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The Titan launch vehicle family was developed by the United States Air Force to meet its medium lift requirements in the 1960's. The designs finally put into production were derived from the Titan II ICBM. Titan outlived the competing NASA Saturn I launch vehicle and the Space Shuttle for military launches. It was finally replaced by the USAF's EELV boosters, the Atlas V and Delta IV. Although conceived as a low-cost, quick-reaction system, Titan was not successful as a commercial launch vehicle. Air Force requirements growth over the years drove its costs up - the Ariane using similar technology provided lower-cost access to space. The reasons given for developing the booster in parallel with the NASA Saturn I of the same class were that the solid fuel boosters and storable (although corrosive and toxic) liquid propellants of the core provided a vehicle with improved readiness compared to the Saturn. However USAF 'ownership' (no NASA claims of priority) and the NIH (Not Invented Here) syndrome were probably more important factors. Whatever the controversies at its genesis, the Titan has outlived the Saturn and will continue in use in the 21st century. It was originally conceived as a carrier of manned military spacecraft - first the X-20A Dynasoar, then the Gemini B and Manned Orbiting Laboratory, and finally lifting body spaceplanes in support of MOL follow-on space stations. All of these projects were cancelled in turn. Titans have been used instead to launch unmanned military spacecraft, ranging from heavy photoreconnaisance platforms in low earth orbit to geosynchronous communications, missile launch detection, and ELINT satellites. After NASA junked the Saturn launch vehicle family in the mid-1970's, and the Challenger disaster in the 1980's, Titans were used for launching NASA deep-space probes. Whatever trouble NASA managed to get itself into, the Titan was still there to keep its planetary exploration program going. Manufacturer: Martin. Launches: 370. Failures: 41. Success Rate: 88.92%. First Launch Date: 1959-02-06. Last Launch Date: 2005-10-19. Launch data is: complete.
Version: Soltan. Status: Study 1961. The progenitor of the Titan 3 was this design, which used two, 3 segment, 100 inch diameter solid rocket boosters. The 100 inch segmented boosters had already been ground-fired by Aerojet. However the final decision was to develop the more-capable Titan 3C with 5 segment, 120 inch diameter solid rocket boosters.
The original design submitted for the SLV-4 competition had two 2.54 m diameter solid boosters. LEO Payload: 8,030 kg (17,700 lb). to: 148 km Orbit. at: 28.00 degrees. Associated Spacecraft: Dynasoar. Liftoff Thrust: 6,021.000 kN (1,353,574 lbf). Total Mass: 388,560 kg (856,620 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 40.40 m (132.50 ft). Span: 15.70 m (51.50 ft). Titan C.
The Titan C, a Titan II booster stage topped by a new liquid oxygen/hydrogen upper stage, was the launch vehicle selected in November 1959 for the DynaSoar orbital flight program. Despite the fact the upper stage engine was secretly tested in 1958-1960, after many political twists and turns, it was cancelled in favor of the Titan 3C in July 1961 The Dyna-Soar specification was formalised by the USAF on 23 August 1957 as System 464L. This 'Hypersonic Glide Rocket Weapon System' was to be a manned, winged vehicle that would be rocket-boosted to hypersonic speed. The Air Force considered 12 contractors as capable of bidding on the programme. Nine vendor teams submitted bids by March 1958. The evaluation whittled this down to two teams: Martin-Bell and Boeing. Boeing proposed to manage the entire project alone, while on the other team Bell would provide the manned glider, and Martin the launch vehicles. In a shock move, Boeing was selected for the glider in June 1959, while Martin was selected for the launch vehicles. The service greatly preferred Martin's booster proposal (Titan I for the suborbital tests, Titan C for global flights). Boeing's vague proposal was to use Atlas-Centaur for suborbital flights, and a booster 'to be determined' for orbital flights. The contract awards for Dyna-Soar were announced on November 9, 1959. By then the program was had gone down to two phases, and then back to three phases - a suborbital test Phase 1, an orbital test Phase 2, and an operational weapon system in Phase 3. The selection of the Titan C for the Phase 2 booster was controversial. This was a Titan II booster stage topped by a new liquid oxygen/hydrogen upper stage. There were several competitors. Unknown to the competitors was that Aerojet was conducting a secret program to develop the engine for the Titan C second stage. The resulting Lox/LH2 version of the Titan LR87 motor was the first large Lox/LH2 engine fired in the world. The entire development took place from 1958-1960, and was of the same magnitude as the parallel, more public modification of the LR-87 engine to burn storable propellants for the Titan 2. The Lox/LH2 engine was essentially an LR-87 regeneratively cooled thrust chamber and nozzle, with a modified injector, and redesigned fuel pump. There were a total of 52 static tests run on full scale flight-weight hardware. Sea level thrust was as high as 59,000 kgf, equivalent to 68,000 kgf in vacuum. Simple impinging stream injectors were used rather than the more expensive conventional coaxial types used later on the M-l and SSME. All start-ups and shutdowns were smooth, and the combustion efficiency reached 99%. Operation was stable throughout and there were no major leakage problems. Early tests used pressurised propellants, but the later ones used flight-type turbopump assemblies. In comparison with the Lox/Kerosene LR87, major changes were made on the injectors, and the RP-1 fuel pump was replaced by a single stage hydrogen pump specially designed for the purpose. The oxygen pump and its gearbox were unchanged from the original design. Despite this demonstrated hardware, in May 1960 Rocketdyne won NASA's competition for a 91,000 kgf upper stage Lox/LH2 engine with their paper J-2 design. Thereafter Martin and Aerojet had to propose the Titan C with a J-2 engine in the upper stage. While glider development continued at Boeing, the booster kept changing. The US Army's ABMA, led by Wernher Von Braun, had the Saturn I launch vehicle under development. There were elements in the Air Force pushing their Space Launching System family of modular launch vehicles. And there was an Air Force requirement, beyond Dyna-Soar, for development of a large booster for its SLV-4 requirement. This new vehicle would be needed by the late 1960's for launch of ten-tonne reconnaissance satellites into low orbit and heavy communications, ELINT, and early warning satellites into high orbits. The tangled Pentagon politics involved in the decisions of the time are reflected in the following memoir. General Medaris, commander of the Army Ballistic Missile Agency, related (from the Army point of view) how he was blindsided by the Titan C in the summer of 1959, and how Wernher von Braun's Saturn booster came to be involved in the Dynasoar program: We had gone through the whole process of selecting upper stages for Saturn and had made our recommendations to ARPA. We had indicated very clearly that we were willing to accept either the Atlas or Titan as the basis for building the second stage. The real difference was that in one case we would be using the Atlas engines and associated equipment, built by North American, while in the other case, we would be using the Titan power plant built by Aerojet. Largely because of the multitude of different projects that had been saddled on the Atlas, we favor the Titan. Convair built the Atlas, and we had great confidence in Convair's engineering, but this was overshadowed in our mind by the practical difficulties of getting enough Atlas hardware. However, we assured ARPA that we would take either one.It can be seen in this quotation that the Army and von Braun team were completely in the dark on the development work done by Martin and Aerojet on the Titan C by that time. So the Saturn I launch vehicle became the leading candidate to boost Dynasoar, at least in the eyes of the Pentagon's civilian bureaucracy. There were elements in the Air Force pushing yet a third vehicle - their (also very secret) visionary Space Launching System family of modular launch vehicles. Complicating matters further was an Air Force 'SLV-4' requirement, beyond Dyna-Soar, for development of a large booster. This new vehicle would be needed by the late 1960's for launch of ten-tonne reconnaissance satellites into low orbit and heavy communications, ELINT, and early warning satellites into high orbits. So production of Titan I boosters for Dynasoar Phase 1 was authorised while a decision on the orbital booster was deferred. The Titan C suffered blow after blow. On 31 May 1960, Aerojet lost the competition to Rocketdyne for development of the J-2 engine for Saturn upper stages - despite the fact that Aerojet had already completed tests of their LR87. By January 1961 it was decided to use the Titan 2 instead of the Titan 1 for the suborbital flights. In July 1961 the Air Force dropped the Titan C and Saturn I alternatives and recommended production of the Space Launching System for the SLV-4 requirement. The A-388 'Phoenix' variant of the modular booster would provide Dyna-Soar's ride to orbit. Meanwhile the first test firings of large segmented solid propellant boosters had occurred. This was a key technology for the Space Launching System. But it could equally be applied to the proven Martin Titan vehicle family. So the selection of the Space Launching System was overturned three months later and the Titan 3 became the heavy-launch vehicle for the USAF. This consisted of the Titan 2 as a core vehicle, with two large segmented solid propellant boosters. This was the end of the road for the Titan C. A month later, at the end of 1961, it was decided to dump the Titan 2 sub-orbital phase of Dyna-Soar launches, and use the Titan 3 alone for Dyna-Soar launches. LEO Payload: 7,300 kg (16,000 lb). to: 480 km Orbit. at: 28.00 degrees. Associated Spacecraft: Dynasoar. Total Mass: 185,820 kg (409,660 lb). Core Diameter: 4.06 m (13.32 ft). Total Length: 53.00 m (173.00 ft). Span: 15.50 m (50.80 ft).
Titan 1.
ICBM, built as back-up to Atlas, using two stages instead of one and a half, and conventional tank construction in lieu of balloon tanks. It was also to have been used for suborbital tests of the X-20A Dynasoar manned space plane. For unknown reasons never refurbished for use as space launcher and scrapped after being replaced by the Titan II in the missile role in mid-1960's. Historical Essay © Andreas Parsch Martin SM-68/HGM-25/LGM-25 Titan I The Titan was the second Intercontinental Ballistic Missile (ICBM) of the USAF, the USAF's first multistage design, and the largest ICBM ever deployed by the United States. In 1954, when development of the definite configuration of the SM-65 Atlas ICBM started, the USAF also awarded development contracts for alternative designs of many Atlas components, like engines, guidance system, and reentry vehicle. This was to prevent failure of the whole ICBM program in case a single component design didn't work. During 1955 it was finally decided to develop a complete second ICBM system as a full backup to Atlas. In October 1955, Martin was awarded a contract for airframe design and system integration for this "backup" ICBM, to be known as SM-68 Titan. Martin chose not to use the fragile pressure stabilized airframe design of the Atlas, and therefore the whole structure was heavier, necessitating a two-stage design. Because Titan was a true backup, not intended for full-scale development and production unless Atlas would be significantly delayed, progress was slow until 1957. However, this changed in October that year after the Soviet Sputnik launch, and it was decided to deploy both Atlas and Titan by 1962. Testing of the SM-68 finally began in late 1958, and the first launch of an XSM-68 prototype (which had only a dummy second stage) succeeded in February 1959. Development problems (several XSM-68s exploded on the pad) delayed the first successful two-stage flight until January 1960. Titan testing continued through 1961, including launches from the silo-lift launcher of the operational missile. In April 1962, the first squadron of SM-68 Titan I missiles was declared operational. The SM-68 was a two-stage liqued-fueled rocket-powered missile. The first stage used two Aerojet LR87-AJ-1 engines, and the second stage consisted of a single Aerojet LR91-AJ-1, with all engines burning kerosene (RP-1) and liquid oxygen. The SM-68 used a radio-command/inertial guidance after the originally planned all-inertial system had been transferred to the SM-65/CGM-16 Atlas. The SM-68 used the same Mk.4 reentry vehicle and W-38 warhead as the SM-65E/F Atlas E/F. The missiles were stored in widely dispersed hardended underground silos. After fueling, the Titan I had to be lifted out of the silo for launch. As with the Atlas, the non-storable liquid fuels were a safety hazard and also lead to a reaction time from order to launch of about 20 minutes. There was also am unarmed training version of the Titan I, designated USM-68A Titan Trainer. When the much more advanced LGM-30 Minuteman and LGM-25C Titan II (see below) became operational in 1963, it was decided to phase out the Titan I (together with the Atlas) as quickly as possible. Between January and April 1965, all deployed Titan Is (54 missiles) were retired from service. Total production of the Titan I was about 160 missiles, of which more than 60 were launched for tests and training. Launches: 70. Failures: 15. Success Rate: 78.57%. First Launch Date: 1959-02-06. Last Launch Date: 1965-03-05. Apogee: 1,000 km (600 mi). Associated Spacecraft: Avco Project 7969, Martin Project 7969. Liftoff Thrust: 1,295.900 kN (291,330 lbf). Total Mass: 105,142 kg (231,798 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 31.00 m (101.00 ft). Span: 3.05 m (10.00 ft). Maximum range: 11,300 km (7,000 mi). Number Standard Warheads: 1. Standard RV: Mk. 3. Standard warhead: W49. Standard warhead yield: 1,440 KT. Standard warhead CEP: 2.02 km (1.25 mi). Boost Propulsion: Liquid rocket, Lox/Kerosene. Guidance: Inertial. Maximum speed: 29,030 kph (18,030 mph). Ceiling: 1,287,800 m (4,225,000 ft). Development Cost $: 1,643.300 million. in: 1960 average dollars. Recurring Price $: 15.618 million. Total Number Built: 155. Total Development Built: 47. Total Production Built: 108. Flyaway Unit Cost $: 1.502 million. in: 1962 unit dollars.
Titan-Vanguard. Status: Design 1957. The Martin Company proposed to the Department of Defense that the first stage of the Titan I intercontinental ballistic missile be combined with the Vanguard rocket to provide a launch vehicle capable of placing an instrument package into lunar orbit and on the lunar surface. NASA was instead given the mission and used Atlas/Agena and Atlas/Centaur for this purpose instead.
Associated Spacecraft: Goodyear Project 7969.
Version: Winged Titan.
The only trace of this winged version of the Titan launch vehicle are some drawings in popular magazines ca. 1960.
ICBM, developed also as the launch vehicle for the manned Gemini spacecraft in the early 1960's. When the ICBM's were retired in the 1980's they were refurbished and a new series of launches began. The Titan 1 ICBM had been developed by Martin and Aerojet as technical insurance if the Atlas, built by Convair and Rocketdyne, had failed. The Martin team had been instructed to use the liquid oxygen/kerosene propellants used for the Atlas, even though Aerojet's prior experience was primarily with storable propellants. As early as 1957 Martin and Aerojet proposed a number of improvements to the basic Titan design, which would make the follow-on missile a much more useful weapon system. Storable propellants would eliminate the loading, just prior to launch, of the cryogenic liquid oxygen needed by the Atlas and Titan 1. A storable-propellant missile could remain fueled, stored in a silo, ready for launch at a moment's notice. The complicated elevator and fuelling apparatus of the immense Titan 1 complexes could be eliminated. The Aerojet storable propellant engines would be immensely simplified compared to the cryogenic Titan 1 engines. A new AC Spark Plug inertial navigation system would make the missile more accurate and impervious to jamming. With the new propellants, and a constant missile diameter, the improved missile would fit in the same silo and transport envelope, but have 50% greater takeoff mass, and nearly triple the payload. The Air Force authorized Martin to proceed with the Titan 2 ICBM in June 1960. In January 1961 the Titan 2 was selected to boost the Dynasoar manned spaceplane on suborbital tests, and in July 1961, to orbit the manned Gemini spacecraft. Therefore during development the ICBM had also to be man-rated. This caused some difficulties, as a pogo problem encountered in flight tests was acceptable to the Air Force for a weapon system, but unacceptable to NASA for a manned booster. The problem was solved to NASA's satisfaction, and the Titan went on to a perfect launch record during the Gemini program. Meanwhile Titan 2's were deployed in 54 fixed silos at three bases by the end of 1964. The missile was equipped with the immense W53 nuclear warhead and penetration aids to ensure that it would get through the evolving Soviet anti-ballistic missile systems around Moscow. Throughout the Cold War, the Titan 2 was the main threat to the Soviet leadership in Moscow, even within their subterranean command bunkers. It represented only 5% of America's ICBM's, but over 30% of the deliverable megatonnage. However solid propellant missiles were more attractive to Defense Secretary McNamara, and the Atlas and Titan 1 ICBM's were all decommissioned by 1966 after short service lives. But the Russians had unveiled their equivalent of the Titan 2, the awesome SS-9 Scarp (R-36) "city buster". It was politically imprudent to decommission the only American equivalent, and so the Titan 2 soldiered on as the only American liquid-propellant ICBM. It was not until 1987 that it was replaced by the solid-propellant Peacekeeper. By then the Cold War had only three more years to run. The Peacekeeper, developed at incredible expense, had a very short service life, being outlawed under missile reduction agreements after a few years service. The decommissioned Titan 2's were refurbished and used as space launchers until the last was finally expended in 2003. Modifications of the Titan 2 continued in production as the core for the Titan 3, 34, and 4 series of space launchers, until the last was finally launched in 2005. During its life the storable propellants, which resulted in a simple and extremely reliable vehicle, became prohibitively expensive. This was because they were toxic, and environmental regulations made them, eventually, unprofitable to produce and difficult to handle. Outside of the United States the forces of Environmental Correctness were not as strong. The same propellants continued in use into the 21st Century in the Ariane 4 boosters for France, the GSLV for India, the Proton and Dnepr of Russia, and the CZ series in China. The only major improvement fitted to the ICBM version of the missile during its service life was installation of the Universal Space Guidance System, developed for the Titan 3 space launcher. Otherwise the missile continued to perform with remarkable reliability in both operational missie tests and as a space booster. Total Titan 2 production and disposition was as follows:
Launches: 81. Failures: 6. Success Rate: 92.59%. First Launch Date: 1962-03-16. Last Launch Date: 1976-06-28. LEO Payload: 3,100 kg (6,800 lb). to: 185 km Orbit. Associated Spacecraft: Advanced Tiros N , Clementine, Coriolis, DMSP Block 5D-2, DMSP Block 5D-3, Landsat 6, QuikScat, Singleton, Tiros N. Liftoff Thrust: 1,893.400 kN (425,653 lbf). Total Mass: 154,000 kg (339,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 31.40 m (103.00 ft). Span: 3.05 m (10.00 ft). Maximum range: 11,690 km (7,260 mi). Number Standard Warheads: 1. Standard RV: Mk. 6. Standard warhead: W53. Standard warhead yield: 8,900 KT. Standard warhead CEP: 1.61 km (1.00 mi). Cruise Propulsion: Liquid (stor). Guidance: Inertial. Maximum speed: 29,030 kph (18,030 mph). Ceiling: 1,287,800 m (4,225,000 ft). Development Cost $: 400.000 million. in: 1963 average dollars. Recurring Price $: 16.389 million. Total Number Built: 131. Total Development Built: 23. Total Production Built: 108. Flyaway Unit Cost $: 3.158 million. in: 1969 unit dollars.
Titan II GLV.
Version for launch of Gemini manned spacecraft. Developed in parallel with ICBM version. Differed in having redundancy features in systems and MDS (Malfunction Detection System) installed. Modifications to Titan II for use as the Gemini Launch Vehicle included:
Launches: 12. First Launch Date: 1964-04-08. Last Launch Date: 1966-11-11. LEO Payload: 3,600 kg (7,900 lb). Apogee: 300 km (180 mi). Liftoff Thrust: 2,090.000 kN (469,850 lbf). Total Mass: 150,530 kg (331,860 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 32.80 m (107.60 ft). Flyaway Unit Cost $: 3.158 million. in: 1965 unit dollars.
Titan 23B. Basic Titan 3A core, originally developed for Titan 3C, with Agena D upper stage replacing Transtage. New radio guidance system, 1.5 m diameter fairing atop Agena. Payload remained attached to the Agena.
Launches: 2. First Launch Date: 1971-01-21. Last Launch Date: 1971-04-22. Apogee: 1,000 km (600 mi). Associated Spacecraft: KH-8. Liftoff Thrust: 2,300.000 kN (517,000 lbf). Total Mass: 165,000 kg (363,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 45.00 m (147.00 ft).
Titan 24B. Stretched first stage, originally developed for the cancelled MOL program, with Agena D upper stage. Radio guidance system, 1.5 m diameter fairing atop Agena. Payload remained attached to the Agena.
Launches: 23. Failures: 2. First Launch Date: 1971-08-12. Last Launch Date: 1984-04-17. Apogee: 1,000 km (600 mi). Associated Spacecraft: KH-8. Liftoff Thrust: 2,410.000 kN (541,780 lbf). Total Mass: 170,000 kg (370,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 45.00 m (147.00 ft).
Titan 2G. Intercontinental ballistic orbital launch vehicle. Department of Defence Designation: SLV-5. Space launch version, obtained through minimal refurbishment of decommissioned ICBM's. The decommissioned ICBM's received a new payload interfaces (a conical structure that provided 0.91 m, 1.42 m, and 3.05 m payload ring adapters), an attitude control system taken from the Titan 3, replacement of the second-stage verniers with retrorockets to improve payload separation, and a Titan 3 fairing, 3.05 m diameter and 6.1 to 9.2 m long. With solid propellant kick stages, the Titan 2G could put 3,028 kg into a 546 km sun synchronous orbit, of 1,043 kg into a geosynchronous transfer orbit. The Titan 2 ICBM had been outfitted with a Delco Carousel- type guidance similar to that used in the Titan 3 while it was still deployed as a ballistic missile. That same guidance system, using the same equipment was used on the Titan 2 space booster, modified to handle telemetry. These guidance systems each had thousands of hours of operating time as a result of use on ICBM's and probably set an operating time record for such space launch hardware. The Titan 2 vehicles were not completely dismantled as was done with the Atlas E and Atlas F space boosters. A new rate gyro package was added to the second stage (after testing proved that using just the output from the HIG gyros would not work - and by that time the first vehicle had already been delivered to Vandenberg AFB. The top of the second stage was modified for the 3.05-m-diameter fairing, destruct, tracking, and telemetry equipment were added, but that was about all. The engines were test fired but not overhauled. Although 55 surplus ICBM's were available for use as space launchers, only the original 14 contracted in 1986-1987 were ever refurbished and launched, due to the inexplicably high cost of the minimal refurbishment. Launches: 13. Failures: 1. First Launch Date: 1988-09-05. Last Launch Date: 2003-10-18. LEO Payload: 3,175 kg (6,999 lb). to: 185 km Orbit. at: 28.60 degrees. Payload: 2,177 kg (4,799 lb). to a: 185 km polar orbit trajectory. Liftoff Thrust: 2,090.000 kN (469,850 lbf). Total Mass: 154,000 kg (339,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 31.40 m (103.00 ft). Launch Price $: 34.000 million. in: 1994 price dollars. Total Number Built: 131. Flyaway Unit Cost $: 26.000 million. in: 1987 unit dollars. Cost of design, development, launch complex development, and first 8 refurbished ICBM's in 1986 was $ 529 million. Next 6 cost $ 155 million = $ 26 million each. Refurbishment and launch of 14 surplus ICBM's in 1997 was $ 660 million = $ 47 million per launch. Version:Titan 2B. Intercontinental ballistic orbital launch vehicle. Space launch version of Titan 2 ICBM, obtained through minimal modification of ICBM (new wiring and avionics only, and use of existing ICBM re-entry vehicle shroud). Proposed in the late 1980's but never developed.
LEO Payload: 3,175 kg (6,999 lb). to: 185 km Orbit. at: 28.60 degrees. Liftoff Thrust: 2,090.000 kN (469,850 lbf). Total Mass: 154,000 kg (339,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 31.40 m (103.00 ft). Version:Titan 2L. Intercontinental ballistic orbital launch vehicle. Version of refurbished Titan 2 ICBM with two liquid propellant strap-on stages. Proposed in the late 1980's but never developed. No technical details available on the liquid boosters. LEO Payload: 8,165 kg (18,000 lb). to: 185 km Orbit. at: 28.60 degrees. Core Diameter: 3.05 m (10.00 ft). Total Length: 35.00 m (114.00 ft).
Version: Titan 2S. Intercontinental ballistic orbital launch vehicle. Version of refurbished Titan 2 ICBM with two to eight Castor 4A solid-propellant strap-on stages. Proposed in the late 1980's but never developed. Larger GEM-40 motors were also proposed. Would have required development of a new skirt for the first stage for attachment of the solid boosters. LEO Payload: 9,000 kg (19,800 lb). to: 185 km Orbit. at: 28.60 degrees. Total Mass: 247,000 kg (544,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 35.00 m (114.00 ft). Span: 9.60 m (31.40 ft).
Version: Titan 3A.
Titan with Transtage third stage. Core for Titan 3C.
Launches: 3. Failures: 1. First Launch Date: 1964-09-01. Last Launch Date: 1965-02-11. LEO Payload: 3,100 kg (6,800 lb). to: 185 km Orbit. Apogee: 4,000 km (2,400 mi). Associated Spacecraft: LCS, LES. Liftoff Thrust: 1,936.900 kN (435,432 lbf). Total Mass: 161,730 kg (356,550 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 42.00 m (137.00 ft). Flyaway Unit Cost $: 30.740 million. in: 1985 unit dollars.
Titan 3B.
Titan core with Agena upper stage. Found to be more cost effective and higher performance than using Transtage.
Launches: 29. Failures: 1. First Launch Date: 1966-07-29. Last Launch Date: 1970-10-23. LEO Payload: 3,300 kg (7,200 lb). to: 185 km Orbit. Apogee: 1,000 km (600 mi). Associated Spacecraft: KH-8, X-38. Liftoff Thrust: 1,936.900 kN (435,432 lbf). Total Mass: 156,540 kg (345,110 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 45.00 m (147.00 ft). Flyaway Unit Cost $: 24.940 million. in: 1985 unit dollars.
Titan 3BAS2.
Configuration of Titan 3B proposed by Martin in mid-1960's. Titan 3B for deep space missions with Centaur upper stage, Algol strapons for liftoff thrust augmentation. Never flown.
LEO Payload: 6,600 kg (14,500 lb). to: 185 km Orbit. Payload: 1,900 kg (4,100 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 3,024.000 kN (679,822 lbf). Total Mass: 225,650 kg (497,470 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 52.00 m (170.00 ft). Launch Price $: 14.000 million. in: 1965 price dollars.
Titan 33B.
Basic Titan 3A core, except guidance provided by the Agena upper stage. The Agena and its payload were completely enclosed in a new 3.05 m diameter shroud. 'Ascent Agena' seperated after orbital insertion and did not remain attached to the payload.
Launches: 3. Failures: 1. First Launch Date: 1971-03-21. Last Launch Date: 1973-08-21. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: Jumpseat. Liftoff Thrust: 2,300.000 kN (517,000 lbf). Total Mass: 185,000 kg (407,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 45.00 m (147.00 ft).
Titan 34B. Stretched Titan core, originally developed for Titan 3M MOL, with Agena D upper stage. Guidance provided by the Agena upper stage. The Agena and its payload were completely enclosed in a 3.05 m diameter shroud. 'Ascent Agena' seperated after orbital insertion and did not remain attached to the payload.
Launches: 11. First Launch Date: 1975-03-10. Last Launch Date: 1987-02-12. LEO Payload: 3,500 kg (7,700 lb). to: 185 km Orbit. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: Jumpseat, SDS. Liftoff Thrust: 1,997.700 kN (449,101 lbf). Total Mass: 188,520 kg (415,610 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 48.00 m (157.00 ft). Flyaway Unit Cost $: 25.810 million. in: 1985 unit dollars.
Titan 3C.
Titan 3A with five segment solid motors. Man-rated design originally developed for Dynasoar spaceplane.
Launches: 36. Failures: 5. Success Rate: 86.11%. First Launch Date: 1965-06-18. Last Launch Date: 1982-03-06. LEO Payload: 13,100 kg (28,800 lb). to: 185 km Orbit. Payload: 3,000 kg (6,600 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: Advanced Vela, ATS-6, Chalet, DODGE, DSCS II, DSP, ERS, Gemini, GGTS, IDCSP, IMEWS, LCS, LES, MOL, Oscar, OV1, OV2, OV4, OV5, Solrad, Tacsat, Dynasoar. Liftoff Thrust: 10,586.800 kN (2,380,007 lbf). Total Mass: 626,190 kg (1,380,510 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 42.00 m (137.00 ft). Launch Price $: 18.000 million. in: 1965 price dollars. Flyaway Unit Cost $: 66.700 million. in: 1985 unit dollars.
Titan 3C7.
Variant of Titan 3C with seven segment solid motors. Proposed by Martin for precise delivery of payloads beyond Titan 3C capacity into geosynch orbit. Never flown.
LEO Payload: 15,800 kg (34,800 lb). to: 185 km Orbit. Payload: 4,300 kg (9,400 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 12,821.000 kN (2,882,275 lbf). Total Mass: 818,380 kg (1,804,210 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 43.00 m (141.00 ft). Launch Price $: 19.000 million. in: 1965 price dollars.
Titan 3M.
Man-rated launch vehicle designed for MOL and other missions of the 1970's. Malfunction Detection System initiated abort procedures during launch. Also suited for launch of 'bulbous and lifting body payloads'. 7 segment UA1207 motors developed but not used until Titan 4 in 1990's. Cancelled with MOL program in 1969.
LEO Payload: 17,000 kg (37,000 lb). to: 185 km Orbit. Associated Spacecraft: MOL, Gemini Ferry. Liftoff Thrust: 12,821.000 kN (2,882,275 lbf). Total Mass: 836,560 kg (1,844,290 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 39.00 m (127.00 ft). Launch Price $: 22.000 million. in: 1965 price dollars.
Titan 23C. Status: Out of production. Department of Defence Designation: SLV-5C. Post-MOL standardisation of Titan 3C, with man-rated systems removed, upgraded first stage engines, digital avionics, blowdown solid rocket motor thrust vector control in place of pressure-regulated system, simplified Transtage attitude control system.
LEO Payload: 13,100 kg (28,800 lb). to: 185 km Orbit. Payload: 3,000 kg (6,600 lb). to a: Geosynchronous transfer trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 10,586.800 kN (2,380,007 lbf). Total Mass: 626,190 kg (1,380,510 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 42.00 m (137.00 ft).
Titan 3D.
Titan 3C without transtage.
Launches: 22. First Launch Date: 1971-06-15. Last Launch Date: 1982-11-17. LEO Payload: 12,300 kg (27,100 lb). to: 185 km Orbit. Apogee: 1,000 km (600 mi). Associated Spacecraft: KH-11, KH-9, S73-7 Cal Balloon, SESP, SSF. Liftoff Thrust: 10,586.800 kN (2,380,007 lbf). Total Mass: 612,990 kg (1,351,410 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 36.00 m (118.00 ft). Launch Price $: 14.000 million. in: 1965 price dollars. Flyaway Unit Cost $: 52.200 million. in: 1985 unit dollars.
Titan 3E.
Titan 3D with Centaur D-1T upper stage. Used by NASA for deep space missions in 1970's.
Launches: 7. Failures: 1. First Launch Date: 1974-02-11. Last Launch Date: 1977-09-05. LEO Payload: 15,400 kg (33,900 lb). to: 185 km Orbit. Payload: 3,700 kg (8,100 lb). to a: TransMars trajectory. Apogee: 400,000 km (240,000 mi). Associated Spacecraft: Helios, Sphinx, Viking, Voyager. Liftoff Thrust: 10,586.800 kN (2,380,007 lbf). Total Mass: 632,970 kg (1,395,450 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 48.00 m (157.00 ft). Launch Price $: 29.300 million. in: 1974 price dollars. Flyaway Unit Cost $: 72.500 million. in: 1985 unit dollars.
Titan 34D.
Stretched Titan core designed for use with 5 1/2 segment solid rocket motors. IUS (Interim/Inertial Upper Stage) solid upper stages, Transtage, or used without upper stages.
Launches: 7. Failures: 2. First Launch Date: 1983-06-20. Last Launch Date: 1988-11-06. LEO Payload: 14,515 kg (32,000 lb). to: 185 km Orbit. Payload: 5,000 kg (11,000 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: Chalet, DSCS II, DSCS III, DSP, KH-11, KH-9, SSF. Liftoff Thrust: 11,279.100 kN (2,535,643 lbf). Total Mass: 723,490 kg (1,595,020 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 50.00 m (164.00 ft). Launch Price $: 150.000 million. in: 1994 price dollars. Flyaway Unit Cost $: 126.550 million. in: 1985 unit dollars.
Titan 34D/IUS. Version of Titan 34D with IUS upper stages.
Launches: 1. First Launch Date: 1982-10-30. Last Launch Date: 1982-10-30. LEO Payload: 5,000 kg (11,000 lb). Payload: 5,000 kg (11,000 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 11,280.000 kN (2,535,840 lbf). Total Mass: 725,000 kg (1,598,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 52.40 m (171.90 ft).
Titan 34D/Transtage. Version of Titan 34D with Transtage upper stage.
Launches: 7. Failures: 1. First Launch Date: 1984-01-31. Last Launch Date: 1989-09-04. LEO Payload: 5,000 kg (11,000 lb). Payload: 5,000 kg (11,000 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 11,280.000 kN (2,535,840 lbf). Total Mass: 720,000 kg (1,580,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 50.00 m (164.00 ft).
Commercial Titan 3. Commercial version of Titan 34D military booster. It differed in having a lengthened second stage and a 4 m diameter payload shroud to handle shuttle-class or Ariane-type dual payloads. The design originated as the losing Martin submission for the USAF Medium Launch Vehicle competition (which was awarded to Douglas for their Delta 7000 series in January 1987). However commercial buyers had already booked flights on the booster in September 1986. Availability was however restricted due to renovaton of Cape Canaveral pad 40 from July 1990 to 1992. Launches: 4. Failures: 1. First Launch Date: 1990-01-01. Last Launch Date: 1992-09-25. LEO Payload: 14,515 kg (32,000 lb). Payload: 1,850 kg (4,070 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 40,000 km (24,000 mi). Associated Spacecraft: ECS/OTS, HS 393, Mars Observer. Liftoff Thrust: 12,450.000 kN (2,798,870 lbf). Total Mass: 680,000 kg (1,490,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 47.30 m (155.10 ft). Span: 9.20 m (30.10 ft). Launch Price $: 136.600 million. in: 1992 price dollars. Cost comments: Launch price for NASA Mars Observer. An additional $ 20 million was spent on payload-specific modifications.
Titan 4.
Developed to handle military payloads designed for launch on Shuttle from Vandenberg before the USAF pulled out of the Shuttle program after the Challenger disaster. Further stretch of core from Titan 34, 7-segment solid rocket motors (developed for MOL but not used until 25 years later). Enlarged Centaur G used as upper stage (variant of stage designed for Shuttle but prohibited for flight safety reasons after Challenger). Completely revised electronics. All the changes resulted in major increase in cost of launch vehicle and launch operations.
LEO Payload: 17,700 kg (39,000 lb). to: 185 km Orbit. Payload: 6,350 kg (13,990 lb). to a: Geosynchronous transfer trajectory. Associated Spacecraft: Advanced Orion, DSP Block 14, Improved CRYSTAL, KH-12, Lacrosse, Mercury ELINT, Milstar, NOSS, NOSS-2, NOSS-2 subsatellite, NOSS-Subsat, SDS-2, TIPS, Trumpet. Liftoff Thrust: 12,821.000 kN (2,882,275 lbf). Total Mass: 886,420 kg (1,954,220 lb). Core Diameter: 4.33 m (14.20 ft). Total Length: 51.00 m (167.00 ft). Launch Price $: 400.000 million. in: 1997 price dollars. Flyaway Unit Cost $: 89.360 million. in: 1985 unit dollars. Cost comments: Titan IV development contract was $ 15.8 billion, including 40 launch vehicles and 39 launches.
Version: Titan 401A/Centaur. Manufacturer's Designation: Titan 45E. Version of Titan 4 with Centaur T upper stage. Launches: 9. Failures: 1. First Launch Date: 1994-02-07. Last Launch Date: 1998-08-12. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 14,200.000 kN (3,192,200 lbf). Total Mass: 868,000 kg (1,913,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 63.10 m (207.00 ft). Titan 402A/IUS. Manufacturer's Designation: Titan 45D. Version of Titan 4 with IUS upper stages. Launches: 3. First Launch Date: 1989-06-14. Last Launch Date: 1994-12-22. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 14,200.000 kN (3,192,200 lbf). Total Mass: 910,000 kg (2,000,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 54.00 m (177.00 ft). Titan 403A.
Version of Titan 4 with no upper stage, configured for launch of lower-mass, higher-orbit Lacrosse, SDS and NOSS-2 payloads from Vandenberg.
Launches: 5. Failures: 1. First Launch Date: 1991-03-08. Last Launch Date: 1997-10-24. LEO Payload: 17,700 kg (39,000 lb). Apogee: 1,000 km (600 mi). Liftoff Thrust: 14,200.000 kN (3,192,200 lbf). Total Mass: 906,000 kg (1,997,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 54.00 m (177.00 ft).
Titan 404A. Manufacturer's Designation: Titan 45J. Version of Titan 4 with no upper stage, configured for launch of heavy-weight, low altitude KH-12 and Improved CRYSTAL payloads from Vandenberg.
Launches: 3. First Launch Date: 1992-11-28. Last Launch Date: 1996-12-20. LEO Payload: 17,700 kg (39,000 lb). Apogee: 1,000 km (600 mi). Liftoff Thrust: 14,200.000 kN (3,192,200 lbf). Total Mass: 906,000 kg (1,997,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 54.00 m (177.00 ft).
Titan 405A. Manufacturer's Designation: Titan 45H. Version of Titan 4 with no upper stage, configured for launch of lower-mass, higher-orbit SDS and NOSS-2 payloads from Cape Canaveral.
Launches: 2. First Launch Date: 1990-06-08. Last Launch Date: 1996-07-03. LEO Payload: 17,700 kg (39,000 lb). Apogee: 1,000 km (600 mi). Liftoff Thrust: 14,200.000 kN (3,192,200 lbf). Total Mass: 906,000 kg (1,997,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 54.00 m (177.00 ft).
Titan 4B.
Titan 4 with Upgraded Solid Rocket Motors replacing UA1207. Developed to improve performance for certain missions, and reduce number of field joints in motor after Challenger and Titan 34D explosions involving segmented motors.
LEO Payload: 21,680 kg (47,790 lb). to: 150 km Orbit. at: 28.60 degrees. Payload: 5,760 kg (12,690 lb). to a: Geosynchronous orbit trajectory. Associated Spacecraft: Advanced Orion, Cassini, DSP Block 14, Huygens, Improved CRYSTAL, Lacrosse, Milstar. Liftoff Thrust: 13,693.800 kN (3,078,489 lbf). Total Mass: 943,050 kg (2,079,060 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 44.00 m (144.00 ft). Development Cost $: 15,800.000 million. in: 1996 average dollars. Launch Price $: 432.000 million. in: 1999 price dollars. Flyaway Unit Cost $: 84.300 million. in: 1985 unit dollars. Cost comments: There is little reported difference between the launch cost for the Centaur and IUS upper stage versions.
Version: Titan 401B/Centaur. Manufacturer's Designation: Titan 45E. Version of Titan 4B with Centaur T upper stage. Launches: 7. Failures: 1. First Launch Date: 1997-10-15. Last Launch Date: 2003-09-09. LEO Payload: 9,000 kg (19,800 lb). Payload: 9,000 kg (19,800 lb). to a: geosynchronous transfer orbit trajectory. Apogee: 400,000 km (240,000 mi). Liftoff Thrust: 15,000.000 kN (3,372,000 lbf). Total Mass: 939,000 kg (2,070,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 62.20 m (204.00 ft). Titan 402B/IUS. Manufacturer's Designation: Titan 45D. Version of Titan 4B with IUS upper stage. Launches: 5. Failures: 1. First Launch Date: 1997-02-23. Last Launch Date: 2004-02-14. Apogee: 40,000 km (24,000 mi). Liftoff Thrust: 15,000.000 kN (3,372,000 lbf). Total Mass: 925,000 kg (2,039,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 54.00 m (177.00 ft). Titan 403B. Manufacturer's Designation: Titan 45F. Version of Titan 4B with no upper stage, configured for launch from Vandenberg. Launches: 2. First Launch Date: 2000-08-17. Last Launch Date: 2005-04-30. LEO Payload: 21,680 kg (47,790 lb). Apogee: 1,000 km (600 mi). Liftoff Thrust: 15,000.000 kN (3,372,000 lbf). Total Mass: 910,000 kg (2,000,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 54.00 m (177.00 ft). Titan 404B.
Version of Titan 4B with no upper stage, configured for launch from Vandenberg.
Launches: 3. First Launch Date: 1999-05-22. Last Launch Date: 2005-10-19. LEO Payload: 21,680 kg (47,790 lb). Apogee: 1,000 km (600 mi). Liftoff Thrust: 15,000.000 kN (3,372,000 lbf). Total Mass: 910,000 kg (2,000,000 lb). Core Diameter: 3.05 m (10.00 ft). Total Length: 54.00 m (177.00 ft).
Titan 3L2.
Variant of Titan with 15 foot Large Diameter Core, 2 x 7 segment strap-ons. Man-rated, optimized for delivery of heavy payloads into LEO. Never developed.
LEO Payload: 35,000 kg (77,000 lb). to: 185 km Orbit. Payload: 12,000 kg (26,000 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 12,821.000 kN (2,882,275 lbf). Total Mass: 1,096,920 kg (2,418,290 lb). Core Diameter: 4.57 m (14.99 ft). Total Length: 63.00 m (206.00 ft). Launch Price $: 33.000 million. in: 1965 price dollars.
Titan 3L4.
Variant of Titan with 15 foot Large Diameter Core, 4 x 7 segment strap-ons. Man rated, optimized for delivery of 40,000 pound manned payloads into 250 nm / 50 deg space station orbit.
LEO Payload: 45,000 kg (99,000 lb). to: 185 km Orbit. Payload: 16,000 kg (35,000 lb). to a: Geosynchronous transfer trajectory. Liftoff Thrust: 25,642.100 kN (5,764,573 lbf). Total Mass: 1,747,580 kg (3,852,750 lb). Core Diameter: 4.57 m (14.99 ft). Total Length: 63.00 m (206.00 ft). Launch Price $: 38.000 million. in: 1965 price dollars.
Titan 5. Status: Study 1988. Proposed Titan upgrade with cryogenic core as replacement for NLS.
Liftoff Thrust: 16,533.600 kN (3,716,901 lbf). Total Mass: 1,138,660 kg (2,510,310 lb). Core Diameter: 6.00 m (19.60 ft). Total Length: 72.00 m (236.00 ft). Flyaway Unit Cost $: 48.720 million. in: 1985 unit dollars.
Titan Chronology 1955 May 2 - Titan 1 begun. USAF approved Western Development Division proposals to inaugurate a second ICBM airframe, which became the Titan ICBM (SM-68). 1957 December - Titan plus Vanguard proposed to place instrument package into lunar orbit The Martin Company proposed to the Department of Defense (DOD) that a stage of the Titan intercontinental ballistic missile be combined with the Vanguard rocket to provide a launch vehicle capable of placing an instrument package into lunar orbit and, ultimately, on the lunar surface. 1958 June 16 - Dynasoar Phase I contracts announced. Spacecraft: Dynasoar. Phase I contracts for the Dyna-Soar boost-glide orbital spacecraft are awarded by the USAF to two teams of contractors: one headed by Boeing (Aerojet, General Electric, Ramo-Wooldridge, North American, and Chance Vought), and one headed by Martin (Bell, American Machine & Foundry, Bendix, Goodyear, and Minneapolis-Honeywell). Under the $ 9 million one-year contracts each team was to refine its design, leading to a competitive down-select. 1958 July - Advanced Titan considered. USAF reviews improvements (inertial guidance, storable fuel, 1 x 9 basing, both stages constant 3.05 m diameter, in silo launch) to the Titan I. 1959 January 19 - Silo-launched Titan approved. Major General Schriever approves conversion of future Titan facilities from silo-lift to in-silo launch. 1959 February 6 - 21:22 GMT - Cape Canaveral LC15. LV Model: Titan 1 . Titan I A-3 Agency: USAF. Apogee: 1,000 km (600 mi). First test launch of USAF Titan ICBM (A-3) from Cape Canaveral. Dummy second stage (500 km range). 1959 February 25 - 19:45 GMT - Cape Canaveral LC15. LV Model: Titan 1 . Titan I A-5 Test mission Agency: USAF. Apogee: 1,000 km (600 mi). 1959 April 3 - 17:11 GMT - Cape Canaveral LC15. LV Model: Titan 1 . Titan I A-4 Test mission Agency: USAF. Apogee: 1,000 km (600 mi). 1959 May 4 - 18:30 GMT - Cape Canaveral LC15. LV Model: Titan 1 . Titan I A-6 Agency: USAF. Apogee: 1,000 km (600 mi). Successful dummy second stage separation. 1959 May 15 - Titan 1 B-4 FAILURE: Exploded during static testing. Titan 1 B-4 1959 June 1 - Dyna-Soar contractors Boeing and Martin selected. Spacecraft: Dynasoar. The Dyna-Soar source selection board completed its evaluation of the proposals of the Boeing Airplane Company and the Martin Company. The board recommended the development of the Boeing glider but also favored the employment of the orbtal Titan C booster offered by Martin. 1959 July 3 - Titan 1 B-3 FAILURE: Exploded during static testing. Titan 1 B-3 1959 August 14 - 16:00 GMT - Cape Canaveral LC19. LV Model: Titan 1 . Titan I B-5 FAILURE: Failure. Test mission Agency: USAF. Apogee: 0 km ( mi). 1959 September 16-18 - Plans for advanced launch vehicles The ARPA-NASA Booster Evaluation Committee appointed by Herbert F. York, DOD Director of Defense Research and Engineering, April 15, 1959, convened to review plans for advanced launch vehicles. A comparison of the Saturn (C-1) and the Titan-C boosters showed that the Saturn, with its substantially greater payload capacity, would be ready at least one year sooner than the Titan-C. In addition, the cost estimates on the Titan-C proved to be unrealistic. On the basis of the Advanced Research Projects Agency presentation, York agreed to continue the Saturn program but, following the meeting, began negotiations with NASA Administrator T. Keith Glennan to transfer the Army Ballistic Missile Agency (and, therefore, Saturn ) to NASA. 1959 November 9 - Contractor selection for Dynasoar and Titan I announced. Spacecraft: Dynasoar. Boeing and Martin selected by USAF to develop Dynasoar and Titan I launch vehicle. The compromise project reformulation a week earlier led to this announcement by the Secretary of the Air Force. Boeing was the winner of the DynaSoar design competition on 9 November 1959 - but for the glider and total system only. Martin was selected as an associate contractor for booster development. Dynasoar received the designation WS-620A on 17 November 1959 1959 December 12 - 17:11 GMT - Cape Canaveral LC16. LV Model: Titan 1 . Titan I C-3 FAILURE: Exploded just above pad. RVX-3 Re-entry Vehicle test Agency: USAF. Apogee: 0 km ( mi). First Titan ICBM launching testing second stage was unsuccessful at AMR. 1960 - Configuration of Titan 3B proposed by Martin in mid-1960's. Titan 3B for deep space missions with Centaur upper stage, Algol strapons for liftoff thrust augmentation. Never flown. 1960 February 2 - 18:08 GMT - Cape Canaveral LC19. LV Model: Titan 1 . Titan I B-7A Test mission Agency: USAF. Apogee: 1,000 km (600 mi). 1960 February 5 - 21:46 GMT - Cape Canaveral LC16. LV Model: Titan 1 . Titan I C-4 FAILURE: Failure. RVX-3 Re-entry Vehicle test Agency: USAF. Apogee: 0 km ( mi). 1960 February 24 - Cape Canaveral LC15. LV Model: Titan 1 . Titan I G-4 RVX-4 test Agency: USAF. Apogee: 1,000 km (600 mi). 1960 March 8 - 18:00 GMT - Cape Canaveral LC16. LV Model: Titan 1 . Titan I C-1 FAILURE: Failure. RVX-3 Re-entry Vehicle test Agency: USAF. Apogee: 0 km ( mi). 1960 March 22 - Cape Canaveral LC15. LV Model: Titan 1 . Titan I G-5 RVX-4 test Agency: USAF. Apogee: 1,000 km (600 mi). USAF Titan fired 5,000 statute miles / 8000 km and data capsule recovered. 1960 April 8 - Cape Canaveral LC16. LV Model: Titan 1 . Titan I C-5 RVX-3 Re-entry Vehicle test Agency: USAF. Apogee: 1,000 km (600 mi). 1960 April 21 - 20:55 GMT - Cape Canaveral LC15. LV Model: Titan 1 . Titan I G-6 RVX-4 test Agency: USAF. Apogee: 1,000 km (600 mi). 1960 April 28 - 20:18 GMT - Cape Canaveral LC16. LV Model: Titan 1 . Titan I C-6 RVX-3 Re-entry Vehicle test Agency: USAF. Apogee: 1,000 km (600 mi). 1960 May 13 - 21:25 GMT - Cape Canaveral LC15. LV Model: Titan 1 . Titan I G-7 RVX-4 test Agency: USAF. Apogee: 1,000 km (600 mi). 1960 May 27 - 17:20 GMT - Cape Canaveral LC16. LV Model: Titan 1 . Titan I G-9 RVX-4 test Agency: USAF. Apogee: 1,000 km (600 mi). 1960 June - Martin awarded a contract to develop the Titan 2 ICBM. 1960 June 8 - Martin to develop the Dyna-Soar booster airframe. Spacecraft: Dynasoar. The Air Force gave the Martin Company responsibility for the development of the Dyna-Soar booster airframe. 1960 June 24 - |
