Encyclopedia Astronautica
Nova GD-F



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Nova Model F
Nova General Dynamics Model F
Credit: © Mark Wade
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Nova Model F Cutaway
Nova General Dynamics Model F Cutaway
Credit: © Mark Wade
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Nova F, H and J
Cutaway view of General Dynamics Nova F, H and J concepts.
Credit: Lockheed Martin
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Nova - GD
Nova Concepts - General Dynamics
Credit: © Mark Wade
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Nova GD Advanced
General Dynamics advanced Nova designs
Credit: Lockheed Martin
American heavy-lift orbital launch vehicle. General Dynamics Nova design using new 3.5 million kgf Lox/Kerosene engines in first stage. Recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.

LEO Payload: 454,000 kg (1,000,000 lb) to a 185 km orbit.

Stage Data - Nova GD-F

  • Stage 1. 1 x Nova GD-F-1. Gross Mass: 9,977,000 kg (21,995,000 lb). Empty Mass: 680,000 kg (1,490,000 lb). Thrust (vac): 148,031.000 kN (33,278,692 lbf). Isp: 335 sec. Burn time: 203 sec. Isp(sl): 310 sec. Diameter: 18.30 m (60.00 ft). Span: 26.20 m (85.90 ft). Length: 54.30 m (178.10 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: L-7.70. Status: Study General Dynamics 1963. Comments: Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange.
  • Stage 2. 1 x Nova GD-F-2. Gross Mass: 1,497,000 kg (3,300,000 lb). Empty Mass: 91,000 kg (200,000 lb). Thrust (vac): 13,346.000 kN (3,000,300 lbf). Isp: 428 sec. Burn time: 435 sec. Diameter: 18.30 m (60.00 ft). Span: 18.30 m (60.00 ft). Length: 29.90 m (98.00 ft). Propellants: Lox/LH2. No Engines: 2. Engine: M-1. Status: Study General Dynamics 1963. Comments: Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.

Status: Study 1963.
Gross mass: 12,018,800 kg (26,496,900 lb).
Payload: 454,000 kg (1,000,000 lb).
Height: 101.00 m (331.00 ft).
Diameter: 18.30 m (60.00 ft).
Thrust: 136,984.30 kN (30,795,296 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • L-7.70 Notional Lox/Kerosene rocket engine. 37,007 kN. Study 1963. Engines used in recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange. Isp=335s. More...
  • M-1 Aerojet lox/lh2 rocket engine. 5335.9 kN. Study 1961. Isp=428s. Engine developed 1962-1966 for Uprated Saturn and Nova million-pound payload boosters to support manned Mars missions. Reached component test stage before cancellation. 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
  • Martin American manufacturer of rockets, spacecraft, and rocket engines. Martin Marietta Astronautics Group (1956), Denver, CO, USA. More...

Associated Stages
  • Nova GD-F-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 9,977,000/680,000 kg. Thrust 148,031.00 kN. Vacuum specific impulse 335 seconds. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange. More...
  • Nova GD-F-2 Lox/LH2 propellant rocket stage. Loaded/empty mass 1,497,000/91,000 kg. Thrust 13,346.00 kN. Vacuum specific impulse 428 seconds. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. More...

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