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Nuclear orbital launch vehicle. Year: 1963. Family: Nerva. Country: USA. Status: Study 1963. Nuclear, recoverable upper stage boosted above atmosphere by minimum chemical stage. Improved Specific Impulse chemical stage used many engines feeding into single large nozzle. Douglas/Bono design approach to same concept as Convair/Ehricke Helios. Manufacturer: Douglas. LEO Payload: 454,500 kg (1,002,000 lb). to: 325 km Orbit. Liftoff Thrust: 39,955.800 kN (8,982,421 lbf). Total Mass: 2,948,400 kg (6,500,100 lb). Core Diameter: 24.40 m (80.00 ft). Total Length: 60.00 m (196.00 ft). Flyaway Unit Cost $: 105.700 million. in: 1985 unit dollars.
Stage Data - DAC Helios ISI - Stage Number: 1. 1 x Stage: DAC Helios ISI-1. Gross Mass: 1,333,000 kg (2,938,000 lb). Empty Mass: 120,000 kg (260,000 lb). Thrust (vac): 49,807.000 kN (11,197,059 lbf). Isp: 455 sec. Burn time: 107 sec. Isp(sl): 365 sec. Diameter: 24.40 m (80.00 ft). Span: 29.00 m (95.00 ft). Length: 22.90 m (75.10 ft). Propellants: Lox/LH2. No Engines: 4. Engine: Chamber/single nozzle. Status: Study 1963.
- Stage Number: 2. 1 x Stage: DAC Helios ISI-2. Gross Mass: 1,070,000 kg (2,350,000 lb). Empty Mass: 214,000 kg (471,000 lb). Thrust (vac): 17,926.000 kN (4,029,925 lbf). Isp: 850 sec. Burn time: 392 sec. Diameter: 21.30 m (69.80 ft). Span: 38.10 m (124.90 ft). Length: 27.40 m (89.80 ft). Propellants: Nuclear/LH2. No Engines: 4. Engine: NERVA 1mlbf. Status: Study 1963.
Bibliography and Further Reading - Bono, Philip, Advanced in the Astronautical Sciences, "Design Objectives for Tomorow's Big Boosters", 1963.
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