Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

---

Titan 4B

---

Titan 4U Credit: © Mark Wade

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.