Nova Model R10E/R10R
Nova Martin Marietta Model R10E-2 / R10R-2
Credit: © Mark Wade
Nova Martin Marietta
Cutaway view of Martin Marrietta air-breathing single stage to orbit Nova R10R-2 concept
Credit: Lockheed Martin
American heavy-lift orbital launch vehicle. Expendable version of most exotic Martin Nova vairant; single stage to orbit, 30 cd module air augmented engines in annular shroud. Operational date would have been October 1980.
LEO Payload: 596,000 kg (1,313,000 lb) to a 185 km orbit.
Stage Data - Nova MM R10E-2
- Stage 1. 1 x Nova MM R10E-2. Gross Mass: 8,474,000 kg (18,681,000 lb). Empty Mass: 1,188,000 kg (2,619,000 lb). Thrust (vac): 140,539.000 kN (31,594,424 lbf). Isp: 620 sec. Burn time: 310 sec. Isp(sl): 620 sec. Diameter: 21.30 m (69.80 ft). Span: 43.70 m (143.30 ft). Length: 49.10 m (161.00 ft). Propellants: Air/Lox/LH2. No Engines: 40. Engine: CD Module. Status: Study 1963. Comments: Operational date would have been October 1980. Expendable stage. Air-augmented plug nozzle.
Status: Study 1963.
More... - Chronology...
Gross mass: 9,189,200 kg (20,258,700 lb).
Payload: 596,000 kg (1,313,000 lb).
Height: 59.00 m (193.00 ft).
Diameter: 21.30 m (69.80 ft).
Thrust: 140,540.00 kN (31,594,640 lbf).
Apogee: 185 km (114 mi).
CD Module Notional lox/lh2 rocket engine. 7361 kN. Study 1969. Isp=420s. CD Modules - conceptual engines of various thrusts, according to design - were clustered in Martin Marietta Nova designs More...
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...
Nova MM R10E-2 Air/Lox/LH2 propellant rocket stage. Loaded/empty mass 8,474,000/1,188,000 kg. Thrust 140,539.00 kN. Specific impulse 620 seconds. Operational date would have been October 1980. Expendable stage. Air-augmented plug nozzle. More...
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