 | Nova NASA 9 F-1
Credit - © Mark Wade
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Orbital launch vehicle. Year: 1960. Family: Nova. Country: USA. Status: Study 1960. NASA Nova design using clustered small diameter tanks; 9 x F-1 first stage and 4 x F-1 second stage; compared with solid Nova using five six segment solid motors in first stage and four four segment motors in second stage. Manufacturer: NASA. LEO Payload: 176,000 kg (388,000 lb). to: 160 km Orbit. Payload: 59,000 kg (130,000 lb). to a: translunar trajectory. Liftoff Thrust: 59,318.000 kN (13,335,216 lbf). Total Mass: 5,227,200 kg (11,524,000 lb). Core Diameter: 15.20 m (49.80 ft). Total Length: 144.00 m (472.00 ft).
Stage Data - Nova 9L - Stage Number: 1. 1 x Stage: Nova 9L-1. Gross Mass: 2,721,000 kg (5,998,000 lb). Empty Mass: 181,000 kg (399,000 lb). Thrust (vac): 68,048.000 kN (15,297,798 lbf). Isp: 304 sec. Burn time: 110 sec. Isp(sl): 265 sec. Diameter: 15.20 m (49.80 ft). Span: 15.20 m (49.80 ft). Length: 42.70 m (140.00 ft). Propellants: Lox/Kerosene. No Engines: 9. Engine: F-1. Status: Study 1960. Masses estimated based on total vehicle thrust, performance, and stage volumes.
- Stage Number: 2. 1 x Stage: Nova 9L-2. Gross Mass: 1,814,000 kg (3,999,000 lb). Empty Mass: 125,000 kg (275,000 lb). Thrust (vac): 30,243.000 kN (6,798,896 lbf). Isp: 304 sec. Burn time: 164 sec. Isp(sl): 265 sec. Diameter: 13.70 m (44.90 ft). Span: 13.70 m (44.90 ft). Length: 35.10 m (115.10 ft). Propellants: Lox/Kerosene. No Engines: 4. Engine: F-1. Status: Study 1960. Masses estimated based on total vehicle thrust, performance, and stage volumes.
- Stage Number: 3. 1 x Stage: 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 1960. Masses estimated based on total vehicle thrust, performance, and stage volumes.
- Stage Number: 4. 1 x Stage: 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 1960. Masses estimated based on total vehicle thrust, performance, and stage volumes.
Bibliography and Further Reading - Hobbs, Marvin, Fundamentals of Rockets, Missiles, and Spacecraft, John F Rider, 1961..
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