Encyclopedia Astronautica
Nova GD-J



nogdj.gif
Nova Model J
Nova General Dynamics Model J
Credit: © Mark Wade
novammgd.gif
Nova - GD
Nova Concepts - General Dynamics
Credit: © Mark Wade
novagdc3.jpg
Nova GD Advanced
General Dynamics advanced Nova designs
Credit: Lockheed Martin
novagdc2.jpg
Nova F, H and J
Cutaway view of General Dynamics Nova F, H and J concepts.
Credit: Lockheed Martin
nogdjcut.gif
Nova Model J Cutaway
Nova General Dynamics Model J Cutaway
Credit: © Mark Wade
American heavy-lift orbital launch vehicle. General Dynamics Nova design using recoverable Lox/RP-1 stage of ballistic shape with 3 million kgf engines; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 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-J

  • Stage 1. 1 x Nova GD-J-1. Gross Mass: 8,617,000 kg (18,997,000 lb). Empty Mass: 680,000 kg (1,490,000 lb). Thrust (vac): 124,044.000 kN (27,886,200 lbf). Isp: 330 sec. Burn time: 203 sec. Isp(sl): 310 sec. Diameter: 42.40 m (139.10 ft). Span: 20.10 m (65.90 ft). Length: 36.60 m (120.00 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: L-6.55. Status: Study General Dynamics 1963. Comments: Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable stage of ballistic shape; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange.
  • Stage 2. 1 x Nova GD-J-2. Gross Mass: 1,270,000 kg (2,790,000 lb). Empty Mass: 91,000 kg (200,000 lb). Thrust (vac): 13,346.000 kN (3,000,300 lbf). Isp: 428 sec. Burn time: 365 sec. Diameter: 19.50 m (63.90 ft). Span: 19.50 m (63.90 ft). Length: 38.00 m (124.00 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: 10,431,800 kg (22,998,100 lb).
Payload: 454,000 kg (1,000,000 lb).
Height: 90.00 m (295.00 ft).
Diameter: 42.40 m (139.10 ft).
Thrust: 116,526.40 kN (26,196,177 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • L-6.55 Notional Lox/Kerosene rocket engine. 31,010 kN. Study 1963. Engines used in recoverable stage of ballistic shape; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange. Isp=330s. 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
  • Convair American manufacturer of rockets, spacecraft, and rocket engines. Convair, USA. More...

Associated Stages
  • Nova GD-J-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 8,617,000/680,000 kg. Thrust 124,044.00 kN. Vacuum specific impulse 330 seconds. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable stage of ballistic shape; separation at 3,420 m/s at 93,900 m altitude; splashdown using retrorockets under 7 parachutes 1340 km downrange. More...
  • Nova GD-J-2 Lox/LH2 propellant rocket stage. Loaded/empty mass 1,270,000/91,000 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...

Home - Browse - Contact
© / Conditions for Use