Jarvis launch vehicle

American orbital launch vehicle. Launch vehicle planned for Pacific launch based on Saturn V engines, tooling. Masses, payload estimated.

LEO Payload: 38,000 kg (83,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 13,000 kg (28,000 lb) to a GTO. Flyaway Unit Cost 1985$: 260.000 million.

Stage Data - Jarvis

• Stage 1. 1 x Jarvis-1. Gross Mass: 950,000 kg (2,090,000 lb). Empty Mass: 60,000 kg (132,000 lb). Thrust (vac): 15,481.260 kN (3,480,326 lbf). Isp: 304 sec. Burn time: 170 sec. Isp(sl): 265 sec. Diameter: 8.38 m (27.49 ft). Span: 8.38 m (27.49 ft). Length: 35.00 m (114.00 ft). Propellants: Lox/Kerosene. No Engines: 2. Engine: F-1. Status: Study 1985.

• Stage 2. 1 x Jarvis-2. Gross Mass: 145,000 kg (319,000 lb). Empty Mass: 15,000 kg (33,000 lb). Thrust (vac): 1,031.983 kN (231,999 lbf). Isp: 425 sec. Burn time: 525 sec. Isp(sl): 200 sec. Diameter: 8.38 m (27.49 ft). Span: 8.38 m (27.49 ft). Length: 10.00 m (32.00 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Status: Study 1985.

• Stage 3. 1 x Jarvis-3. Gross Mass: 13,400 kg (29,500 lb). Empty Mass: 2,000 kg (4,400 lb). Thrust (vac): 3.920 kN (881 lbf). Isp: 312 sec. Burn time: 8,100 sec. Diameter: 5.18 m (16.99 ft). Span: 5.18 m (16.99 ft). Length: 3.00 m (9.80 ft). Propellants: N2O4/MMH. No Engines: 8. Engine: R-4D. Status: Study 1985.