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Titan 4B
Part of Titan Family
Titan 4U
Titan 4U
Credit: © Mark Wade
American orbital launch vehicle. 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.

Status: Out of production. Payload: 21,680 kg (47,790 lb). Thrust: 13,693.80 kN (3,078,489 lbf). Gross mass: 943,050 kg (2,079,060 lb). Height: 44.00 m (144.00 ft). Diameter: 3.05 m (10.00 ft). Apogee: 150 km (90 mi).

LEO Payload: 21,680 kg (47,790 lb) to a 150 km orbit at 28.60 degrees. Payload: 5,760 kg (12,690 lb) to a GEO. Development Cost $: 15,800.000 million. Launch Price $: 432.000 million in 1985 dollars. Flyaway Unit Cost 1985$: 84.300 million.

Stage Data - Titan 4B

  • Stage 0. 2 x Titan USRM. Gross Mass: 357,239 kg (787,577 lb). Empty Mass: 52,040 kg (114,720 lb). Thrust (vac): 7,560.681 kN (1,699,709 lbf). Isp: 286 sec. Burn time: 140 sec. Isp(sl): 259 sec. Diameter: 3.20 m (10.40 ft). Span: 3.20 m (10.40 ft). Length: 33.54 m (110.03 ft). Propellants: Solid. No Engines: 1. Engine: USRM. Other designations: Upgraded Solid Rocket Motor. Status: In production.
  • Stage 1. 1 x Titan 4-1. Gross Mass: 163,000 kg (359,000 lb). Empty Mass: 8,000 kg (17,600 lb). Thrust (vac): 2,428.312 kN (545,906 lbf). Isp: 302 sec. Burn time: 164 sec. Isp(sl): 250 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 26.37 m (86.51 ft). Propellants: N2O4/Aerozine-50. No Engines: 2. Engine: LR-87-11. Status: In Production.
  • Stage 2. 1 x Titan 4-2. Gross Mass: 39,500 kg (87,000 lb). Empty Mass: 4,500 kg (9,900 lb). Thrust (vac): 459.510 kN (103,302 lbf). Isp: 316 sec. Burn time: 223 sec. Isp(sl): 160 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 9.94 m (32.61 ft). Propellants: N2O4/Aerozine-50. No Engines: 1. Engine: LR-91-11. Status: In Production.
  • Stage 3. 1 x IUS-1. Gross Mass: 10,841 kg (23,900 lb). Empty Mass: 1,134 kg (2,500 lb). Thrust (vac): 181.501 kN (40,803 lbf). Isp: 296 sec. Burn time: 152 sec. Isp(sl): 220 sec. Diameter: 2.34 m (7.67 ft). Span: 2.34 m (7.67 ft). Length: 3.52 m (11.54 ft). Propellants: Solid. No Engines: 1. Engine: SRM-1. Other designations: Orbus 21D. Status: In Production.
  • Stage 3. 1 x Centaur G. Gross Mass: 23,880 kg (52,640 lb). Empty Mass: 2,775 kg (6,117 lb). Thrust (vac): 146.800 kN (33,002 lbf). Isp: 444 sec. Burn time: 625 sec. Diameter: 4.33 m (14.20 ft). Span: 4.33 m (14.20 ft). Length: 9.00 m (29.50 ft). Propellants: Lox/LH2. No Engines: 2. Engine: RL-10A-3A. Status: In Production. Comments: Centaur for Titan 4.
  • Stage 4. 1 x IUS-2. Gross Mass: 3,919 kg (8,639 lb). Empty Mass: 1,170 kg (2,570 lb). Thrust (vac): 78.413 kN (17,628 lbf). Isp: 304 sec. Burn time: 103 sec. Isp(sl): 200 sec. Diameter: 1.61 m (5.28 ft). Span: 1.61 m (5.28 ft). Length: 2.08 m (6.82 ft). Propellants: Solid. No Engines: 1. Engine: SRM-2. Other designations: TOS. Status: In Production.



Family: orbital launch vehicle. Country: USA. Engines: LR87-11, LR91-11. Spacecraft: DSP, Lacrosse (satellite), Improved Crystal, Milstar, Advanced Orion, Cassini, Huygens. Stages: USRM. Agency: Martin.

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