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Helios
Credit - © Mark Wade
Nuclear-powered orbital launch vehicle. Country: USA. Status: Study 1960.

Study by Kraft Ehricke of a vehicle where the booster stage contains liquid oxygen tanks only and takes the nuclear second stage to the stratosphere. The nuclear sustainer then takes the payload to orbit or escape trajectory.

Manufacturer: Convair. Version:

Helios A. Status: Study 1960.

LEO Payload: 73,400 kg (161,800 lb). to: 556 km Orbit. Payload: 42,000 kg (92,000 lb). to a: escape trajectory. Liftoff Thrust: 5,670.000 kN (1,274,660 lbf). Total Mass: 441,080 kg (972,410 lb). Core Diameter: 6.70 m (21.90 ft). Total Length: 81.00 m (265.00 ft).

  • Stage1: 1 x Helios A-1. Gross Mass: 200,000 kg (440,000 lb). Empty Mass: 10,000 kg (22,000 lb). Motor: 4 x Helios Stage 1. Thrust (vac): 6,660.000 kN (1,497,220 lbf). Isp: 400 sec. Burn time: 110 sec. Length: 8.80 m (28.80 ft). Diameter: 6.70 m (21.90 ft). Propellants: Lox/LH2.
  • Stage2: 1 x Helios A-2. Gross Mass: 153,000 kg (337,000 lb). Empty Mass: 26,000 kg (57,000 lb). Motor: 1 x Nuclear 12 Gw. Thrust (vac): 2,892.000 kN (650,147 lbf). Isp: 830 sec. Burn time: 353 sec. Length: 67.10 m (220.10 ft). Diameter: 6.70 m (21.90 ft). Propellants: Nuclear/LH2.
Version:

Helios B. Status: Study 1960.

LEO Payload: 144,600 kg (318,700 lb). to: 556 km Orbit. Payload: 81,600 kg (179,800 lb). to a: escape trajectory. Liftoff Thrust: 6,619.000 kN (1,488,010 lbf). Total Mass: 586,520 kg (1,293,050 lb). Core Diameter: 6.70 m (21.90 ft). Total Length: 93.00 m (305.00 ft).

  • Stage1: 1 x Helios B-1. Gross Mass: 236,000 kg (520,000 lb). Empty Mass: 14,000 kg (30,000 lb). Motor: 5 x Helios Stage 1. Thrust (vac): 7,786.000 kN (1,750,362 lbf). Isp: 400 sec. Burn time: 110 sec. Length: 8.80 m (28.80 ft). Diameter: 6.70 m (21.90 ft). Propellants: Lox/LH2.
  • Stage2: 1 x Helios B-2. Gross Mass: 177,000 kg (390,000 lb). Empty Mass: 29,000 kg (63,000 lb). Motor: 1 x Nuclear 14 Gw. Thrust (vac): 3,330.000 kN (748,610 lbf). Isp: 830 sec. Burn time: 355 sec. Length: 77.70 m (254.90 ft). Diameter: 6.70 m (21.90 ft). Propellants: Nuclear/LH2.
Version:

Helios C. Status: Study 1960.

LEO Payload: 86,200 kg (190,000 lb). to: 556 km Orbit. Payload: 49,000 kg (108,000 lb). to a: escape trajectory. Liftoff Thrust: 10,586.000 kN (2,379,827 lbf). Total Mass: 807,440 kg (1,780,100 lb). Core Diameter: 8.50 m (27.80 ft). Total Length: 102.00 m (334.00 ft).

  • Stage1: 1 x Helios C-1. Gross Mass: 395,000 kg (870,000 lb). Empty Mass: 18,000 kg (39,000 lb). Motor: 8 x Helios Stage 1. Thrust (vac): 12,450.000 kN (2,798,870 lbf). Isp: 400 sec. Burn time: 117 sec. Length: 11.00 m (36.00 ft). Diameter: 8.50 m (27.80 ft). Propellants: Lox/LH2.
  • Stage2: 1 x Helios C-2. Gross Mass: 309,000 kg (681,000 lb). Empty Mass: 54,000 kg (119,000 lb). Motor: 2 x Nuclear 12 Gw. Thrust (vac): 5,780.000 kN (1,299,390 lbf). Isp: 830 sec. Burn time: 355 sec. Length: 85.40 m (280.10 ft). Diameter: 8.50 m (27.80 ft). Propellants: Nuclear/LH2.
Bibliography:

  • Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961.
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