Jarvis Booster - Jarvis Launch Vehicle Credit: Hughes. 7,333 bytes. 68 x 387 pixels.

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

LEO Payload: 38,000 kg. to: 185 km Orbit. at: 28.0 degrees. Payload: 13,000 kg. to a: Geosynchronous transfer trajectory. Liftoff Thrust: 1,376,130 kgf. Total Mass: 1,154,000 kg. Core Diameter: 8.4 m. Total Length: 58.0 m. Flyaway Unit Cost $: 260.00 million. in 1985 unit dollars.

• Stage Number: 1. 1 x Jarvis-1 Gross Mass: 950,000 kg. Empty Mass: 60,000 kg. Thrust (vac): 1,578,650 kgf. Isp: 304 sec. Burn time: 170 sec. Isp(sl): 265 sec. Diameter: 8.4 m. Span: 8.4 m. Length: 35.0 m. Propellants: Lox/Kerosene No Engines: 2. F-1

• Stage Number: 2. 1 x Jarvis-2 Gross Mass: 145,000 kg. Empty Mass: 15,000 kg. Thrust (vac): 105,233 kgf. Isp: 425 sec. Burn time: 525 sec. Isp(sl): 200 sec. Diameter: 8.4 m. Span: 8.4 m. Length: 10.0 m. Propellants: Lox/LH2 No Engines: 1. J-2

• Stage Number: 3. 1 x Jarvis-3 Gross Mass: 13,400 kg. Empty Mass: 2,000 kg. Thrust (vac): 400 kgf. Isp: 312 sec. Burn time: 8,100 sec. Isp(sl): 0 sec. Diameter: 5.2 m. Span: 5.2 m. Length: 3.0 m. Propellants: N2O4/MMH No Engines: 8. R-4D

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

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Jarvis launch pad - Jarvis launc pad on Christmas Island in the mid-Pacific Credit: Hughes. 10,110 bytes. 218 x 179 pixels.

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