Nova A - Credit: © Mark Wade. 1,295 bytes. 41 x 397 pixels.

Convair/Ehricke Nova design using standard tank/engine modules of 4.9 m diameter in both first and second stages; 4 F-1 engine/modules in first stage, 4 J-2 engine/modules in second stage.

LEO Payload: 68,000 kg. to: 556 km Orbit. at: 0.0 degrees. Payload: 27,000 kg. to a: escape trajectory. Liftoff Thrust: 2,721,480 kgf. Total Mass: 1,866,600 kg. Core Diameter: 9.8 m. Total Length: 78.0 m.

• Stage Number: 1. 1 x Nova A-1 Gross Mass: 1,342,000 kg. Empty Mass: 73,000 kg. Thrust (vac): 3,122,000 kgf. Isp: 304 sec. Burn time: 121 sec. Isp(sl): 265 sec. Diameter: 9.8 m. Span: 11.9 m. Length: 28.0 m. Propellants: Lox/Kerosene No Engines: 4. F-1

• Stage Number: 2. 1 x Nova A-2 Gross Mass: 403,000 kg. Empty Mass: 29,000 kg. Thrust (vac): 544,000 kgf. Isp: 420 sec. Burn time: 284 sec. Isp(sl): 150 sec. Diameter: 9.8 m. Span: 11.9 m. Length: 23.8 m. Propellants: Lox/LH2 No Engines: 4. J-2

• Stage Number: 3. 1 x Nova A-3 Gross Mass: 40,000 kg. Empty Mass: 4,000 kg. Thrust (vac): 32,000 kgf. Isp: 427 sec. Burn time: 480 sec. Diameter: 5.8 m. Span: 5.8 m. Length: 13.1 m. Propellants: Lox/LH2 No Engines: 5. RL-10

• Preparation for NOVA rocket motor tests.

  National Bureau of Standards broke ground for new research facility at Gaithersburg, Md., which will include a mega-pound deadweight testing machine to provide measurement standards for multimillion rocket thrust requirements.

• Nova launch vehicle studies begun.

  Studies of "unconventional" rockets using liquid fuels in the thrust range from 2 to 24 million pounds announced by NASA; 2 contracts being carried out by Aerojet-General and Rocketdyne Division of North American Aviation.

• 45 - Koelle, Heinz Hermann,, Handbook of Astronautical Engineering, McGraw-Hill,New York, 1961.