Nuclear-powered orbital launch vehicle. Country: USA. Status: Cancelled 1992. DARPA project. Nuclear fission engine using pebble bed reactor with spherical fuel elements.
Manufacturer: DARPA. Liftoff Thrust: 13,693.800 kN (3,078,489 lbf). Total Mass: 884,478 kg (1,949,940 lb). Core Diameter: 8.70 m (28.50 ft). Total Length: 36.00 m (118.00 ft). Flyaway Unit Cost $: 166.660 million. in: 1985 unit dollars.
- Stage0: 2 x Titan USRM. Gross Mass: 357,239 kg (787,577 lb). Empty Mass: 52,040 kg (114,720 lb). Motor: 1 x USRM. Thrust (vac): 7,560.681 kN (1,699,709 lbf). Isp: 286 sec. Burn time: 140 sec. Length: 33.54 m (110.03 ft). Diameter: 3.20 m (10.40 ft). Propellants: Solid.
- Stage1: 1 x Timberwind 250. Gross Mass: 170,000 kg (370,000 lb). Empty Mass: 45,000 kg (99,000 lb). Motor: 1 x Timberwind 250. Thrust (vac): 2,450.000 kN (550,780 lbf). Isp: 1,000 sec. Burn time: 493 sec. Length: 30.00 m (98.00 ft). Diameter: 8.70 m (28.50 ft). Propellants: Nuclear/LH2.
Version: Timberwind Centaur. Status: Development ended 1992.
LEO Payload: 12,272 kg (27,055 lb). to: 80 km Orbit. Payload: 6,363 kg (14,028 lb). to a: 19,000 km orbital trajectory. Liftoff Thrust: 3,828.630 kN (860,710 lbf). Total Mass: 223,628 kg (493,015 lb). Core Diameter: 4.25 m (13.94 ft). Total Length: 29.00 m (95.00 ft). Flyaway Unit Cost $: 100.000 million. in: 1985 unit dollars.
- Stage1: 1 x Atlas IIIA. Gross Mass: 195,628 kg (431,285 lb). Empty Mass: 13,725 kg (30,258 lb). Motor: 1 x RD-180. Thrust (vac): 4,148.722 kN (932,670 lbf). Isp: 337 sec. Burn time: 132 sec. Length: 29.00 m (95.00 ft). Diameter: 3.05 m (10.00 ft). Propellants: Lox/Kerosene.
- Stage2: 1 x Timberwind 45. Gross Mass: 28,000 kg (61,000 lb). Empty Mass: 7,500 kg (16,500 lb). Motor: 1 x Timberwind 45. Thrust (vac): 441.000 kN (99,140 lbf). Isp: 1,000 sec. Burn time: 449 sec. Length: 23.87 m (78.31 ft). Diameter: 4.25 m (13.94 ft). Propellants: Nuclear/LH2.
Version: Timberwind Titan. Status: Development ended 1992.
LEO Payload: 63,636 kg (140,293 lb). to: 155 km Orbit. Liftoff Thrust: 13,693.800 kN (3,078,489 lbf). Total Mass: 900,840 kg (1,986,010 lb). Core Diameter: 6.10 m (20.00 ft). Total Length: 55.00 m (180.00 ft). Flyaway Unit Cost $: 166.660 million. in: 1985 unit dollars.
- Stage0: 2 x Titan USRM. Gross Mass: 357,239 kg (787,577 lb). Empty Mass: 52,040 kg (114,720 lb). Motor: 1 x USRM. Thrust (vac): 7,560.681 kN (1,699,709 lbf). Isp: 286 sec. Burn time: 140 sec. Length: 33.54 m (110.03 ft). Diameter: 3.20 m (10.40 ft). Propellants: Solid.
- Stage1: 1 x Timberwind 75. Gross Mass: 110,000 kg (240,000 lb). Empty Mass: 28,500 kg (62,800 lb). Motor: 3 x Timberwind 75. Thrust (vac): 2,206.000 kN (495,928 lbf). Isp: 1,000 sec. Burn time: 357 sec. Length: 45.50 m (149.20 ft). Diameter: 6.10 m (20.00 ft). Propellants: Nuclear/LH2.
Bibliography:- Asker, James R, Aviation Week and Space Technology, "Particle Bed Reactor Central to SDI Nuclear Rocket Project", 1991-04-08, page 18.