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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. 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.
Stage Data - Timberwind Centaur - Stage Number: 1. 1 x Stage: Atlas IIIA. Gross Mass: 195,628 kg (431,285 lb). Empty Mass: 13,725 kg (30,258 lb). Thrust (vac): 4,148.722 kN (932,670 lbf). Isp: 337 sec. Burn time: 132 sec. Isp(sl): 311 sec. Diameter: 3.05 m (10.00 ft). Span: 3.05 m (10.00 ft). Length: 29.00 m (95.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-180. Status: Out of production. Atlas booster and sustainer engine arrangement replaced by Glushko engines developed for Zenit. Not capable of single stage to single stage to orbit capability (an Internet spaceflight urban myth). The single-stage Atlas IIIA booster uses a high-performance RD-180 propulsion system produced by a U.S./Russian joint venture (RD AMROSS) comprised of Pratt & Whitney (U.S.) and NPO Energomash (Russia). The RD-180 burns liquid oxygen and RP-1 propellant and develops a lift-off (sea-level) thrust of 2.6 MN. The RD-180 throttles to various levels during atmospheric ascent to effectively manage the air-loads experienced by the vehicle enabling minimum Atlas vehicle and launch site infrastructure changes. Additionally, throttling results in satellite experienced flight environments that are nearly identical to Atlas IIAS.
- Stage Number: 2. 1 x Stage: Timberwind 45. Gross Mass: 28,000 kg (61,000 lb). Empty Mass: 7,500 kg (16,500 lb). Thrust (vac): 441.000 kN (99,140 lbf). Isp: 1,000 sec. Burn time: 449 sec. Isp(sl): 890 sec. Diameter: 4.25 m (13.94 ft). Span: 4.25 m (13.94 ft). Length: 23.87 m (78.31 ft). Propellants: Nuclear/LH2. No Engines: 1. Engine: Timberwind 45. 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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