Nova GD-E

American heavy-lift orbital launch vehicle. General Dynamics Nova design using 325 inch solid motors as first stage, M-1 engines in second stage. Recoverable solid motors, separation at 1,972 m/s at 53,000 m altitude; splashdown using retrorockets under 3 61 m diameter parachutes 610 km downrange. Recovery of solid motors foreshadowed same approach on shuttle 15 years later. Masses estimated based on tank volumes, total thrust, and first stage burnout conditions.

LEO Payload: 458,000 kg (1,009,000 lb) to a 185 km orbit.

Stage Data - Nova GD-E

• Stage 1. 4 x Nova GD-E-1. Gross Mass: 3,628,000 kg (7,998,000 lb). Empty Mass: 454,000 kg (1,000,000 lb). Thrust (vac): 69,048.000 kN (15,522,607 lbf). Isp: 263 sec. Burn time: 116 sec. Isp(sl): 238 sec. Diameter: 8.30 m (27.20 ft). Span: 8.30 m (27.20 ft). Length: 60.40 m (198.10 ft). Propellants: Solid. No Engines: 1. Engine: 325 in solid. Status: Study General Dynamics 1963. Comments: Massed estimated based on tank volumes, total thrust, and first stage burnout conditions. Recoverable stage; separation at 1,972 m/s at 53,000 m altitude; splashdown using retrorockets under 3 61 m diameter parachutes 610 km downrange.

• Stage 2. 1 x Nova GD-E-2. Gross Mass: 4,535,000 kg (9,997,000 lb). Empty Mass: 363,000 kg (800,000 lb). Thrust (vac): 26,683.000 kN (5,998,577 lbf). Isp: 428 sec. Burn time: 646 sec. Diameter: 20.60 m (67.50 ft). Span: 20.60 m (67.50 ft). Length: 47.90 m (157.10 ft). Propellants: Lox/LH2. No Engines: 4. Engine: M-1. Status: Study General Dynamics 1963. Comments: Massed estimated based on tank volumes, total thrust, and first stage burnout conditions.