Encyclopedia Astronautica
Nova 7S



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Nova NASA 7 Solid Mo
Nova NASA 7 Solid Motors
Credit: © Mark Wade
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Nova Concepts - NASA
Credit: © Mark Wade
American heavy-lift orbital launch vehicle. NASA Nova design using a cluster of 7 x 160 inch solid motors used as first stage; upper stages as Nova 4S and 8L.

LEO Payload: 197,300 kg (434,900 lb) to a 160 km orbit. Payload: 75,300 kg (166,000 lb) to a translunar trajectory.

Stage Data - Nova 7S

  • Stage 1. 7 x 160 inch solid. Gross Mass: 907,000 kg (1,999,000 lb). Empty Mass: 91,000 kg (200,000 lb). Thrust (vac): 13,788.000 kN (3,099,665 lbf). Isp: 263 sec. Burn time: 150 sec. Isp(sl): 238 sec. Diameter: 4.10 m (13.40 ft). Span: 4.10 m (13.40 ft). Length: 36.60 m (120.00 ft). Propellants: Solid. No Engines: 1. Status: Study NASA, 1960. Comments: Notional 160 inch solid motor considered in cluster of 7 as alternative to Nova 8 F-1 stage. Led to 156 inch motors tested in late 1960's.
  • Stage 2. 1 x Nova 60-8-2. Gross Mass: 680,000 kg (1,490,000 lb). Empty Mass: 54,000 kg (119,000 lb). Thrust (vac): 10,669.000 kN (2,398,486 lbf). Isp: 428 sec. Burn time: 242 sec. Isp(sl): 310 sec. Diameter: 11.60 m (38.00 ft). Span: 11.60 m (38.00 ft). Length: 35.10 m (115.10 ft). Propellants: Lox/LH2. No Engines: 2. Engine: M-1. Status: Study 1960. Comments: Mass estimated based on total LV weight. J-2-powered version of this stage also proposed.
  • Stage 3. 1 x Nova 60-8-3. Gross Mass: 227,000 kg (500,000 lb). Empty Mass: 23,000 kg (50,000 lb). Thrust (vac): 892.000 kN (200,529 lbf). Isp: 425 sec. Burn time: 941 sec. Isp(sl): 306 sec. Diameter: 6.70 m (21.90 ft). Span: 6.70 m (21.90 ft). Length: 30.50 m (100.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1960. Comments: Mass estimated based on total LV weight.

Status: Study 1960.
Gross mass: 7,492,760 kg (16,518,700 lb).
Payload: 197,300 kg (434,900 lb).
Height: 123.00 m (403.00 ft).
Diameter: 11.60 m (38.00 ft).
Thrust: 87,342.40 kN (19,635,353 lbf).
Apogee: 160 km (90 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • J-2 Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966. 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
  • NASA American agency overseeing development of rockets and spacecraft. National Aeronautics and Space Administration, USA, USA. More...

Associated Stages
  • 160 inch solid Solid propellant rocket stage. Loaded/empty mass 907,000/91,000 kg. Thrust 13,788.00 kN. Vacuum specific impulse 263 seconds. Notional 160 inch solid motor considered in cluster of 7 as alternative to Nova 8 F-1 stage. Led to 156 inch motors tested in late 1960's. More...
  • Nova 60-8-2 Lox/LH2 propellant rocket stage. Loaded/empty mass 680,000/54,000 kg. Thrust 10,669.00 kN. Vacuum specific impulse 428 seconds. Mass estimated based on total LV weight. J-2-powered version of this stage also proposed. More...
  • Nova 60-8-3 Lox/LH2 propellant rocket stage. Loaded/empty mass 227,000/23,000 kg. Thrust 892.00 kN. Vacuum specific impulse 425 seconds. Mass estimated based on total LV weight. More...

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