 1965-1974.
Base for units deployed with six Pioner missile launchers.
Recknagel, Otto German expert in guided missiles during World War II. As of January 1947, last known to be working at Englesby.
Books that should be on your bookshelf...
Recoverable Booster Space System.
Alternate designation for RBSS winged orbital launch vehicle.
Recoverable Booster Systems for Orbital Logistics.
American winged orbital launch vehicle. Lockheed investigated the economics of reusable launch vehicles for crews and light space station cargo during the early 1960s. Anticipated manned space activities in the 1970s included a two-phase Earth-orbital space station program, a lunar base, an early Mars mission, plus later Mars/Venus missions. Lockheed proposed four possible launch systems to support the scenario, ranging from System I, a 6-man Apollo CSM/Saturn-IB vehicle, to a fully reusable System IV with a ramjet-rocket booster.
Recoverable Test Satellite.
Alternate designation for FSW military surveillance satellite.
The Recruit motor was usually used as an upper stage, but in this air-launched vehicle was used for re-entry vehicle heat transfer and aerodynamic stability tests.
American sounding rocket. The Recruit motor was usually used as an upper stage, but in this air-launched vehicle was used for re-entry vehicle heat transfer and aerodynamic stability tests.
American sounding rocket. The Recruit motor was the first stage of this larger booster, dropped from a B-57 for re-entry vehicle heat transfer tests.
Red Army.
Red Duster.
Popular Name of Bloodhound Mk. 1 surface-to-air missile.
Sounding rocket range, known to have been used for 23 launches in 1979, reaching up to 215 kilometers altitude.
Tomahawk Sandia, Nike, Loki, Honest John, Hawk, Black Brant, Arcas launch complex. Chukuni Range
Astrobee launch complex. McMarmac Site
Redesigned Solid Rocket Motor.
Alternate designation for Shuttle RSRM rocket stage.
Thiokol solid rocket engine. 11,520 kN. In Production. Isp=268s. Replacement shuttle solid rocket booster with redesigned field joints to prevent failure that caused the Challenger disaster.
American manufacturer of rocket engines. Redmond, USA.
American manufacturer. Redondo Beach, USA.
Redstone was the first large liquid rocket developed in the US using German V-2 technology. Originally designated Hermes C. Redstones later launched the first US satellite and the first American astronaut into space.
Redstone was the first large liquid rocket developed in the US using German V-2 technology. Originally designated Hermes C. Redstones later launched the first US satellite and the first American astronaut into space.
Lox/Alcohol propellant rocket stage. Loaded/empty mass 28,440/3,125 kg. Thrust 414.34 kN. Vacuum specific impulse 265 seconds.
Lox/Alcohol propellant rocket stage. Loaded/empty mass 28,440/3,125 kg. Thrust 414.34 kN. Vacuum specific impulse 265 seconds. Used for Jupiter-C satellite missions, and greatly modified, for Mercury manned positions. For Jupiter-C missions, used Hydyne fuel, which was toxic but increased specific impulse.
American suborbital launch vehicle. Greatly modified Redstone rocket used to launch the Mercury manned spacecraft on a suborbital trajectory, typically 380 km downrange, 220 km altitude, and a speed of 6800 kph.
Originally "exceeding what is necessary or normal"; technically a back-up system which takes over when the prime system fails.
Reeder, J American test pilot. Flew the X-5 # 1.
American manned rescue spacecraft. Study 1963. One crew lifting re-entry capsule. No abort capability. Mass per crew 1171 kg.
American manned rescue spacecraft. Study 1963. A six-man parasail escape system was studied as an elaboration of the single-crew system. It was to provide rescue from manned spacecraft as well as stations.
Reentry Vehicle.
Alternate designation for Big Gemini RV manned spacecraft module.
Re-entry vehicle technology satellite.
Category of spacecraft.
Rees.
Rees, Eberhard Friedrich Michael (1908-1998) German-American engineer, von Braun's right hand man, in charge of manufacturing 1940-1969 for V-2, Redstone, Jupiter, and rockets stages for Saturn LVs that took America to the moon. Succeeded von Braun as Director at Huntsville 1970-1973.
Russian technology satellite. One launch, 2001.12.10. The 8 kg Reflektor was built by NII KP in Russia for space debris studies in a joint experiment with the Air Force Research Lab.
Regener, Erich (1881-1955) German physical chemist during World War II. As of January 1947, living at Stuttgart Physikal Inst. d. T.H.S..
Sounding rocket launch location known to have been used for 12 launches from 1961 to 1965, reaching up to 150 kilometers altitude.
American intermediate range subsonic cruise missile. The Regulus was the first strategic long-range nuclear-armed guided missile deployed by the US Navy.
American intermediate range cruise missile family. The first strategic long-range nuclear-armed guided missile deployed by the US Navy.
American supersonic sub-to-surface intermediate-range cruise missile, development started in 1953. Program cancelled in 1958 in deference to Polaris project.
Regulus I.
Reichelderfer, Francis W (1895-1983) American meteorologist. Head of US Weather Bureau, 1938-1963. At the end of his tenure the first weather satellite was designed and orbited.
Reid.
Reid, Henry J E (1895-1968) American engineer, at NASA 1921-1961, designed basic instruments for flight research.
Reiff, Rolf German expert in the V-2 missile during World War II. As of January 1947, held at Camp Woilburg.
Reightler, Kenneth Stanley Jr 'Ken' (1951-) American test pilot astronaut. Flew on STS-48, STS-60.
Reilly, Dr James Francis II 'JR' (1954-) American geologist mission specialist astronaut. Flew on STS-89, STS-104, STS-117.
Japanese technology satellite. One launch, 2005.08.23. Plasma Science Technology. INDEX, renamed Reimei ("Dawn") after launch, was a test satellite with new lightweight satellite components, and a demonstration auroral imager payload.
Reinhard, Siegfried (1919-) German designer in WW2, member of the Rocket Team in the Soviet Union, worked on rocket engine development in Glushko's design bureau from 1947 to 1952. Worked in Engineering and Design; Dept. 61.
Reisig, Gerhard Herbert Richard (1910-2005) German engineer. Expert in guided missile guidance, telemetry, and control, working for von Braun from 1937. Worked for Dornberger on Wasserfall SAM from 1943. Member of von Braun's Rocket Team in the US from 1947.
Reisman, Garrett Erin (1968-) Jewish-American engineer mission specialist astronaut. Flew on ISS EO-16-3, STS-123, STS-132.
Reiter, Thomas Arthur (1958-) German test pilot cosmonaut. Flew on Mir EO-20, ISS Astrolab.
Reitsch, Hanna (1912-1979) German test pilot. Famed German aviatrix, glider and test pilot during WW2. She flew the womanned version of the V-1 cruise missile
American communications technology satellite. 2 launches, 1962.12.13 (Relay 1) and 1964.01.21 (Relay 2).
Relay Mirror Experiment.
Alternate designation for RME military strategic defense satellite.
REM.
Rat Enclosure Module (for SLS mission)
Remek, Vladimir 'Volodya' (1948-) Czech pilot cosmonaut. Flew on Salyut 6 EP-2. First Czech astronaut.
Russian logistics spacecraft. Study 1962. Remova was a Soviet Manned Maneuvering Unit design that first appeared in a German book in 1967. It was said that the study was made at the beginning of the 1960's.
Ren Xinmin Chinese Engineer. Chief Designer of Chinese storable propellant rocket engines. Replaced Wu Xiji in developing CZ-1 launch vehicle. Chief Designer for CZ-3 launch vehicle, DFH, Fengyun, and SJ series satellites.
Rendezvous technology satellite.
Category of spacecraft.
Renova.
Alternate designation for Nova MM R10R-2 heavy-lift orbital launch vehicle.
REP.
Rendezvous evaluation pod
American manufacturer of rockets and spacecraft. Republic, USA.
American pressure suit, tested 1966. This was a Republic Aviation design for a hard space suit for extended operations on the lunar surface.
American manned spacecraft. Study 1958. Republic's studies for the Air Force or NACA initial manned space project started at the beginning of 1958. Their unique concept was a lifting re-entry vehicle, termed the Ferri sled.
Res.
Res, Eberhard Fritz Michael German engineer in WW2, member of the Rocket Team in the United States thereafter. German expert in guided missiles during WW2. As of January 1947, working at Fort Bliss, Texas.
Rocketdyne N2O4/MMH rocket engine. 0.215 kN. Pitch Control Propulsion Module. Pressure-fed.
Rocketdyne N2O4/MMH rocket engine. 7.109 kN. Spacecraft. Pressure-fed. Isp=280s.
In the early 1960's, in the hey-day of the X-20 Dynasoar, it seemed that the US military would naturally keep building military aerospacecraft that would just keep going higher and faster. It was also supposed that the pilot would have to be given the equivalent of an ejection seat - some means of bailing out of the spacecraft in case of catastrophic failure or enemy attack.
American manned rescue spacecraft. Study 1984. The Personal Rescue Enclosure (PRE) Rescue Ball was an 86 cm diameter high-tech beach ball for transport of astronauts from a spacecraft in distress to the space shuttle.
American manned rescue spacecraft. Study 1966. A version of Gemini was proposed for rescue of crews stranded in Earth orbit. This version, launched by a Titan 3C, used a transtage for maneuvering.
Russian manufacturer of rockets and spacecraft. Reshetnev Design Bureau, Krasnoyarsk-26/Zhelenogorsk, Russia.
Reshetnev, Mikhail Fedorovich (1924-1996) Russian engineer. Chief Designer and General Designer 1961-1996 of OKB-10, primary Soviet designer of communications and navigation satellites.
Resnik, Dr Judith Arlene 'JR' (1949-1986) Jewish-American engineer mission specialist astronaut. Flew on STS-41-D, STS-51-L. Engineer. Died in Challenger accident.
Sounding rocket launch location known to have been used for 17 launches from 1966 to 1971, reaching up to 200 kilometers altitude.
The ability of an optical system to separate adjacent points and lines in the image and to show fine detail of the target.
Category of spacecraft.
Resupply Module.
Alternate designation for Apollo RM logistics spacecraft.
Zenit-derived satellites used for earth resources studies as part of the 'Resurs' and 'Gektor-Priroda' project. Investigation of the natural resources of the earth in the interests of various branches of the national economy of the USSR and international cooperation.
Russian earth land resources satellite. 7 launches, 1986.07.16 (Cosmos 1762) to 1988.02.18 (Cosmos 1920). The Resurs-F earth resource satellite was based on the recoverable Zenit-4 spy satellite.
Russian earth land resources satellite. 18 launches, 1988.05.31 (Cosmos 1951) to 1993.08.24 (Resurs F-19). A decree of 5 May 1977 authorized development of three earth resource satellites.
Russian earth land resources satellite. 29 launches, 1979.09.05 (Cosmos 1127) to 1986.05.28 (Cosmos 1746). The 17F41 was the first of 4 models of the Resurs-F to fly.
Russian earth land resources satellite. 2 launches, 1997.11.17 (Resurs F-1M) to 1999.09.28 (Resurs F-1M). Variant of the Resurs-F recoverable earth resources satellite. See Resurs F1-17F40 for a full technical description.
Russian earth land resources satellite. 11 launches, 1987.12.26 (Cosmos 1906) to 1995.09.26 (Resurs F2 N.10). Adaptation of recoverable Vostok spacecraft for remote sensing.
Russian earth land resources satellite. 4 launches, 1985.10.03 (Cosmos 1689) to 1998.07.10 (Resurs-O1 No. 4). A decree of 5 May 1977 authorized development of three earth resource satellites.
Ukrainian earth land resources satellite. Study 1980.
Russian earth land resources satellite. 2 launches, 1980.06.18 (Meteor 1-30) to 1983.07.24 (Cosmos 1484). Modified Meteor; prototype for Resurs-O1.
Russian civilian surveillance satellite. Study 1994.
Resurs-T.
Category of launch vehicles.
Retro and Correction Stage.
Alternate designation for Energia RCS rocket stage.
Retropack.
Alternate designation for Mercury Retropack manned spacecraft module.
Reusable One stage Orbital Space Truck.
American manned spaceplane. Study 1964. The Reusable Orbital Carrier (ROC) was a 1964 Lockheed study of a sled-launched HTHL TSTO. The second stage orbiter rocketplane would use Lox/LH2 propulsion to orbit and make an unpowered glide return and landing.
American sled-launched winged orbital launch vehicle. The Reusable Orbital Carrier (ROC) was a 1964 Lockheed study of a sled-launched HTHL TSTO. The booster's rocket engines would burn liquid oxygen and jet fuel while small turbojets would be used for landing approach. The 2nd stage orbiter rocketplane would make an unpowered glide return and landing. LOX, LH2 rocket propulsion would be used on the second stage. The gross liftoff weight would be about 453t and the vehicle could deliver ten passengers+3000kg to a space station. Alternatively, an unmanned 11,340kg payload could be carried.
Reusable Orbital Module-Booster & Utility Shuttle.
Alternate designation for Rombus ssto vtovl orbital launch vehicle.
Reusable Transport Spacecraft - Vertical Landing.
Alternate designation for MTKVA manned spaceplane.
American manufacturer. Revere, USA.
Revin, Sergey Nikolayevich (1966-) Russian engineer cosmonaut, 1996-on.
Iranian agency. Revolutionary Guards, Iran.
REX.
American earth ionosphere satellite. 2 launches, 1991.06.29 (REX) and 1996.03.09 (REX-II). The REX satellites were designed to study scintillation effects of the Earth's atmosphere on RF transmissions.
RF.
Russian Federation (Russian abbreviation); or Radio Frequency
RFI.
Radio Frequency Interference
RFNA.
Red Fuming Nitric Acid
RFP.
Request for proposal
RGM-15.
Department of Defence Designation of Regulus 2 intermediate range cruise missile.
RGM-165.
Department of Defence Designation of LASM short range ballistic missile.
RGM-59.
Department of Defence Designation of Taurus RGM-59 tactical ballistic missile.
RGM-6.
Department of Defence Designation of Regulus 1 intermediate range cruise missile.
American intermediate range cruise missile.
American intermediate range cruise missile.
American tactical cruise missile.
American tactical cruise missile.
RH.
Indian solid propellant sounding rocket family using indigenous rocket motors derived from French Belier / Jericho rocket engine technology.
RH.
Indian solid propellant sounding rocket family using indigenous rocket motors derived from French Belier / Jericho rocket engine technology.
ISRO VSSC solid rocket engine family.
Indian sounding rocket. Single stage vehicle
ISRO VSSC solid rocket engine. 8.4 kN.
ISRO VSSC solid rocket engine. 1.3 kN.
Indian sounding rocket. Two stage vehicle consisting of 1 x RH-200 + 1 x RH-125
ISRO solid rocket engine. 16.9 kN.
Solid propellant rocket stage. Loaded mass 100 kg. Thrust 16.90 kN.
Solid rocket stage. 8.40 kN (1,888 lbf) thrust. Mass 20 kg (44 lb).
Indian sounding rocket.
ISRO solid rocket engine family.
Indian sounding rocket. Sounding rocket derived from French Belier rocket engine technology.
ISRO solid rocket engine. 33.3 kN.
Indian single stage sounding rocket.
Solid propellant rocket stage. Loaded mass 500 kg. Thrust 39.10 kN.
Indian sounding rocket. Three stage vehicle consisting of 1 x RH-300 + 1 x RH-200 + 1 x RH-200
Solid rocket stage. 33.30 kN (7,486 lbf) thrust. Mass 300 kg (661 lb).
ISRO solid rocket engine. 39.1 kN.
Indian sounding rocket. 2 stage vehicle derived from French Stromboli engine technology.
ISRO/Antrix solid rocket engine. 76 kN.
Indian two-stage sounding rocket derived from French Stromboli engine technology.
Solid rocket stage. 76.00 kN (17,085 lbf) thrust. Mass 900 kg (1,984 lb).
Indian sounding rocket. Single stage vehicle
ISRO solid rocket engine.
Solid propellant rocket stage. Loaded mass 10 kg.
German surface-to-surface missile. Director Klein and Doctor Vuellers at Rheinmetall in Leba had developed this unguided bombardment weapon. It was a four-stage powder rocket of minimum weight but a range of 120 km.
German manufacturer of rockets. Rheinmetall, Germany.
German surface-to-air missile, tested during World War II, but never completed development. The name translates as 'Rhine Maiden'.
Rhode, Richard V (1904-1994) American engineer, at NASA 1925-1967, involved with air and launch vehicle research and advanced design criteria.
American military naval signals reconnaisance satellite. 4 launches, 1970.06.19 (Rhyolite 1) to 1978.04.07 (Rhyolite 4).
Research Institute for Advanced Computer Science
Rib Stiffened Expandable Escape System.
American manned rescue spacecraft. Study 1968. This Rockwell concept was stowed in a canister. In an emergency, the articulated rib-truss structure would be deployed into a mechanically rigid aeroshell shape.
Rice.
American manufacturer of spacecraft. Rice, USA.
Richards, Richard Noel 'Dick' (1946-) American test pilot astronaut. Flew on STS-28, STS-41, STS-50, STS-64.
Richards, Paul William (1964-) American engineer mission specialist astronaut. Flew on STS-102.
Rickhey, Georg German Engineer. Engineer and general manager of Mittelwerk during World War II. As of January 1947, working at Wright Field, Ohio.
Ride.
Ride, Dr Sally Kristen (1951-) American physicist mission specialist astronaut. Flew on STS-7, STS-41-G. Physicist, first American woman in space. Was married to astronaut Steven Alan Hawley.
American manned Mars expedition. Study 1987. Former astronaut Sally Ride was asked to head a task force to formulate a new NASA strategic plan in August 1986.
Ridenour, Louis Nicot (1911-1959) American physicist, served in leading academic, industry, and government positions, notably as chief scientist with the US Air Force in the early 1950s.
Ridley, Jack (1915-1957) American test pilot. Technical lead for pioneering rocketplanes at Edwards AFB 1946-1956. Killed in transport aircraft crash, 1957.
Riedel, Klaus Erhardt (1907-1944) Talented German engineer, instrumental in developing the first liquid propellant rocket engines in Germany at VfR and in design and debugging of the V-2's engine. Unrelated to contemporary rocket engineers Walter Riedel and Walther Riedel. Killed in an automobile crash near Karlshagen, Germany.
Riedel, Walter J H 'Papa' (1902-1968) German rocket engineer; worked for Heylandt, then von Braun; involved in development of V-2 engine. Disliked von Braun; left rocketry in 1946. Not to be confused with Walther Riedel or Klaus Riedl, two other contemporary rocket engineers.
Riedel, Walther Johannes (1903-1974) German manager and engineer who managed development of V-2 rocket engine after the death of Thiel. In the US he transferred this technology to Rocketdyne, which led to the engines for the Redstone, Thor, Jupiter, Atlas, and Saturn I rockets.
Rif.
Launch System of S-300F surface-to-air missile.
Rif.
Russian orbital launch vehicle. R-39 SLBM adapted for use as suborbital test vehicle or orbital launch vehicle.
N2O4/UDMH propellant rocket stage. Loaded mass 10,000 kg.
Rif-M.
Launch System of S-300FM surface-to-air missile.
Rif-Ma.
Russian orbital launch vehicle. Orbital launch vehicle derived from R-39 SLBM. Air-launched from An-124. Ignition mass 79 tonnes.
Argentinan sounding rocket. Two stage vehicle.
American Navy pioneering cruise missile project. Development started in 1943. Program cancelled in 1953.
American military target satellite. One launch, 1971.08.07. Space craft engaged in investigation of spaceflight techniques and technology.
Rij.
Rij, Jerry Jerome (1950-) American engineer military spaceflight engineer astronaut, 1979-1985. Served at Onizuka AFB, California. Retired from the Air Force in 1995. Thereafter worked in private industry in Virginia.
Russian orbital launch vehicle. New design launch vehicle based on SLBM technology.
RIM-156.
Department of Defence Designation of Standard SM-2ER Block IV surface-to-air missile.
RIM-161A.
Department of Defence Designation of Standard SM-3 anti-ballistic missile.
RIM-2.
Department of Defence Designation of Terrier surface-to-air missile.
American surface-to-air missile.
American surface-to-air missile.
American surface-to-air missile.
American surface-to-air missile. Nuclear warhead.
American surface-to-air missile.
RIM-67.
Department of Defence designation of Standard-ER missile.
American surface-to-air missile.
American surface-to-air missile.
American surface-to-air missile. Standard SM-2 ER
American surface-to-air missile. Command/inertial, semi-active RF terminal guided. 2 stage vehicle.
RIM-8.
Department of Defence designation of Talos missile.
American surface-to-air missile.
American surface-to-air missile.
American surface-to-air missile.
American surface-to-air missile.
American surface-to-air missile.
American surface-to-air missile.
American surface-to-air missile.
Rimsat Corp, USA
RISP.
American lunar flyby probe. Study 1959. The Recoverable Interplanetary Space Probe was a 1957 proposal of the MIT Instrumentation Laboratory.
Rita 2.
Alternate designation for MSBS M2-2 rocket stage.
American nuclear-powered orbital launch vehicle. Nuclear single-stage-to-orbit booster.
Nuclear/LH2 propellant rocket stage. Loaded/empty mass 4,399,000/880,000 kg. Thrust 96,507.00 kN. Vacuum specific impulse 810 seconds. Same engine chamber used to burn liquid oxygen and hydrogen for boost phase, switching to pure nuclear thermal engine for high-performance final acceleration.
Sud/SEP solid rocket engine. 320 kN.
RJ47.
Wright ramjet engine. 44.6 kN. Development ended 1958. Used on Navaho G-38 launch vehicle.
RJ47.
Wright ramjet engine. 44.6 kN. Development ended 1958. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point. Isp=1200s. Used on Navaho G-38 launch vehicle.
RK-.
Cruise missile (designation numbering series) (Russian abbreviation)
RKA.
Russian Space Agency
RKA.
Rossiskoye Kosmicheskoye Agentsvo (Russian Space Agency), Moskva, Russia
Glushko Lox/Kerosene rocket engine. 980 kN. Keldysh Bomber. Design 1946. Nominal design engine for 1946 Keldysh bomber design. The Soviet Union would not produce an engine with these propellants and thrust levels until nearly 20 years later. Isp=285s.
RKK.
Rocket-Space Corporation or Rocket-spacecraft complex (Russian abbreviations)
RKK Energia.
Manufacturer's designation for Marpost manned mars expedition.
RKK Energia (1976).
Fifth Owner of Korolev
RKO.
Orbital Radio Control Station (Russian abbreviations)
RKS.
Adjustment of Apparent Velocity (Russian abbreviation)
RKV-.
Air-launched cruise missile (designation numbering series) (Russian abbreviations); or Rose Knot Victor tracking ship
RL-.
Liquid rocket (designation numbering series, Pratt and Whitney)
Pratt and Whitney lox/lh2 rocket engine family. First flight 1961. Originally planned for use in Centaur upper stage for Atlas, but earliest successful flights in Saturn IV stage for Saturn I. Throttleable version designed for direct-landing Apollo mission, but cancelled. Sea-level version used in DC-X SSTO test vehicle. Numerous developed versions used in Atlas, Atlas V, Delta IV upper stages. Only production American upper-stage lox/lh2 engine.
Pratt and Whitney lox/lh2 rocket engine. 66.7 kN. Isp=410s. Early version as proposed for Nova A, Nova B, Saturn B-1, Saturn C-2, Saturn C-3, Saturn I. First flight 1961.
Pratt and Whitney lox/lh2 rocket engine. 66.7 kN. Isp=425s. Version used on Atlas Centaur LV-3C, and proposed for various early Saturn launch vehicle designs. First flight 1961.
Pratt and Whitney lox/lh2 rocket engine. 65.6 kN. Study 1968. Isp=444s. First flight 1967.
Pratt and Whitney lox/lh2 rocket engine. 73.4 kN. Isp=444s. Used on Centaur stage atop Atlas G, Atlas I, Atlas II, Titan 4. First flight 1984.
Pratt and Whitney lox/lh2 rocket engine. 92.5 kN. Out of production. Isp=449s. Centaur stage for Atlas IIA, Atlas IIAS. First flight 1992.
Pratt and Whitney lox/lh2 rocket engine. 99.1 kN. Out of production. Isp=451s. Used on Atlas IIIA launch vehicle. First flight 2000. Version with one of engines removed; remaining engine re-positioned to center-mount; new electro-mechanical gimbals.
Pratt and Whitney lox/lh2 rocket engine. 99.1 kN. In production. Isp=451s. Used on Atlas IIIB launch vehicle. First flight 2002. Two engines; electro-mechanical thrust vector control actuators replaced earlier hydraulically actuated system.
Pratt and Whitney lox/lh2 rocket engine. 64.7 kN. Isp=373s. Throttleable to 30% of thrust, sea level version of RL10. Four engines were built and were used on the DC-X and the upgraded DC-XA VTOVL SSTO launch vehicle demonstrators. First flight 1993.
Pratt and Whitney lox/lh2 rocket engine. 100.488 kN. Kistler proposal. Design 1992. Isp=398s. Throttleable to 30% of thrust, sea level version of RL10 with extendable nozzle for high altitude operation.
Pratt and Whitney lox/lh2 rocket engine. 110 kN. In production. Isp=462s. Used on Delta 3 , Delta IV launch vehicles. First flight 1998. Extendable exit cone for increased specific impulse; electromechanical actuators replace hydraulic systems.
Pratt and Whitney lox/lh2 rocket engine. 93.4 kN. Design concept 1994. Isp=470s.
Pratt and Whitney lox/lh2 rocket engine. 155.7 kN. In Production. Used in Delta 3 - 2. Isp=450s. First flight 1998.
Pratt and Whitney lox/lh2 rocket engine. 110.8 kN. Design concept 1994. Isp=450s.
Pratt and Whitney lox/lh2 rocket engine. 290 kN. Development. Isp=472s. Advanced, high-performance upper-stage rocket engine proposed by Pratt & Whitney for both domestic and international launch vehicles.
Pratt and Whitney lox/lh2 rocket engine. 289.1 kN. Design. Isp=470s. Upper stage engine to have been developed by Pratt and Whitney with several international partners. Same dimensions as the RL-10, but over twice the thrust.
RLA.
The RLA (Rocket Flight Apparatus) family of modular, lox/kerosene powered vehicles were designed by Glushko in 1974 to meet the Soviet military's third-generation space launch requirements. The approach was rejected by 1976 in favor of the Zenit/Energia family using both lox/kerosene amd lox/hydrogen stages.
RLA.
Russian heavy-lift orbital launch vehicle. The RLA (Rocket Flight Apparatus) family of modular, lox/kerosene powered vehicles were designed by Glushko in 1974 to meet the Soviet military's third-generation space launch requirements. The approach was rejected by 1976 in favor of the Zenit/Energia family using both lox/kerosene amd lox/hydrogen stages.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 800,000/45,000 kg. Thrust 11,700.00 kN. Vacuum specific impulse 337 seconds. Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design.
Russian heavy-lift orbital launch vehicle. Medium booster concept with a payload to low earth orbit of 30 metric tons using the RLA-120 core and a 150 metric ton upper stage. Glushko proposed that the RLA-120 would boost reconnaissance satellites and modules of his POS Permanent Orbital Station into a sun synchronous orbit beginning in 1979. The government rejected the RLA concept, but this design led directly to the successful Zenit-2 booster.
Glushko Lox/Kerosene rocket engine. 12,700 kN. Design 1974. Proposed engines for the RLA series launch vehicles. This version would use four chambers. 'Down-sized' to 200 tonnes thrust for Energia.
Russian heavy-lift orbital launch vehicle. Heavyweight booster concept with a payload to low earth orbit of 100 metric tons using two modules as the first stage and the RLA-120 core. Glushko proposed that the booster could launch a Soviet manned lunar landing by 1981. The government rejected the RLA concept, but it did lead to the Zenit-2 and Energia boosters of the 1980's.
Russian heavy-lift orbital launch vehicle. Super-booster concept with a payload to low earth orbit of 250 metric tons using six modules as the first stage and the RLA-120 core. Glushko proposed that the booster could launch a Soviet manned Mars landing by 1983. The government rejected the RLA concept, but it did lead to the Energia booster of the 1980's.
Lox/Kerosene propellant rocket stage. Loaded/empty mass 150,000/10,000 kg. Thrust 2,940.00 kN. Vacuum specific impulse 349 seconds. Empty mass, specific impulses, length estimated by comparison to smaller Zenit successor design.
Glushko Lox/Kerosene rocket engine. 3187 kN. Design 1974. Proposed for the RLA series launch vehicles and the UR-700M Mars booster. Following rejection of RLA, design 'down-sized' to 200 tonnes thrust for Energia and Zenit.
Glushko Lox/Kerosene rocket engine. 6370 kN. Design 1972. Two-chamber version of RLA-300. Proposed for the RLA series launch vehicles and the UR-700M Mars booster.
RM.
American earth micrometeoroid satellite. 2 launches, 1968.08.16 (RM-18) and 1970.11.09 (RM-1; RMS). Spacecraft engaged in research and exploration of the upper atmosphere or outer space.
Rocketdyne hydrazine monopropellant rocket engine. 44 mN. Spacecraft. Pressure-fed. Isp=91s.
Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Satellite Reaction Control System. Pressure-fed. Isp=238s.
American test vehicle. Two-stage test vehicle to make heat transfer studies at high speed in free flight, launched from NACA's Pilotless Aircraft Reserach Station at Wallops Island, Va. Vehicle was developed by PARD of Langley Laboratory.
Rocketdyne N2O4/MMH rocket engine family. Satellite applications.
Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Spacecraft. Pressure-fed. Isp=301s.
Rocketdyne Nitric acid/UDMH rocket engine. 0.441 kN. Satellite Reaction Control. Pressure-fed. Isp=283s.
Rocketdyne N2O4/Aerozine-50 rocket engine. 0.441 kN. Lunar Flyer. Pressure-fed. Isp=296s.
Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control System. Pressure-fed. Isp=245s.
Cooper solid rocket engine. 26 kN.
Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Reaction Control. Pressure-fed. Isp=238s.
Cooper solid rocket engine. 12.7 kN.
Rocketdyne lox/lh2 rocket engine. 6.660 kN. Space Shuttle Orbiter Auxiliary Propulsion. Pressure-fed. Isp=400s.
RM-1600.
Manufacturer's designation of RESA-5 N2O4-MMH rocket engine.
Russian surface-to-air missile. Drone version.
Russian target drone. Retired 207A missiles converted to use as target drones were given this designation and the code name Belka.
Russian surface-to-air missile. Drone version.
Russian target drone. Retired 217M missiles converted to use as target drones were given this designation and used in a large number of versions (code named Zvezda-1, -2, -3, -4, -4MV, -5, -5F).
Rocketdyne N2O4/MMH rocket engine family. Spacecraft.
Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressure-fed. Isp=286s.
Rocketdyne N2O4/MMH rocket engine. 0.107 kN. Spacecraft. Pressure-fed. Isp=300s.
GCR solid rocket engine. 8.6 kN.
RM-50.
Manufacturer's designation of RESA-2 N2O4-MMH rocket engine.
RM-81.
Alternate designation for Agena A rocket stage.
Rocketdyne N2O4/MMH rocket engine. 4.001 kN. Shuttle Orbiter Reaction Control. Pressure-fed. Isp=309s.
RME.
American military strategic defense satellite. One launch, 1990.02.14, USA 52. The Relay Mirror Experiment (RME) was launched as a dual payload with LACE.
RMS.
Remote Manipulator System
RMU.
Remote maneuvering unit
RN.
Royal Navy, UK.
RN.
Royal Navy
RN-6.
Rocketdyne nuclear/lh2 rocket engine. Nuclear Deep Space. Nuclear.
RNAF.
RNAF
RNGC.
Revised New General Catalog
RNII.
Reactive Propulsion Scientific-Research Institute (Russian abbreviation)
Russian sounding rocket. P I Ivanov at RNII (Reaction Scientific Research Institute) developed a four-stage solid rocket capable of reaching 40 km altitude in 1944-1946. Two launches were made, but the project was considered generally unsuccessful and not followed up.
RO.
RO.
RO-1.
Manufacturer's designation of S2.1200 rocket engine.
RO1-154.
Alternate designation for RD-0200 Nitric acid-Amine rocket engine.
RO-200.
Alternate designation for RD-0120 Lox-LH2 rocket engine.
Kosberg nuclear/lh2 rocket engine. 392 kN. UR-700 Third Stage. Study 1967. Engine proposed for UR-700 third stage to achieve 250 tonne payload to low earth orbit. Probably closely related to RD-0411.
RO-5, RD-428.
Alternate designation for RD-0105 Lox-Kerosene rocket engine.
RO-97.
Alternate designation for RD-0126 Lox-LH2 rocket engine.
RO-97A.
Alternate designation for RD-0126A Lox-LH2 rocket engine.
RO-97E.
Alternate designation for RD-0126E Lox-LH2 rocket engine.
One man in Russia filmed the future - before Sputnik! Did Kubrick copy his work?
Roberts, Katherine Eileen Sparks (1954-) American engineer military spaceflight engineer astronaut, 1982-1987.
Roberts, Walter O (1915-1990) American astronomer, heavily involved in the debate over "nuclear winter" and the possibility of the "Greenhouse Effect" on the Earth in 1980s.
Originally known as the Georgia Air Depot, this major Air Force maintenance facility was established in 1941.
Robinson, Dr Stephen Kern (1955-) American engineer mission specialist astronaut. Flew on STS-85, STS-95, STS-114, STS-130.
Robo.
American manned combat spacecraft. Study 1955. Hypersonic manned rocket bomber project of the 1950's. Predecessor to Dynasoar.
American logistics spacecraft. Studied for ISS, but cancelled when the station's free-flying space platforms were deleted.
American sounding rocket. The Rockair technique (research rocket launched from aircraft) was developed by the Office of Naval Research and the University of Maryland. A 2.75-inch FFAR rocket was fired from a Navy F2H-2 Banshee aircraft to an altitude of approximately 60,000 m.
Solid rocket stage. 3.60 kN (809 lbf) thrust.
American air-launched sounding rocket. This USAF version of the Navy Rockair (research rocket launched from aircraft) vehicle consisted of a Deacon rocket launched from an F-86D Sabrejet fighter.
Category applied to unguided rockets.
American test vehicle. In the 1960's Bell Aerosystems caught the public imagination with a series of rocket and jet-powered rocket belts. Rocket belt-equipped fliers became a symbol of the future and a fixture at World Fairs, football games, etc. But the technology was too expensive and limited to ever be adopted for military or civilian terrestrial purposes.
Rocket Bomber.
Alternate designation for Robo manned combat spacecraft.
American manned lunar lander. Study 2005. In 2005 SpaceDev resurrected the 1960 NASA Langley individual crew lunar lander concept.
Rocket Research.
First Owner of Redmond
Rocketdyne.
First name of Pratt and Whitney
Rocketdyne, USA.
Rocketdyne Division of North American (1955).
Second Owner of Rocketdyne
RocketLab.
Category of launch vehicles and spacecraft.
Category of persons.
American manned spaceplane. Study 2015. The Rocketplane XP Vehicle was a proposed suborbital manned spaceplane with accommodations for four crew.
American sounding rocket. Meteorological sounding rockets that could use Loki Datasonde, Arcas, or Deacon rockets as the booster.
Solid rocket stage.
American air-launched sounding rocket. The Rockoon (balloon-launched rocket) consisted of a small high-performance sounding rocket launched from a balloon above most of the atmosphere. The Rockoon low-cost technique was conceived during an Aerobee firing cruse of the Norton Sound in March 1949. Rockoons were first launched from icebreaker Eastwind off Greenland by an ONR group under James A. Van Allen. They were later used by ONR and University of Iowa research groups in 1953-55 and 1957, from ships in sea between Boston and Thule, Greenland. A variety of upper stage rocket stages were used.
The Rockoon (balloon-launched rocket) consisted of a small high-performance sounding rocket launched from a balloon above most of the atmosphere. The Rockoon low-cost technique was conceived during an Aerobee firing cruse of the Norton Sound in March 1949. Rockoons were first launched from icebreaker Eastwind off Greenland by an ONR group under James A. Van Allen. They were later used by ONR and University of Iowa research groups in 1953-55 and 1957, from ships in sea between Boston and Thule, Greenland. A variety of upper stage rocket stages were used.
Rocksonde.
Alternate designation for PWN-5 sounding rocket.
Rockwell.
First name of North American
Rockwell.
Second name of Seal Beach
Rockwell International Corp.
Fifth Owner of North American
Rockwell Rocketdyne (1966?).
Third Owner of Rocketdyne
American manned rescue spacecraft. Study 1976. The Rockwell Spherical Heat Shield escape concept used a return capsule shell like a Vostok capsule cut in half. Two crew could be returned in a pressurized environment. Mass per crew 220 kg.
Taiwanese earth sea satellite. 3 launches, 1999.01.27 (ROCSAT-1) to 2008.10.01 (ROCSAT 2). Taiwan's ROCSAT (Republic of China Satellites) were built for Taiwan's National Space Program Office.
Rodimov, Petr Vadilyevich (1902-1996) Russian officer. Colonel-General, professor, Chief of Mozhaiskiy Academy in Leningrad 1947-1969. Entered military in 1923. Graduated Zhukovskiy Academy 1932. After the war deputy commander of the 16th Air Army for Engineering Service.
ROentgen SATellite.
Alternate designation for ROSAT x-ray astronomy satellite.
Rogers, Russell Lee (1928-1967) American test pilot astronaut, 1962-1963.
Rogers, William P (1913-) American politician, chair of the presidentially-mandated blue ribbon commission investigating the Challenger accident in January 1986
Indian earth land resources satellite. 2 launches, 1980.07.18 (Rohini RS-1) and 1983.04.17 (Rohini 3). Experimental-technology mission.
Indian technology satellite. One launch, 1979.08.10.
Indian technology satellite. One launch, 1981.05.31.
Rokot.
Popular Name of UR-100N missile and launch vehicle.
Russian all-solid orbital launch vehicle, consisting of decommissioned UR-100N ICBMs with a Briz-KM upper stage.
Russian all-solid orbital launch vehicle. Version with Briz-K upper stage.
N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,565/1,600 kg. Thrust 19.60 kN. Vacuum specific impulse 326 seconds. High performance storable liquid engine. The basic stage can be adapted with 'wrap-around' propellant tanks for Proton booster applications.
Roksonde.
Alternate Designation of PWN-5 sounding rocket.
roll.
The rotational or oscillatory movement of a spacecraft or similar body about a longitudinal axis through the spacecraft.
British manufacturer of rocket engines. Rolls Royce, UK.
ROM.
Rough order of magnitude
Romanenko, Yuri Viktorovich (1944-) Russian pilot cosmonaut. Flew on Salyut 6 EO-1, Salyut 6 EP-8, Mir LD-1. Father of cosmonaut Roman Romanenko. 430 cumulative days in space.
Romanenko, Roman Yuriyevich (1971-) Russian pilot cosmonaut, 1997-on. Son of cosmonaut Yuri Romanenko. Graduated from Chernigov Higher Military Air School of Pilots, 1992 Russian Air Force. Cosmonaut training completed November 19. 1999.
Romania
Romanian AF.
Romanov, Valeri Aleksandrovich (1946-) Russian engineer cosmonaut, 1978-1987. Graduated from Bauman-Higher School, Moscow, 1970 Civilian Engineer, Chelomei OKB. Worked with NPO Salyut.
Russian intercontinental ballistic missile. Pad-launched version.
Romb.
Alternate designation for Taifun-2 military target satellite.
Romb.
Russian military target satellite. Study 1971. Radar reflective subsatellites, released by Taifun-1, Taifun-2, and Taifun-3 spacecraft, for calibration of PVO air and space defense radars.
American SSTO VTOVL orbital launch vehicle. Bono original design for ballistic single-stage-to-orbit (not quite - it dropped liquid hydrogen tanks on the way up) heavy lift launch vehicle. The recoverable vehicle would re-enter, using its actively-cooled plug nozzle as a heat shield.
Lox/LH2 propellant rocket stage. Loaded/empty mass 5,102,041/306,175 kg. Thrust 101,900.00 kN. Vacuum specific impulse 455 seconds. 36 x plug-nozzle engines (20 atm chamber pressure, 7:1 mixture ratio)
Lox/LH2 propellant rocket drop tank. Loaded/empty mass 107,501/18,143 kg. Vacuum specific impulse 455 seconds. Eight of these liquid hydrogen tanks would be mounted around the core of Rombus and stage in pairs at 130 seconds, 196 seconds, and 300 seconds after launch.
Rominger, Kent Vernon (1956-) American test pilot astronaut. Flew on STS-73, STS-80, STS-85, STS-96, STS-100.
Headquarters of an RVSN Division, 1961-1992. Probably an R-12 missile base.
Ronney, Paul David (1957-) American engineer payload specialist astronaut, 1996-1997. Alternate Payload Specialist for STS-83 Mission MSL-1.
Rook.
Single stage vehicle consisting of a Rook solid rocket motor. Used initially for supersonic tests of aircraft models.
Rook.
British test vehicle. Single stage vehicle consisting of a Rook solid rocket motor. Used initially for supersonic tests of aircraft models.
Rook.
Royal Ordnance solid rocket engine. 300 kN. Out of production. Fast-burning version of Raven. Rook was fired 70 times altogether, in 65 flights and 16 different vehicle designs.
Rook.
Solid rocket stage. 300.00 kN (67,443 lbf) thrust. Mass 1,057 kg (2,330 lb).
Solid rocket stage. 300.00 kN (67,443 lbf) thrust. Mass 1,057 kg (2,330 lb).
British test vehicle.
Solid rocket stage. 300.00 kN (67,443 lbf) thrust. Mass 1,057 kg (2,330 lb).
Solid rocket stage. 300.00 kN (67,443 lbf) thrust. Mass 1,057 kg (2,330 lb).
Roosa, Stuart Allen 'Stu' (1933-1994) American test pilot astronaut. Flew on Apollo 14. Died of viral pneumonia, a complication of pancreatitis.
American SSTO orbital launch vehicle. Bono's first design for a reusable single stage to orbit LH2/Lox booster, using conventional engines.
Lox/LH2 propellant rocket stage. Loaded/empty mass 10,898,000/608,000 kg. Thrust 165,447.00 kN. Vacuum specific impulse 410 seconds.
American SSTO orbital launch vehicle. Bono's first design for a reusable single stage to orbit LH2/Lox booster, using Improved Specific Impulse approach: many engines feeding into single large nozzle.
Lox/LH2 propellant rocket stage. Loaded/empty mass 6,218,000/435,000 kg. Thrust 101,842.00 kN. Vacuum specific impulse 455 seconds.
American sounding rocket. Rooster was a variant of the Arcas sounding rocket. Instead of a temperature transmitter, it used a ROBIN (Rocket Balloon Instrument) inflatable falling sphere as its payload.
Soviet military nuclear-reactor powered radar naval reconnaissance satellite network.
ROS-17K.
Manufacturer's designation for Multipurpose Satellite Gals earth resources radar satellite.
Rosamund Dry Lake, California
Air-launched rocket drop zone known to have been used for 18 launches from 1959 to 1960, reaching up to 26 kilometers altitude.
German x-ray astronomy satellite. One launch, 1990.06.01. West German extreme UV, X-ray telescope; all-sky survey.
Rosen, Harold A (1926-) American Hughes Engineer. Harold A. Rosen was one of the key scientists at the Hughes Aircraft Company who developed Syncom, the first geosynchronous communications satellite, for NASA. He received the National Medal of Technology in 1985.
Rosen, Herbert H American engineer, deputy director of the office of public information in NASA in early 1960.
Rosen, Milton W (1915-) American engineer, at NRL 1940-1957. Supervised Viking rocket 1947-1955, Vanguard rocket 1955-1958. Took the fall for Vanguard's loss of space race to Sputnik. At NASA 1958-1974, involved in key launch vehicle decisions 1958-1963.
Rosenbaum, Mortimer (1914-) American engineer. Vice President of Engineering for the Atlas program.
European comet probe. One launch, 2004.03.02. European comet orbiter/landing mission.
Rosinski, Werner Kurt-Otto (1914-2000) German-American expert in guided missiles during World War II. As of January 1947, working at Fort Bliss, Texas. Worked his entire life with the rocket team, at Fort Bliss, White Stands, and then at Huntsville. Died at Huntsville, Alabama.
Ross.
Ross, Jerry Lynn (1948-) American test pilot mission specialist astronaut. Flew on STS-61-B, STS-27, STS-37, STS-55, STS-74, STS-88, STS-110. Held world record of seven spaceflights. US record of nine spacewalks.
Ross, Chandler Cole 'Chan' (1913-1991) American engineer. Director of numerous advanced projects at Aerojet (including Aerotojet, Aerorocket, NERVA).
Ross, H E British engineer, leader of the British Interplanetary Society from 1933. Originated 1939 article that outlined a method of accomplishing a manned lunar mission.
Rosselevich, Igor Aleksandrovich (1918-1991) Russian engineer. Chief Designer 1954-1983 of Nll-380. Specialised in television systems for spacecraft
Rossiskoye Kosmicheskoye Agentsvo (Russian Space Agency).
First Owner of RAKA
Rossitto, Franco (1940-) Italian physicist payload specialist astronaut, 1984-1986.
Rossmann, Theodor German expert in weapons during World War II. As of January 1947, working at Wright Field, Ohio.
Rostow, Walt W (1916-2003) American economist, assistant to presidents Kennedy and Johnson for national security affairs.
XCOR Lox/Kerosene rocket engine. 22.250 kN. First stages. Developed in 1990's. Developed and tested by Rotary Rocket for their launcher before its cancellation.
Roth.
Roth, Ludwig (1909-1967) German engineer in WW2, member of the Rocket Team in the United States thereafter.
Rothe, Heinrich (1907-2005) German-American expert in guided missiles during World War II. As of January 1947, working at Fort Bliss, Texas. Worked his entire life with the rocket team, at Fort Bliss, White Stands, and then at Huntsville. Died at Huntsville, Alabama.
Sounding rocket launch location known to have been used for 26 launches in 1998, reaching up to 100 kilometers altitude.
American SSTO VTOVL orbital launch vehicle. The Roton was a fully reusable, single-stage-to-orbit, vertical take-off and landing piloted space vehicle designed to transport two crew members and 3200 kg of payload to and from a 300 km / 50 degree inclination earth orbit. It used a unique rotor system for recovery. Although a subscale landing test vehicle was built and received enormous media attention, the concept never made much technical sense.
American manned spacecraft. Study 2000. The Roton was a piloted commercial space vehicle design intended to provide rapid and routine access to orbit for both its two-person crew and their cargo.
American manufacturer of rockets and spacecraft. Roton, USA.
Rotor.
Code name for Zenit-4M military surveillance satellite.
ROUS.
Rodents Of Unusual Size (I don't believe they exist)
Rover.
Alternate designation for Nerva rocket stage.
American manned lunar rover. Study 1992. Boeing updated their Apollo-era MOLAB pressurized rover concept in 1992. The concept, dubbed "Rover First," was smaller than the traditional pressurized rovers, and did not require a separate landing vehicle.
NASA-AEC research and development program of nuclear reactor propulsion for rockets
Royal Malaysia AF.
British manufacturer of rocket engines. Royal Ordnance, UK.
Rozhdestvensky, Valeri Illyich (1939-) Russian engineer cosmonaut. Flew on Soyuz 23.
RP.
Rocket interceptor (Russian abbreviations)
RP.
Russian military anti-satellite system. Study 1985. For interception of enemy ICBM's during boost phase NPO Energia developed a space based rocket interceptor (RP) similar to American 'Brilliant Pebble' systems.
Russian manned rocketplane. Korolev adapted his SK-9 glider in 1936 as the first rocked-powered aircraft in the Soviet Union.
Dushkin Lox/Kerosene rocket engine. Out of Production.
RPI.
American manufacturer of rocket engines and rockets. RPI, USA.
RPM.
Revolutions Per Minute, also Roll Positioning Mechanism.
RPRV.
Remotely piloted research vehicle
RR.
Rendezvous radar
RRSS.
German manufacturer. Return and Rescue Space Systems, Germany.
RS.
Russian intermediate range cruise missile. Soviet Mach 3 manned air-launched ramjet aircraft, developed in 1954-1961, but cancelled before the first full-scale test article could be flown.
RS-.
Strategic missile (designation numbering series) (Russian abbreviations); or Rocket shell (Russian abbreviations)
RS-10.
RS-10M.
Alternate designation for UR-100K intercontinental ballistic missile.
RS-10MUTTKh.
Alternate designation for UR-100U intercontinental ballistic missile.
RS-12.
Alternate designation for RT-2 intercontinental ballistic missile.
RS-12M.
Alternate designation for Topol missile.
RS-12M1 / RS-12M2.
Alternate designation for Topol M intercontinental ballistic missile.
RS-12UTTKh.
Alternate designation for RT-2P intercontinental ballistic missile.
RS-14.
Treaty designation for Temp-2S intercontinental ballistic missile.
Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Minuteman Postboost Velocity Control. Pressure-fed. Isp=315s. First flight 1970.
Rocketdyne N2O4/MMH rocket engine. 0.098 kN. Minuteman Pitch, Yaw & Roll Control. Pressure-fed. Technology engine, developed, but not produced. Led to RS-14 prodution engines. Isp=259s.
Rocketdyne N2O4/MMH rocket engine. 0.078 kN. Minuteman Pitch, Yaw & Roll Control. Pressure-fed. Technology engine, developed, but not produced. Led to RS-14 prodution engines. Isp=230s.
RS-16.
Alternate designation for MR-UR-100 intercontinental ballistic missile.
RS-16B.
Alternate designation for MR-UR-100U 15A16 intercontinental ballistic missile.
RS-17.
Manufacturer's designation of AMPS-1 Lox-LH2 rocket engine.
RS-18.
Rocketdyne N2O4/Aerozine-50 rocket engine. 15.563 kN. Apollo Lunar Ascent Module Engine. Pressure-fed. Isp=310s.
RS-18A.
Alternate designation for UR-100N missile.
RS-18B.
Alternate designation for UR-100NU intercontinental ballistic missile.
Rocketdyne exotic ClF3/Hydrazine rocket engine. Launch thrust 3.108 kN. Condor Development Booster Air-to-Ground Missile. Pressure-fed. Thrust and specific impulse values are at sea level.
RS-20A.
Alternate designation for R-36M intercontinental ballistic missile.
RS-20B.
Alternate designation for R-36MU 15A18 intercontinental ballistic missile.
RS-20K.
Alternate designation for Dnepr intercontinental ballistic missile.
RS-20V.
Alternate designation for R-36M2 15A18M intercontinental ballistic missile.
RS-21.
Rocketdyne lox/lh2 rocket engine. Launch thrust 2047.6 kN. Next Generation Launch Vehicle Booster. Full flow staged combustion, pump-fed. Thrust and specific impulse values are at sea level.
Rocketdyne N2O4/MMH rocket engine family. Derivative of RS-14 Minuteman engine.
Rocketdyne N2O4/MMH rocket engine. 1.333 kN. Mars Mariner. Pressure-fed. Derivtive of RS-14 Minuteman engine. Isp=287s. First flight 1971.
Rocketdyne N2O4/MMH rocket engine. 1.333 kN. Viking. Pressure-fed. Derivtive of RS-14 Minuteman engine. Isp=294s. First flight 1975.
RS-22.
Manufacturer's designation of FLEXEM ClF3-Hydrazine rocket engine.
RS-22.
Treaty designation for RT-23 15Zh52 intercontinental ballistic missile.
Rocketdyne lox/lh2 rocket engine family. Linear Aerospike Engine developed for use on the Lockheed Reusable Launch Vehicle, the production follow-on to the X-33.
Rocketdyne lox/lh2 rocket engine. 2201 kN. Development cancelled 1999. Isp=455s. Linear Aerospike Engine developed for use on the Lockheed Reusable Launch Vehicle, the production follow-on to the X-33.
RS-22A.
Alternate designation for RT-23U 15Zh60 intercontinental ballistic missile.
RS-22B.
Alternate designation for RT-23U 15Zh61 intercontinental ballistic missile.
Rocketdyne N2O4/MMH rocket engine. 26.670 kN. Space Shuttle Orbiter Orbit Maneuvering System. Pressure-fed. Isp=313s. First flight 1981.
RS-24.
Alternate designation for SSME Lox-LH2 rocket engine.
Russian intercontinental ballistic missile. New mobile, solid-propellant ICBM, heavier than the Topol-M, designed to carry up to ten MIRV warheads and to replace the R-36M2 and UR-100N liquid propellant missiles.
RS-25.
Manufacturer's designation of SSME Lox-LH2 rocket engine.
Rocketdyne Lox/Kerosene rocket engine family. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher; replaced the MB-3 as the main system for that launcher. Completed Delta service on the 6000 model in 1992, but continued in use as part of the Atlas MA- 5A powerplant until the retirement of the Atlas.
Rocketdyne Lox/Kerosene rocket engine. 1023 kN. Out of production. Isp=295s. Consisted of RS2701A/B main engine, and twin LR101-NA-11 verniers. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher; replaced the MB-3. First flight 1972.
Rocketdyne Lox/Kerosene rocket engine. 1054.2 kN. . Isp=302s. Replaced the RS-27 as the main system for the Delta and in the MA- 5A for the Atlas. RS2701B main engine, and twin LR101-NA-11 verniers. First flight 1989.
Rocketdyne Lox/Kerosene rocket engine for Delta 7000. 1054.2 kN. Isp=302s. First flight 1990.
Rocketdyne N2O4/MMH rocket engine. 2.667 kN. Space Shuttle Orbiter Reaction Control. Pressure-fed. Isp=220s.
RS-30.
Manufacturer's designation of ASE Lox-LH2 rocket engine.
American technology satellite bus, first launched 2007.03.09. Ball Aerospace's RS-300 was a small, low-cost spacecraft aimed at cost-capped principle investigator led missions for Earth or space science.
RS-32.
Manufacturer's designation of LR101-NA-7 N2O4-MMH rocket engine and LR101-11 Lox-Kerosene rocket engine.
Rocketdyne N2O4/MMH rocket engine. 1.392 kN. Upper Stage Target Engine Systems. Pressure-fed. Derived from Minuteman RS-14. Isp=288s.
RS-34.
Manufacturer's designation of RS-34 Attitude Control Lox-Kerosene rocket engine.
Rocketdyne N2O4/MMH rocket engine. 11.7 kN. Peacekeeper Postboost Axial Thrust. Pressure-fed. 1 main axial thruster per postboost propulsion system. Isp=308s. First flight 1983.
Rocketdyne Lox/Kerosene rocket engine. 0.304 kN. Peacekeeper Postboost Attitude Control. Pressure-fed. 8 attitude thrusters in each postboost propulsion system. Isp=255s. First flight 1983.
RS-36.
Manufacturer's designation of RS-36 Sustainer Lox-Kerosene rocket engine.
Rocketdyne N2O4/MMH rocket engine. 55.6 kN. HOE Homing Overlay Experiment Upper Stage Axial Propulsion System. Pressure-fed. Derivative of Lance propulsioon system. Isp=281s. First flight 1983.
Rocketdyne Lox/Kerosene rocket engine. 9.210 kN. HOE Homing Overlay Experiment Upper Stage Axial Propulsion System. Pressure-fed. Derivative of Lance propulsioon system. Isp=262s. First flight 1983.
Rocketdyne N2O4/MMH rocket engine. 11.960 kN. Axial Spacecraft. Pressure-fed. Isp=320s.
Rocketdyne N2O4/MMH rocket engine. 0.441 kN. Axial Spacecraft. Pressure-fed. Isp=305s.
Rocketdyne N2O4/MMH rocket engine. 0.020 kN. Attitude Control. Pressure-fed. Isp=284s.
RS-44.
Manufacturer's designation of AEC Lox-LH2 rocket engine.
Rocketdyne N2O4/MMH rocket engine. 4.4 N. Satellite Attitude Control and Stationkeeping. Pressure-fed. Isp=300s.
RS-47.
Manufacturer's designation of XLR132 N2O4-MMH rocket engine.
Rocketdyne N2O4/MMH rocket engine. 11.552 kN. Axial Spacecraft. Pressure-fed. Isp=315s.
Rocketdyne lox/lh2 rocket engine. 0.107 kN. Oxygen/Hydrogen Space Station Thruster. Pressure-fed. Technology was developed with 0.1 lb thrust resistojet by using electrically heated waste for space station propulsion. Isp=405s.
Rocketdyne Lox/Kerosene rocket engine. 1046.8 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=299s. Booster engine for Atlas II, IIA, IIAS. First flight 1991.
Rocketdyne Lox/Kerosene rocket engine. 386.4 kN. Out of production. Designed for booster applications. Gas generator, pump-fed. Isp=316s. Sustainer engine for Atlas II, IIA, IIAS. First flight 1991.
Rocketdyne lox/lh2 rocket engine family. First new large liquid-fueled rocket engine developed in America in more than 25 years. Powered the Delta IV booster. First flight 2002.
Rocketdyne lox/lh2 rocket engine. 3312 kN. In production. Isp=420s. First new large liquid-fueled rocket engine developed in America in more than 25 years. Powered the Delta IV booster. First flight 2002.
Rocketdyne lox/lh2 rocket engine. Design concept -2004. Upgrade to basic RS-68 for Delta IV Heavy growth versions. Would use a regeneratively-cooled expansion nozzle, allowing it to run hotter, with higher thrust and specific impulse.
Rocketdyne lox/lh2 rocket engine. Design concept -2004. Upgrade (details not specificed) to basic RS-68 for Delta IV Heavy growth versions.
RS-69.
Manufacturer's designation of XRS-2200 Lox-LH2 rocket engine.
Rocketdyne lox/lh2 rocket engine. 31.126 kN. Development ended 1999. Linear Aerospike SR-71 Experiment. Pressure-fed. Isp=430s.
Rocketdyne, Ottobrunn N2O4/MMH rocket engine. 55.4 kN. Isp=340s. Aestus engine enhanced with the addition of a Boeing-Rocketdyne XLR 32 turbo-pump.
RS-73.
Rocketdyne lox/lh2 rocket engine. Launch thrust 1112 kN. Next Generation Launch Vehicle Booster. Full flow staged combustion, pump-fed. Thrust and specific impulse values are at sea level.
Rocketdyne Lox/Kerosene rocket engine. Launch thrust 4002 kN. Space Shuttle Reusable First Stage. Ox-Rich staged combustion, pump-fed. Thrust and specific impulse values are at sea level.
Rocketdyne solar/lh2 rocket engine. 0.176 kN. Solar Thermal Engine. Pressure-fed. SOTV Solar Orbit Transver Vehicle. Isp=870s.
Rocketdyne lox/lh2 rocket engine. 4110 kN. Design concept -2004. New high-thrust cryogenic engine for Delta IV Heavy growth versions.
Rocketdyne H2O2/kerosene rocket engine. 44.463 kN. Next Generation Non-Toxic Upper Stage. Gas generator, pump-fed. Isp=320s.
Rocketdyne lox/kerosene rocket engine. 5159 kN. Booster stages. Development ended 2005. Isp=335s. Design for NASA's Space Launch Initiative; borrowed extensively from Russian technology developed in the forty years since the USA abandoned the F-1.
Rocketdyne rocket engine designed and built by Rocketdyne for use on Lockheed's Pad Abort Demonstration vehicle. In 2003, NASA tested the RS-88 in a series of 14 hot-fire tests, resulting in 55 seconds of successful engine operation.
RSA.
South African orbital launch vehicle. Israel and South Africa collaborated closely in rocket technology in the 1970's and 1980's. South Africa provided Israel with the uranium and test facilities it needed for its strategic weapons programmes. In exchange Israel provided aerospace technology. This included the capability of building the ten-tonne solid propellant rocket motors designed for the Israeli Jericho-2 missile. These motors were the basis of two space launchers for an indigenous 'R5b' space programme. It seems that South Africa also planned to use these motors in a series of missiles to provide a nuclear deterrent.
RSA.
Israel and South Africa collaborated closely in rocket technology in the 1970's and 1980's. South Africa provided Israel with the uranium and test facilities it needed for its strategic weapons programmes. In exchange Israel provided aerospace technology. This included the capability of building the ten-tonne solid propellant rocket motors designed for the Israeli Jericho-2 missile. These motors were the basis of two space launchers for an indigenous 'R5b' space programme. It seems that South Africa also planned to use these motors in a series of missiles to provide a nuclear deterrent.
It is conjectured that this designation was assigned to an intermediate range single-stage ballistic missile consisting of the first stage of the RSA-3. Purported mission was to strike Cuban military concentrations from mobile launchers on South African territory. The rocket motor closely followed the design of the Israeli Jericho-2 first stage.
South African intermediate range ballistic missile. It is conjectured that this designation was assigned to an intermediate range ballistic missile consisting of the first and second stages of the RSA-3. Probably very similar to, or a licensed copy of the Israeli Jericho-2 missile. A third stage apogee kick motor was added to produce the RSA-3 space launcher.
The RSA-3 satellite launcher began development as an IRBM in the 1980's because of the perceived Soviet threat and isolation of South Africa. It was developed with the assistance of Israel and was believed to be essentially identical to the Israeli Jericho missile/Shavit launch vehicle. The objective of the satellite launcher was to place a small surveillance satellite of 330 kg mass into a 41 degree, 212 x 460 km orbit around the earth. Development continued even after South African renunciation of its nuclear weapons. However the launcher was found not to be viable commercially and so was cancelled in mid-1994.
Solid propellant rocket stage. Loaded/empty mass 10,215/1,100 kg. Thrust 456.00 kN. Vacuum specific impulse 265 seconds. Source: Missile exhibit and placards, AF Museum, South Africa.
South Africansolid rocket engine. 500 kN. Out of production. Built in both Israel and South Africa for RSA-3 and Shavit. Source: Missile exhibit and placards, AF Museum, South Africa. Isp=273s. First flight 1988.
Solid propellant rocket stage. Loaded/empty mass 10,971/1,771 kg. Thrust 476.60 kN. Vacuum specific impulse 277 seconds. Source: Missile exhibit and placards, AF Museum, South Africa. Empty mass includes 583 kg for payload shroud, guidance, orientation and spin-up platform that positions stage 3 and payload for final orbital insertion burn.
South African solid rocket engine. 519 kN. In production. Built in both Israel and South Africa for RSA-3 and Shavit. Source: Missile exhibit and placards, AF Museum, South Africa. Isp=284s. First flight 1988.
Solid propellant rocket stage. Loaded/empty mass 2,048/170 kg. Thrust 58.80 kN. Vacuum specific impulse 298 seconds. Data accurate. Source: Missile exhibit and placards, AF Museum, South Africa. ARC/Rafael AUS 51 is identical.
South Africansolid rocket engine. 51 kN. In production. Israeli AUS-51 rocket motor, built in both Israel and South Africa. Isp=292s. Upper stage engine for RSA-3, RSA-4, Shavit, Shavit 1. First flight 1988.
South African all-solid orbital launch vehicle. The RSA-4 ICBM / satellite launcher was a planned follow-on to the RSA-3. A large new first stage optimised the vehicle and more than doubled the payload in comparison to the RSA-3. It is not known if the project reached the point of testing of the large motor, which was equivalent to the US Peacekeeper first stage.
Solid propellant rocket stage. Loaded/empty mass 66,000/8,000 kg. Thrust 1,520.00 kN. Vacuum specific impulse 270 seconds. Vacuum specific impulse / thrust estimated. Sea leval 139,000 kNs delivered over 73 seconds. Includes 3400 kg mass of fins, interstage and upper-stage constant-diameter fairing ('sleeve') which is jettisoned after first stage burnout.
South Africansolid rocket engine. 1520 kN. Development ended 1994. Isp=263s. Used on RSA-4 launch vehicle.
Solid propellant rocket stage. Loaded/empty mass 11,000/2,000 kg. Thrust 470.00 kN. Vacuum specific impulse 277 seconds. Essentially identical to RSA-3 second stage. Includes 1000 kg upper stage avionic section / spin table, which is jettisoned prior to stage three ignition.
South African solid rocket engine. 676 kN. Development ended 1994. Isp=275s. Used on RSA-4 launch vehicle.
Solid propellant rocket stage. Loaded/empty mass 2,000/100 kg. Thrust 59.13 kN. Vacuum specific impulse 292 seconds. Essentially identical to RSA-3 third stage. Oriented and spun up by 1000 kg avionic section/spin platform, which separates prior to ignition.
Hydrazine propellant rocket stage. Loaded/empty mass 300/100 kg. Thrust 0.40 kN. Vacuum specific impulse 230 seconds. Specific impulse estimated. Maximum propellant load indicated (hydrazine monopropellnat contained in 4 x 50 l tanks). Upper stage used for orbit circularization at apogee, dispensing of dual payloads, third station nutation damping. Equipped with 2 x 200 N engines for maneuver, 4 x 200 N for roll control, and 4 x 25 N for yaw and pitch.
RSAF.
RSAF.
RSC.
RSC
RSC Energia im S P Korolev.
Sixth Owner of Korolev
RSD-.
Intermediate range strategic missile (designation numbering series) (Russian abbreviations)
RSD-10.
Treaty designation for 15Zh45 and 15Zh45UTTKh intermediate range ballistic missiles.
RSM-.
Sea-launched strategic missile (designation numbering series) (Russian abbreviations)
RSM-25.
Alternate designation for R-27 submarine-launched ballistic missile.
RSM-40.
RSM-45.
Alternate designation for R-31 submarine launched ballistic missile.
RSM-50.
RSM-52.
Alternate designation for Rif-MA missile.
RSM-52.
RSM-52M.
Alternate designation for R-39UTTKh submarine-launched ballistic missile.
RSM-52V.
Alternate designation for R-39M submarine-launched ballistic missile.
RSM-54.
Treaty designation for R-29RM submarine-launched ballistic missile.
RSM-56.
Alternate designation for Bulava intercontinental ballistic missile.
RSN.
Real Soon Now
RSRI.
Saudi agency overseeing development of spacecraft. Riyadh Space Research Institute, Riyadh, Saudi Arabia.
RSRM.
Thiokol solid rocket engine. 11,520 kN. Study 1996. After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements. Isp=267s.
Russian intercontinental ballistic missile. SS-18 Replacement. The designation SS-X-26 was originally assigned to the RSS-40, but the number was reused for another missile after its cancellation.
RSS-52.
Russian air-launched test vehicle. Hypersonic ramjet-powered research vehicle proposed by Myasishchev in 1958. This version of the cancelled Buran intercontinental cruise missile would have been air-launched at supersonic speed from a derivative of the M-50 bomber. It would then use its own ramjet to accelerate to hypersonic velocity.
American manufacturer. RS-Systems, USA.
RS-X.
Rocketdyne Lox/Kerosene rocket engine. 1890 kN. Design concept -1997. Employed existing Delta and Atlas MA and RS engine hardware with a new thrust chamber assembly to generate a thrust of 1890 kN for ELV applications.
Rocketdyne lox/lh2 rocket engine. 8230 kN. Design concept -2004. New high-thrust cryogenic engine concept for Next Generation Delta with 7 m diameter modules.
RT-.
Solid rocket (designation numbering series) (Russian abbreviations)
RT-1.
The RT-1 (RT = rocket, solid in Russian) was the first large Soviet solid propellant ballistic missile. It was developed and tested in 1959-1963, but no production was undertaken due to its poor performance.
Solid propellant rocket stage. Thrust 900.00 kN.
Solid rocket stage. 500.00 kN (112,404 lbf) thrust. Mass 10,000 kg (22,046 lb).
Solid propellant rocket stage. Loaded mass 3,000 kg. Thrust 240.00 kN.
MITT solid rocket engine family.
OKB-1 solid rocket engine family.
MIHT solid rocket engine family.
The RT-15 IRBM used the second and third stages if the RT-2 ICBM. After protracted development in 1961-1970 with a range of alternative self-propelled mobile launchers, limited numbers ('few' to 19) of two types of launchers were deployed in 1970. The various transporters tested created confusion in the West (with designations SS-14 Scapegoat and Scamp being applied).
Russian intermediate range ballistic missile. The RT-15 IRBM used the second and third stages if the RT-2 ICBM. After protracted development in 1961-1970 with a range of alternative self-propelled mobile launchers, limited numbers ('few' to 19) of two types of launchers were deployed in 1970. The various transporters tested created confusion in the West (with designations SS-14 Scapegoat and Scamp being applied).
Russian solid rocket engine family.
Russian submarine-launched ballistic missile. Under the original resolution in 1961 starting the RT-2 programme, Makeyev was to develop a submarine-launched version of the RT-15, consisting of the first and second stages of the RT-2. It did not proceed beyond the study stage.
MITT solid rocket engine family.
RT-2.
Development of the RT-2, the Soviet Union's first solid propellant ICBM, was undertaken by Sergei Korolev and his successor from 1961-1968. It was a huge technical challenge, involving technology in which the Russians had no prior experience. The high-priority RT-2 preoccupied Korolev and his team throughout the period of the moon race, and could be considered a factor in the loss of that race to the Americans. In the end only sixty were deployed, but these provided the technical basis for Russian ballistic missiles of the 1980's and beyond.
RT-2.
Development of the RT-2, the Soviet Union's first solid propellant ICBM, was undertaken by Sergei Korolev and his successor from 1961-1968. It was a huge technical challenge, involving technology in which the Russians had no prior experience. The high-priority RT-2 preoccupied Korolev and his team throughout the period of the moon race, and could be considered a factor in the loss of that race to the Americans. In the end only sixty were deployed, but these provided the technical basis for Russian ballistic missiles of the 1980's and beyond.
Russian intermediate range ballistic missile. First and third stages of SS-13. Cancelled after 8 test firings. Claims to have been deployed briefly.
Ukrainian intercontinental ballistic missile. Following the protracted development of Shavyrin's Gnom air-augmented ICBM, it was decided to let Yangel tackle the problem of developing a 30 tonne gross mass ICBM using more conventional technology. At first a three-stage solid propellant design was considered. But it was found impossible to achieve the launch weight with such an approach. Yangel's solution was to propose the only mixed propulsion ICBM ever developed - a solid propellant first stage, and high performance ampulised storable liquid propellant second stage. The draft project for the missile was completed in December 1964 and a decree to proceed with development was issued on 24 August 1965. Shortly thereafter Shavyrin died and Gnom was cancelled, leaving Yangel's RT-20P the lead project for the mobile ICBM requirement. Designs for silo-launched and submarine-launched versions of the missile were to be developed as well.
Russian intercontinental ballistic missile. Project work began in 1963 on this three-stage solid propellant ICBM. Five train-launched variants were studied, as well as a silo-launched version. Studies were completed in 1966 but it was decided not to proceed with the concept.
OKB-1 solid rocket engine. 900 kN.
Russian intercontinental ballistic missile. The RT-22 was a follow-on study to the RT-21 for a train-launched solid-propellant ICBM. It reached the stage of an advanced project in 1969. The three stage rocket would have a total mass of 80 tonnes including its transport container. A train would have a total of 22 cars, six of which would be missile launchers.
The only rail-based ICBM ever deployed. Developed by Yuzhnoye in the Ukraine was protracted, but understandable given the huge technical challenges. Twelve years of design and testing was followed by deployment from 1988. All were retired by 2003.
Ukrainian intercontinental ballistic missile. The only rail-based ICBM ever deployed. Developed by Yuzhnoye in the Ukraine was protracted, but understandable given the huge technical challenges. Twelve years of design and testing was followed by deployment from 1988. All were retired by 2003.
Ukrainian intercontinental ballistic missile. The draft project for the silo-based RT-23 with the 15F143 warhead was completed in December 1979. Trials of this basic version began at Plesetsk on 26 October 1982. The basic RT-23 was accepted for military service on 10 February 1983, but the decision was taken not to put it into production. All resources were to be devoted to an improved RT-23UTTKh.
Ukrainian intercontinental ballistic missile. A draft project of the 15Zh52 MIRV train-based version of the RT-23 was completed in June 1980. The system was designed to allow the mobile launchers to conduct long-duration deployments up to 200 km from base.
N2O4/UDMH propellant rocket stage. Loaded mass 15,000 kg. Thrust 206.00 kN.
Ukrainian intercontinental ballistic missile. Design began of the silo-based version of the RT-23UTTKh on 9 August 1983.
Ukrainian intercontinental ballistic missile. A decree of 9 August 1982 ordered development of an improved RT-23UTTKh, dubbed 'Molodets'. Three basing modes were to be possible using a single containerised missile: train-launched, a 'Tselina-2' road-mobile transport, or silo-based. This would be able to deploy up to ten nuclear warheads from a layered circular dispenser. Retired in 2003.
Russian intermediate range ballistic missile. Decree 316-157 of 4 April 1961 authorised development of a family of solid propellant launch vehicles utilising various combinations of three stages (the RT-2, RT-15, and RT-25). The RT-25 IRBM used the first and third stages of the RT-2 ICBM. M Yu Tsirulnikov at SKB-172 in Perm was responsible for development of the RT-25. However there was little interest in this variant and in 1963 further development was dropped.
SKB-350 solid rocket engine family.
Russian intercontinental ballistic missile. The RT-2M was a modernised RT-2, developed under Savodskiy at Korolev's bureau beginning in the late 1960's in parallel with the RT-2P and using alternate new engines. This increased both range and payload compared to the RT-20. However the RT-2P was selected for further development.
RT-2M2.
Alternate Designation of Topol M intercontinental ballistic missile.
Russian intercontinental ballistic missile. Development of the improved RT-2P version of the basic missile was authorised by decree 1004-365 of 18 December 1968. The overriding concern was imminent deployment by the Americans of the Safeguard anti-ballistic missile system, and the need for the missile to have the necessary countermeasures to defeat those defences.
RT-2PM.
Manufacturer's designation for Topol missile.
RT-2PM2.
RTB.
Rocket braking stage (Russian abbreviations); or Return to base (shuttle abort mode involving shuttle separating from booster, turning around, and landing back at the Kennedy Space Center)
RTG.
Radioisotope Thermoelectric Generator (spacecraft power system) .
RTG.
RTG
RTLS.
Return To Launch Site (Shuttle abort plan)
RTS-.
Telemetry Control System (designation numbering series) (Russian abbreviations)
RTV.
JPL solid rocket engine family.
JPL solid rocket engine. 22 kN.
JPL solid rocket engine. 80 kN.
RTV-A-2.
Department of Defence Designation of Hiroc test vehicle.
RTV-A-3.
Alternate designation for Nativ test vehicle.
RTV-A-5.
Alternate designation for Navaho X-10 intermediate range cruise missile.
RTV-G-1.
Department of Defence Designation of Wac sounding rocket.
RTV-G-10.
Test vehicle for Hermes A-2 and Hermes C-1 tactical ballistic missiles.
RTV-G-3.
Alternate designation for Hermes B-1 tactical ballistic missile.
RTV-G-4.
Department of Defence Designation of Bumper-WAC short range ballistic test vehicle.
RTV-G-6.
Alternate Designation of Hermes B-1 tactical ballistic missile.
RTV-N-12.
Department of Defence Designation of Viking sounding rocket.
RTV-N-12a.
Department of Defence Designation of Viking Type 9 sounding rocket.
Dushkin rocket engine. 31 kN. Developed 1955-57.
RuAF.
Russian agency. Astronautical Federation of Russia, Russia.
American manned spacecraft. Study 2004. X-Prize suborbital ballistic spacecraft concept of STC.
German technology microsatellite. 8 launches, the first on 2000.07.15 (Rubin). Rubin was developed by OHB and students of the Hochschule Bremen.
Rubins, Kathleen Hallisey "Kate" (1978-) American scientist mission specialist astronaut, 2009-on.
French orbital launch vehicle. Two-stage test vehicle consisting of 1 x Agate + 1 x P064. It was designed to test the upper stage and payload elements of the Diamant orbital launcher. These included fairing jettison, spin-up, release, and ignition of the P064 final stage. Six launches were used to validate the design and led to the success of the Diamant on its first flight. The last four launches were made on behalf of CNES to validate payloads for the D1 satellite and carry scientific instruments for the Paris Observatory and Max Planck Institute.
Solid rocket stage. 190.00 kN (42,714 lbf) thrust. Mass 2,000 kg (4,409 lb).
Rude.
Rude, Arthur Harry (1890-1982) American manager. Vice-President of Aerojet, 1944-1966.
Ruden, Paul German expert in aeronautics during World War II. As of January 1947, living at Stuttgart.
Rudenko, Sergei Ignatyevich (1904-1990) Russian officer. First Deputy Commander-in-Chief of Air Force 1958-1968. Oversaw cosmonaut training.
Rudnev, Konstantin Nikolayevich (1911-1980) Russian government official. Director of NII-88 1950-1952. Chaired GKOT 1958-1961.
Rudolph, Arthur Louis Hugo (1906-1996) German-American rocket engineer, with Valier in 1931, von Braun from 1934. Planned V-2 production. Program manager for Redstone, Pershing, and the Saturn V. Retired 1970, but named as a war criminal, returned to Germany in 1984.
Ruediger, Walter (1901-) German measurement technician in WW2, worked in the Soviet Union thereafter. One of the group that fired V-2 rockets at Kapustin Yar in 1946.
Ruehlemann, Erich German expert in guided missiles during World War II. As of January 1947, last known to be working at Bodensee.
Rukavishnikov, Nikolai Nikolayevich (1932-2002) Russian engineer cosmonaut. Flew on Soyuz 10, Soyuz 16, Salyut 6 EP-5-1.
Runco, Mario Jr 'Trooper' (1952-) American meteorologist mission specialist astronaut. Flew on STS-44, STS-54, STS-77.
Runge, Ernst German expert in rockets during World War II at Nordhausen. Later worked in France at LRBA as a technician in the mechanics group of the automated control loop department 1947-1952.
Ruppe, Kurt Oskar Harry (1929-) German space travel expert.
Rus.
Alternate designation for Soyuz M orbital launch vehicle.
Autonomous System of Manual Control (Russian abbreviations)
Rushworth, Robert Aitken (1924-1993) American test pilot. Selected as X-15 pilot in 1958, he made the most X-15 flights and obtained astronaut wings on X-15 Flight 87. Flew 187 combat missions in Vietnam.
Russian Federation Space Systems
Designations of Russian ballistic missiles, launch vehicles, and spacecraft.
Russian Federation Space Systems.
Russian Federation Space Systems
Aelita was the Queen of Mars in the famous socialist parable filmed by Jakov Protazanov in 1924. It was altogether fitting that her name would be given to the leading Soviet plan for the conquest of the Red Planet. The Soviet Union's Korolev had the same original dream as Wernher von Braun - a manned expedition to Mars. In both cases this goal was interrupted by the 'side show' of the moon race of the 1960's. In both cases that race proved so costly and of so little public interest that political support for any Mars expeditions evaporated.
The story of rocketplanes and spaceplanes in the Soviet Union was one of constant setbacks due to internal politics, constant struggle with little result.
Perhaps no missiles ever produced had as much historical influence as the surface-to-air missiles of the Soviet Union. Originally conceived to provide a defence against the American bomber fleets of the early Cold War, they decisively affected the turn of events when they shot down American U-2 reconnaissance aircraft over Russia and Cuba. Soviet-provided missiles accounted for a hundred American aircraft over North Vietnam and set the terms of the air battle. A new generation of missiles presented a huge technological surprise and took an awful toll of Israeli aircraft in the 1973 war. To this day, Russian surface-to-air missiles provide the only defence available to most countries against American bombers, and Russian man-portable anti-aircraft missiles are a major part of the terrorist threat.
Russian Space Agency.
Third Owner of RAKA
Russia's Space Program: Running On Empty.
Part 2 of James Oberg's grim account of the fate of the Russian space program
Headquarters of an RVSN Division, 1960-1990. Base for units deployed with R-12 and later 6 Pioner missile launchers.
RV-A-10.
Test vehicle for Hermes A-2 and Hermes C-1 tactical ballistic missiles.
Rocket stage used on Hermes A-2 test vehicle.
RV-A-5.
Alternate designation for Hermes A-1 tactical ballistic missile.
RV-A-8.
Department of Defence Designation of Hermes A-3A tactical ballistic missile.
RVSN.
Russian agency overseeing development of spacecraft. Raketniye Voiska Stratigcheskovo Naznacheniya (Russian Strategic Rocket Forces), Russia.
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 4 stage separation. Vehicle consisted of an unpowered 'reusable winged drop tank' and 2-engine expendable Ariane-5 upper stage.
Indonesian indigenous sounding rocket design.
Indonesian indigenous sounding rocket design.
LAPAN solid rocket engine family.
Indonesian sounding rocket. Single stage vehicle.
LAPAN solid rocket engine. 52 kN.
Solid propellant rocket stage. Loaded mass 300 kg. Thrust 52.00 kN.
RX-320
RX-420
American space suit, tested 1964. RX-1 Litton full pressure hardsuit, weighed 40 kg, rolling convolute joint technology, 2-plane enclosure, modular sizing, 1964. Followed by RX-2, 40 kg. in 1964 and RX-2A, 36 kg in 1964.
Ryabikov, Vasili Mikhailovich (1907-1974) Russian government official. Chief of Third Chief Directorate of Council of Ministers 1951-1953. Chaired Military-Industrial Commission 1955-1957and Sputnik State Commission.
Ryan.
American manufacturer. Ryan, USA.
Ryazanskiy, Mikhail Sergeyevich (1909-1987) Russian chief designer. Chief Designer 1946-1951 and 1955-1987 of Nll-885. Specialised in missile and spacecraft radio guidance.
Ryazansky, Sergei Nikolayevich (1974-) Russian physician cosmonaut, 2003-on. Worked at IMBP, in the post of senior scientific researcher at the "Sensomotornoy, Fiziology i Profilaktiky" department. Cosmonaut training 16 June 2003 - 27 June 2005.
Ryker, Norman (1926-2006) American engineer, began working at Rocketdyne. Headed North American's Apollo proposal group. Assistant Chief Engineer for Apollo. President of Rocketdyne, 1976-1983, leading development and flight of the Space Shuttle Main Engine.
Sounding rocket launch location known to have been used for 777 launches from 1970 to 2000, reaching up to 65 kilometers altitude.
Ryumin, Valeri Viktorovich (1939-) Russian engineer cosmonaut. Flew on Soyuz 25, Salyut 6 EO-3, Salyut 6 EO-4, STS-91. Was married to astronaut Yelena Kondakova. 371 cumulative days in space. Civilian Engineer, Korolev OKB
Ryusei.
Code name for OREX re-entry vehicle technology satellite.
Ryzhikov, Sergei Nikolaevich (1974-) Russian pilot cosmonaut, 2006-on. Major, VVS and PVO 14th Army (Novosibirsk / SibVO) Cosmonaut 2006-10-11 to .
RZ.2.
Rolls Royce Lox/Kerosene rocket engine. 836.3 kN. Isp=282s. Used on Europa launch vehicle. First flight 1964.