Encyclopedia Astronautica
Nova MM R10R-2


Air/Lox/LH2 propellant rocket stage. Loaded/empty mass 8,647,000/1,361,000 kg. Thrust 140,539.00 kN. Specific impulse 620 seconds. Operational date would have been October 1980. Recoverable stage. Air-augmented plug nozzle.

No Engines: 40.

Status: Study 1963.
Gross mass: 8,647,000 kg (19,063,000 lb).
Unfuelled mass: 1,361,000 kg (3,000,000 lb).
Height: 49.30 m (161.70 ft).
Diameter: 21.30 m (69.80 ft).
Span: 43.70 m (143.30 ft).
Thrust: 140,539.00 kN (31,594,424 lbf).
Specific impulse: 620 s.
Specific impulse sea level: 620 s.
Burn time: 310 s.

More... - Chronology...


Associated Countries
Associated Engines
  • 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...

Associated Launch Vehicles
  • Nova MM R10R-2 American heavy-lift orbital launch vehicle. Reusable 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. More...

Associated Propellants
  • Air/Lox/LH2 Ambient air (78 % nitrogen, 21% oxygen, etc.) is scooped up by air intakes and used in turbojet, turbofan, ramjet, scramjet, or other airbreathing engines as an oxidiser. In this variant the motor converts to pure rocket propulsion, using on-board liquid oxygen for the final push to orbit. More...

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