Nova 5S

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Nova 5S

Part of Nova

Nova NASA 5 Solids
Nova NASA 5 Solid Motors
Credit: © Mark Wade

American heavy-lift orbital launch vehicle. NASA Nova design using segmented solid motors in first and second stages. Five six segment motors in first stage; four four segment motors in second stage, equivalent to 9 x F-1 first stage and 4 x F-1 second stage.

Status: Study 1960. Payload: 176,000 kg (388,000 lb). Thrust: 126,772.00 kN (28,499,479 lbf). Gross mass: 10,076,200 kg (22,214,200 lb). Height: 147.00 m (482.00 ft). Diameter: 10.10 m (33.10 ft). Apogee: 160 km (90 mi).

LEO Payload: 176,000 kg (388,000 lb) to a 160 km orbit. Payload: 59,000 kg (130,000 lb) to a translunar trajectory.

Stage Data - Nova 5S

Stage 1. 5 x Nova Solid 6. Gross Mass: 1,224,000 kg (2,698,000 lb). Empty Mass: 153,000 kg (337,000 lb). Thrust (vac): 28,017.000 kN (6,298,472 lbf). Isp: 263 sec. Burn time: 97 sec. Isp(sl): 238 sec. Diameter: 5.20 m (17.00 ft). Span: 5.20 m (17.00 ft). Length: 45.70 m (149.90 ft). Propellants: Solid. No Engines: 1. Engine: 200 inch solid segment x 6. Status: Study, NASA, 1960. Comments: 5 used as first stage of solid Nova design. Masses estimated based on total vehicle thrust, performance, and stage volumes.

Stage 2. 4 x Nova Solid 4. Gross Mass: 816,000 kg (1,798,000 lb). Empty Mass: 102,000 kg (224,000 lb). Thrust (vac): 11,120.000 kN (2,499,870 lbf). Isp: 285 sec. Burn time: 175 sec. Diameter: 5.20 m (17.00 ft). Span: 5.20 m (17.00 ft). Length: 35.10 m (115.10 ft). Propellants: Solid. No Engines: 1. Engine: 200 inch solid segment x 4. Status: Study, NASA, 1960. Comments: 4 used as first stage of solid Nova design. Extended high-expansion nozzles. Masses estimated based on total vehicle thrust, performance, and stage volumes.

Stage 3. 1 x Nova 9L-3. Gross Mass: 363,000 kg (800,000 lb). Empty Mass: 36,000 kg (79,000 lb). Thrust (vac): 5,334.000 kN (1,199,130 lbf). Isp: 420 sec. Burn time: 250 sec. Diameter: 10.10 m (33.10 ft). Span: 10.10 m (33.10 ft). Length: 21.30 m (69.80 ft). Propellants: Lox/LH2. No Engines: 6. Engine: J-2. Status: Study, NASA, 1960. Comments: Masses estimated based on total vehicle thrust, performance, and stage volumes.

Stage 4. 1 x Nova 9L-4. Gross Mass: 118,000 kg (260,000 lb). Empty Mass: 14,000 kg (30,000 lb). Thrust (vac): 1,775.000 kN (399,035 lbf). Isp: 420 sec. Burn time: 235 sec. Diameter: 6.70 m (21.90 ft). Span: 6.70 m (21.90 ft). Length: 20.70 m (67.90 ft). Propellants: Lox/LH2. No Engines: 2. Engine: J-2. Status: Study, NASA, 1960. Comments: Masses estimated based on total vehicle thrust, performance, and stage volumes.

Family: heavy-lift, orbital launch vehicle. Country: USA. Engines: J-2. Launch Vehicles: Nova 5S. Propellants: Solid. Stages: 200 inch solid segment x 4, 200 inch solid segment x 6, Nova 9L-3, Nova 9L-4. Agency: NASA.

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