Encyclopedia Astronautica
Titan 3C7



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Titan 3C7
Credit: © Mark Wade
American orbital launch vehicle. 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 a 185 km orbit. Payload: 4,300 kg (9,400 lb) to a GTO. Launch Price $: 19.000 million in 1965 dollars.

Stage Data - Titan 3C7

  • Stage 0. 2 x Titan UA1207. Gross Mass: 319,330 kg (704,000 lb). Empty Mass: 51,230 kg (112,940 lb). Thrust (vac): 7,116.999 kN (1,599,965 lbf). Isp: 272 sec. Burn time: 120 sec. Isp(sl): 245 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 34.14 m (112.00 ft). Propellants: Solid. No Engines: 1. Engine: UA1207. Status: In Production.
  • Stage 1. 1 x Titan 3A-1. Gross Mass: 116,573 kg (256,999 lb). Empty Mass: 5,443 kg (11,999 lb). Thrust (vac): 2,339.760 kN (525,999 lbf). Isp: 302 sec. Burn time: 147 sec. Isp(sl): 250 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 22.28 m (73.09 ft). Propellants: N2O4/Aerozine-50. No Engines: 2. Engine: LR-87-11. Status: In Production.
  • Stage 2. 1 x Titan 3A-2. Gross Mass: 29,188 kg (64,348 lb). Empty Mass: 2,653 kg (5,848 lb). Thrust (vac): 453.714 kN (101,999 lbf). Isp: 316 sec. Burn time: 205 sec. Isp(sl): 145 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 7.90 m (25.90 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: LR-91-11. Status: In Production.
  • Stage 3. 1 x Titan Transtage Stretch. Gross Mass: 15,000 kg (33,000 lb). Empty Mass: 2,200 kg (4,800 lb). Thrust (vac): 71.166 kN (15,999 lbf). Isp: 311 sec. Burn time: 520 sec. Isp(sl): 0.0000 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 5.30 m (17.30 ft). Propellants: N2O4/Aerozine-50. No Engines: 2. Engine: AJ10-138. Status: Study 1965. Comments: 20% stretch of Transtage to handle geosynch insertion of larger payloads launched by Titan 3C7. Masses estimated.

Status: Study 1965.
Gross mass: 818,380 kg (1,804,210 lb).
Payload: 15,800 kg (34,800 lb).
Height: 43.00 m (141.00 ft).
Diameter: 3.05 m (10.00 ft).
Thrust: 12,821.00 kN (2,882,275 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • AJ10-138 Aerojet N2O4/Aerozine-50 rocket engine. 35.6 kN. Out of production. Originally developed for Vanguard and Able. Two used, thrust uprated from 3540 kgf to 3628 kgf, with higher specific impulse, in Transtage. Isp=311s. Flown 1964-1980. More...
  • LR87-11 Aerojet N2O4/Aerozine-50 rocket engine. 1218.8 kN. Out of production. Isp=302s. Powered Titan 3 and 4 first stages. Replaced the -9 model, first flown 1968. First flight 1964. More...
  • LR91-11 Aerojet N2O4/Aerozine-50 rocket engine. 467 kN. Out of production. Isp=316s. Second stage engine for Titan 3 and 4. First flight 1968. More...
  • UA1207 CSD solid rocket engine. 7116.9 kN. Isp=272s. First flight 1989. More...

See also
  • Titan 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. More...

Associated Manufacturers and Agencies
  • Martin American manufacturer of rockets, spacecraft, and rocket engines. Martin Marietta Astronautics Group (1956), Denver, CO, USA. More...

Associated Stages
  • Titan 3A-1 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 116,573/5,443 kg. Thrust 2,339.76 kN. Vacuum specific impulse 302 seconds. More...
  • Titan 3A-2 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 29,188/2,653 kg. Thrust 453.71 kN. Vacuum specific impulse 316 seconds. More...
  • Titan Transtage Stretch N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 15,000/2,200 kg. Thrust 71.17 kN. Vacuum specific impulse 311 seconds. 20% stretch of Transtage to handle geosynch insertion of larger payloads launched by Titan 3C7. Masses estimated. More...
  • Titan UA1207 Solid propellant rocket stage. Loaded/empty mass 319,330/51,230 kg. Thrust 7,117.00 kN. Vacuum specific impulse 272 seconds. More...

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