American nuclear-powered orbital launch vehicle. DARPA project. Nuclear fission engine using pebble bed reactor with spherical fuel elements.
Flyaway Unit Cost $: 166.660 million.
Stage Data - Timberwind
- 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 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 1992.
Status: Cancelled 1992.
Gross mass: 884,478 kg (1,949,940 lb).
Height: 36.00 m (118.00 ft).
Diameter: 8.70 m (28.50 ft).
Thrust: 13,693.80 kN (3,078,489 lbf).
More... - Chronology...
Associated Countries
Associated Engines
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Timberwind 250 DoE nuclear/lh2 rocket engine. 2451.6 kN. Development ended 1992. Isp=1000s. Used on Timberwind launch vehicle. More...
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USRM Hercules solid rocket engine. 7560.5 kN. Isp=286s.Strap-on booster for Titan 4B. First flight 1997. More...
See also
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Timberwind DARPA project. Nuclear fission engine using pebble bed reactor with spherical fuel elements. More...
Associated Manufacturers and Agencies
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DARPA American agency overseeing development of rockets and spacecraft. Defense Advanced Research Projects Agency (formerly ARPA), USA. More...
Bibliography
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Asker, James R, "Particle Bed Reactor Central to SDI Nuclear Rocket Project", Aviation Week and Space Technology, 1991-04-08, page 18.
Associated Stages
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Timberwind 250 Nuclear/LH2 propellant rocket stage. Loaded/empty mass 170,000/45,000 kg. Thrust 2,450.00 kN. Vacuum specific impulse 1000 seconds. More...
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Titan USRM Solid propellant rocket stage. Loaded/empty mass 357,239/52,040 kg. Thrust 7,560.68 kN. Vacuum specific impulse 286 seconds. More...
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