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Nuclear orbital launch vehicle. Year: 1992. Family: Nerva. Country: USA. Status: Development ended 1992. DARPA project. Nuclear fission engine using 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.
Stage Data - Timberwind - Stage Number: 0. 2 x Stage: 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.
- Stage Number: 1. 1 x Stage: Timberwind 250. Gross Mass: 170,000 kg (370,000 lb). Empty Mass: 45,000 kg (99,000 lb). Thrust (vac): 2,450.000 kN (550,780 lbf). Isp: 1,000 sec. Burn time: 493 sec. Isp(sl): 780 sec. Diameter: 8.70 m (28.50 ft). Span: 8.70 m (28.50 ft). Length: 30.00 m (98.00 ft). Propellants: Nuclear/LH2. No Engines: 1. Engine: Timberwind 250. Status: Development ended 1992.
Bibliography and Further Reading - Asker, James R, Aviation Week and Space Technology, "Particle Bed Reactor Central to SDI Nuclear Rocket Project", 1991-04-08, page 18.
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