Encyclopedia Astronautica
Titan 3L2



titan3l2.gif
Titan 3lL2
Credit: © Mark Wade
American orbital launch vehicle. 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 a 185 km orbit. Payload: 12,000 kg (26,000 lb) to a GTO. Launch Price $: 33.000 million in 1965 dollars.

Stage Data - Titan 3L2

  • 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 LDC-1. Gross Mass: 350,000 kg (770,000 lb). Empty Mass: 20,000 kg (44,000 lb). Thrust (vac): 4,344.463 kN (976,674 lbf). Isp: 296 sec. Burn time: 210 sec. Isp(sl): 258 sec. Diameter: 4.57 m (14.99 ft). Span: 4.57 m (14.99 ft). Length: 29.90 m (98.00 ft). Propellants: N2O4/Aerozine-50. No Engines: 4. Engine: LR-87-7. Status: Study 1965. Comments: 15 foot diameter core Titan proposed in 1960's for space station logistics. Masses estimated.
  • Stage 2. 1 x Titan LDC-2. Gross Mass: 50,000 kg (110,000 lb). Empty Mass: 3,000 kg (6,600 lb). Thrust (vac): 444.819 kN (99,999 lbf). Isp: 316 sec. Burn time: 320 sec. Isp(sl): 160 sec. Diameter: 4.57 m (14.99 ft). Span: 4.57 m (14.99 ft). Length: 13.40 m (43.90 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: LR-91-7. Status: Study 1965. Comments: 15 foot diameter core Titan proposed in 1960's for space station logistics. Masses estimated.
  • Stage 3. 1 x Centaur D/E. Gross Mass: 16,258 kg (35,842 lb). Empty Mass: 2,631 kg (5,800 lb). Thrust (vac): 131.222 kN (29,500 lbf). Isp: 444 sec. Burn time: 470 sec. Isp(sl): 0.0000 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.60 m (31.40 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-3. Status: Out of Production.

Status: Study 1965.
Gross mass: 1,096,920 kg (2,418,290 lb).
Payload: 35,000 kg (77,000 lb).
Height: 63.00 m (206.00 ft).
Diameter: 4.57 m (14.99 ft).
Thrust: 12,821.00 kN (2,882,275 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • LR87-7 Aerojet N2O4/Aerozine-50 rocket engine. 1086.1 kN. Study 1961. Version of LR-87-5 used on Gemini Titan 2 launch vehicle. Isp=296s. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962. More...
  • LR91-7 Aerojet N2O4/Aerozine-50 rocket engine. 444.8 kN. Study 1961. Version used on Stage 2 of Gemini Titan 2 Launch Vehicle. Isp=316s. Proposed for unflown Titan 3L2, Titan 3L4 boosters. First flight 1962. More...
  • RL-10A-3 Pratt and Whitney lox/lh2 rocket engine. 65.6 kN. Study 1968. Isp=444s. First flight 1967. 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
  • Centaur D/E Lox/LH2 propellant rocket stage. Loaded/empty mass 16,258/2,631 kg. Thrust 131.22 kN. Vacuum specific impulse 444 seconds. 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...
  • Titan LDC-2 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 50,000/3,000 kg. Thrust 444.82 kN. Vacuum specific impulse 316 seconds. 15 foot diameter core Titan proposed in 1960's for space station logistics. Masses estimated. More...
  • Titan LDC-1 N2O4/Aerozine-50 propellant rocket stage. Loaded/empty mass 350,000/20,000 kg. Thrust 4,344.46 kN. Vacuum specific impulse 296 seconds. 15 foot diameter core Titan proposed in 1960's for space station logistics. Masses estimated. More...

Home - Browse - Contact
© / Conditions for Use