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Nova 4L

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Nova NASA 4 F-1 Credit: © Mark Wade

Status: Study 1959. Payload: 68,000 kg (149,000 lb). Thrust: 33,712.00 kN (7,578,759 lbf). Gross mass: 3,084,600 kg (6,800,300 lb). Height: 78.00 m (255.00 ft). Diameter: 15.50 m (50.80 ft). Apogee: 160 km (90 mi).

LEO Payload: 68,000 kg (149,000 lb) to a 160 km orbit. Payload: 24,000 kg (52,000 lb) to a translunar trajectory.

Stage Data - Nova 4L

• Stage 1. 1 x Nova 59-4-1. Gross Mass: 2,177,000 kg (4,799,000 lb). Empty Mass: 136,000 kg (299,000 lb). Thrust (vac): 38,697.000 kN (8,699,431 lbf). Isp: 295 sec. Burn time: 150 sec. Isp(sl): 257 sec. Diameter: 15.50 m (50.80 ft). Span: 15.50 m (50.80 ft). Length: 23.20 m (76.10 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1. Status: Study NASA 1959. Comments: Empty Mass Estimated.

• Stage 2. 1 x Nova 59-4-2. Gross Mass: 590,000 kg (1,300,000 lb). Empty Mass: 45,000 kg (99,000 lb). Thrust (vac): 7,560.000 kN (1,699,550 lbf). Isp: 310 sec. Burn time: 215 sec. Isp(sl): 265 sec. Diameter: 5.20 m (17.00 ft). Span: 5.20 m (17.00 ft). Length: 16.20 m (53.10 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: F-1. Status: Study NASA 1959. Comments: Empty Mass Estimated.

• Stage 3. 1 x Nova 59-4-3. Gross Mass: 168,000 kg (370,000 lb). Empty Mass: 18,000 kg (39,000 lb). Thrust (vac): 1,421.000 kN (319,453 lbf). Isp: 420 sec. Burn time: 426 sec. Isp(sl): 306 sec. Diameter: 5.20 m (17.00 ft). Span: 5.20 m (17.00 ft). Length: 14.00 m (45.00 ft). Propellants: Lox/LH2. No Engines: 4. Engine: LH2-80k. Status: Study NASA 1959. Comments: Empty Mass Estimated.

• Stage 4. 1 x Nova 59-4-4. Gross Mass: 68,000 kg (149,000 lb). Empty Mass: 9,000 kg (19,800 lb). Thrust (vac): 353.000 kN (79,357 lbf). Isp: 420 sec. Burn time: 672 sec. Isp(sl): 306 sec. Diameter: 3.00 m (9.80 ft). Span: 3.00 m (9.80 ft). Length: 11.90 m (39.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: LH2-80k. Status: Study NASA 1959. Comments: Empty Mass Estimated.

Photo Gallery

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Nova Concepts - NASA Credit: © Mark Wade

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Nova NASA 4 F-1 Nova NASA 4 F-1 / Nerva Credit: © Mark Wade

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• First meeting of the Manned Lunar Landing Task Group - . Nation: USA. Related Persons: Silverstein. Program: Apollo. Spacecraft: Apollo CSM, Apollo Lunar Landing, CSM Source Selection, LM Mode Debate, LM Source Selection.

  At the first meeting of the Manned Lunar Landing Task Group, Associate Administrator Robert C. Seamans, Jr., Director of the Office of Space Flight Programs Abe Silverstein, and Director of the Office of Advanced Research Programs Ira H. Abbott outlined the purpose of the Group to the members. After a discussion of the instructions, the Group considered first the objectives of the total NASA program:

  1. the exploration of the solar system for knowledge to benefit mankind; and
  2. the development of technology to permit exploitation of space flight for scientific, military, and commercial uses.
  NASA's lunar program was a logical step toward these objectives. In current lunar program planning, three steps were projected:
  1. a manned landing on the moon with return to earth,
  2. limited manned lunar exploration, and
  3. a scientific lunar base.
  To accomplish the first step, a great increase in launch vehicle capability would be needed beyond that provided by current funding. A comparison of a three-million-pound-thrust and a six-million-pound-thrust Nova launch vehicle was made. It was estimated that a 60,000- to 80,000-pound payload to escape velocity would be needed for a manned lunar landing mission.