Encyclopedia Astronautica
Nova MM 33



nomm33.gif
Nova Model 33
Nova Martin Marietta Model 33
Credit: © Mark Wade
novammc2.jpg
Nova 24G, 34, and 33
Nova Martin Marietta designs 24G, 34, and 33
Credit: Lockheed Martin
American heavy-lift orbital launch vehicle. Nova single stage to orbit design with 24 new high pressure LH2/Lox engines in the first stage in a plug nozzle arrangement. Operational date would have been April 1975.

LEO Payload: 472,000 kg (1,040,000 lb) to a 185 km orbit.

Stage Data - Nova MM 33

  • Stage 1. 1 x Nova MM 33-1. Gross Mass: 10,489,000 kg (23,124,000 lb). Empty Mass: 626,000 kg (1,380,000 lb). Thrust (vac): 156,876.000 kN (35,267,127 lbf). Isp: 443 sec. Burn time: 268 sec. Isp(sl): 379 sec. Diameter: 24.40 m (80.00 ft). Span: 26.20 m (85.90 ft). Length: 75.90 m (249.00 ft). Propellants: Lox/LH2. No Engines: 24. Engine: HP-1. Status: Study 1963. Comments: Operational date would have been April 1975. SSTO - payload 1,042,000 lbs.

Status: Study 1963.
Gross mass: 11,055,400 kg (24,372,900 lb).
Payload: 472,000 kg (1,040,000 lb).
Height: 91.00 m (298.00 ft).
Diameter: 24.40 m (80.00 ft).
Thrust: 134,213.00 kN (30,172,282 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • HP-1 Notional lox/lh2 rocket engine. 6536 kN. Study 1963. Operational date would have been December 1974. Isp=451s. Used in Martin Nova studies MM 24G, MM 33. 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 MM 33-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 10,489,000/626,000 kg. Thrust 156,876.00 kN. Vacuum specific impulse 443 seconds. Operational date would have been April 1975. SSTO - payload 1,042,000 lbs. More...

Home - Browse - Contact
© / Conditions for Use