Encyclopedia Astronautica
Nova GD-B



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Nova Model B
Nova General Dynamics Model B
Credit: © Mark Wade
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Nova GD Advanced
General Dynamics advanced Nova designs
Credit: Lockheed Martin
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Nova - GD
Nova Concepts - General Dynamics
Credit: © Mark Wade
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Nova Model B Cutaway
Nova General Dynamics Model B Cutaway
Credit: © Mark Wade
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Nova B and E
Cutaway view of General Dynamics Nova B and E concepts.
Credit: Lockheed Martin
American heavy-lift orbital launch vehicle. General Dynamics Nova design using existing engines. Recoverable engine package; separation at 3,398 m/s at 76,200 m altitude; splashdown using retrorockets under 7 30 m diameter parachutes 1300 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.

LEO Payload: 338,000 kg (745,000 lb) to a 185 km orbit.

Stage Data - Nova GD-B

  • Stage 1. 1 x Nova GD-B-1. Gross Mass: 9,070,000 kg (19,990,000 lb). Empty Mass: 635,000 kg (1,399,000 lb). Thrust (vac): 142,451.000 kN (32,024,258 lbf). Isp: 310 sec. Burn time: 177 sec. Isp(sl): 271 sec. Diameter: 20.60 m (67.50 ft). Span: 25.70 m (84.30 ft). Length: 45.20 m (148.20 ft). Propellants: Lox/Kerosene. No Engines: 16. Engine: F-1A. Status: Study General Dynamics 1963. Comments: Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable engine package; separation at 3,398 m/s at 76,200 m altitude; splashdown using retrorockets under 7 30 m diameter parachutes 1300 km downrange.
  • Stage 2. 1 x Nova GD-B-2. Gross Mass: 998,000 kg (2,200,000 lb). Empty Mass: 75,000 kg (165,000 lb). Thrust (vac): 10,669.000 kN (2,398,486 lbf). Isp: 428 sec. Burn time: 357 sec. Diameter: 20.60 m (67.50 ft). Span: 20.60 m (67.50 ft). Length: 27.10 m (88.90 ft). Propellants: Lox/LH2. No Engines: 5. Engine: J-2. Status: Study General Dynamics 1963. Comments: Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.

Status: Study 1963.
Gross mass: 10,473,600 kg (23,090,300 lb).
Payload: 338,000 kg (745,000 lb).
Height: 87.00 m (285.00 ft).
Diameter: 20.60 m (67.50 ft).
Thrust: 124,530.10 kN (27,995,480 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • F-1A Rocketdyne Lox/Kerosene rocket engine. 9189.6 kN. Study 1968. Designed for booster applications. Gas generator, pump-fed. Isp=310s. More...
  • J-2 Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966. More...

See also
  • Nova Nova was NASA's ultimate launch vehicle, studied intently from 1959 to 1962. Originally conceived to allow a direct manned landing on the moon, in its final iteration it was to put a million-pound payload into low earth orbit to support manned Mars expeditions. It was abandoned in NASA advanced mission planning thereafter in favor of growth versions of the Saturn V. More...

Associated Manufacturers and Agencies
  • Convair American manufacturer of rockets, spacecraft, and rocket engines. Convair, USA. More...

Associated Stages
  • Nova GD-B-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 9,070,000/635,000 kg. Thrust 142,451.00 kN. Vacuum specific impulse 310 seconds. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable engine package; separation at 3,398 m/s at 76,200 m altitude; splashdown using retrorockets under 7 30 m diameter parachutes 1300 km downrange. More...
  • Nova GD-B-2 Lox/LH2 propellant rocket stage. Loaded/empty mass 998,000/75,000 kg. Thrust 10,669.00 kN. Vacuum specific impulse 428 seconds. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. More...

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