Nova GD-F

American heavy-lift orbital launch vehicle. General Dynamics Nova design using new 3.5 million kgf LOx/Kerosene engines in first stage. Recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange. Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.

LEO Payload: 454,000 kg (1,000,000 lb) to a 185 km orbit.

Stage Data - Nova GD-F

• Stage 1. 1 x Nova GD-F-1. Gross Mass: 9,977,000 kg (21,995,000 lb). Empty Mass: 680,000 kg (1,490,000 lb). Thrust (vac): 148,031.000 kN (33,278,692 lbf). Isp: 335 sec. Burn time: 203 sec. Isp(sl): 310 sec. Diameter: 18.30 m (60.00 ft). Span: 26.20 m (85.90 ft). Length: 54.30 m (178.10 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: L-7.70. Status: Study General Dynamics 1963. Comments: Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable stage; separation at 3,365 m/s at 89,300 m altitude; splashdown using retrorockets under 8 46 m diameter parachutes 1300 km downrange.

• Stage 2. 1 x Nova GD-F-2. Gross Mass: 1,497,000 kg (3,300,000 lb). Empty Mass: 91,000 kg (200,000 lb). Thrust (vac): 13,346.000 kN (3,000,300 lbf). Isp: 428 sec. Burn time: 435 sec. Diameter: 18.30 m (60.00 ft). Span: 18.30 m (60.00 ft). Length: 29.90 m (98.00 ft). Propellants: Lox/LH2. No Engines: 2. Engine: M-1. Status: Study General Dynamics 1963. Comments: Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.