Encyclopedia Astronautica
Jarvis



jarvipad.jpg
Jarvis launch pad
Jarvis launch pad on Christmas Island in the mid-Pacific
Credit: Hughes
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 in 1985 dollars. Flyaway Unit Cost $: 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. Isp(sl): 0.0000 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.

Status: Study 1985.
Gross mass: 1,154,000 kg (2,544,000 lb).
Payload: 38,000 kg (83,000 lb).
Height: 58.00 m (190.00 ft).
Diameter: 8.38 m (27.49 ft).
Thrust: 13,495.20 kN (3,033,842 lbf).
Apogee: 185 km (114 mi).

More... - Chronology...


Associated Countries
Associated Engines
  • F-1 Rocketdyne Lox/Kerosene rocket engine. 7740.5 kN. Isp=304s. Largest liquid rocket engine ever developed and flown. Severe combustion stability problems were solved during development and it never failed in flight. First flight 1967. More...
  • J-2 Rocketdyne lox/lh2 rocket engine. 1033.1 kN. Study 1961. Isp=421s. Used in Saturn IVB stage in Saturn IB and Saturn V, and Saturn II stage in Saturn V. Gas generator, pump-fed. First flight 1966. More...
  • R-4D Marquardt N2O4/MMH rocket engine. 0.490 kN. Isp=312s. Developed as attitude control thruster for the Apollo Service and Lunar Modules in 1960s. In production for numerous satellites for apogee / perigee maneuvers, orbit adjustment, and attitude control. More...

See also
  • Saturn The Saturn launch vehicle was the penultimate expression of the Peenemuende Rocket Team's designs for manned exploration of the moon and Mars. Numerous designs and variants were studied, but in the end only three models - the Saturn I, IB, and V - were built in the 1960's, and then only used to support NASA's Apollo moon landing program. More...

Associated Manufacturers and Agencies
  • Hughes American manufacturer of rockets, spacecraft, and rocket engines. Hughes Aircraft Co. , USA More...

Bibliography
  • "Air Force Studies MLV", Aviation Week and Space Technology, 1986-08-04, page 34.

Associated Stages
  • Jarvis-2 Lox/LH2 propellant rocket stage. Loaded/empty mass 145,000/15,000 kg. Thrust 1,031.98 kN. Vacuum specific impulse 425 seconds. More...
  • Jarvis-3 N2O4/MMH propellant rocket stage. Loaded/empty mass 13,400/2,000 kg. Thrust 3.92 kN. Vacuum specific impulse 312 seconds. More...
  • Jarvis-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 950,000/60,000 kg. Thrust 15,481.26 kN. Vacuum specific impulse 304 seconds. More...

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