Shuttle-C - Credit: Boeing. 18,735 bytes. 212 x 428 pixels.

Marshall design for replacement of shuttle orbiter with recoverable main engine pod. Same concept as Interim Heavy Lift Launch Vehicle; IHLLV. 2 SSME configuration would have a payload of 45,450 kg.

LEO Payload: 77,000 kg. to: 400 km Orbit. at: 28.0 degrees. Liftoff Thrust: 2,069,940 kgf. Total Mass: 1,966,675 kg. Core Diameter: 8.7 m. Total Length: 56.0 m. Flyaway Unit Cost $: 84.97 million. in 1985 unit dollars.

• Stage Number: 0. 2 x Shuttle SRB Gross Mass: 589,670 kg. Empty Mass: 86,183 kg. Thrust (vac): 1,174,713 kgf. Isp: 269 sec. Burn time: 124 sec. Isp(sl): 237 sec. Diameter: 3.7 m. Span: 5.1 m. Length: 38.5 m. Propellants: Solid No Engines: 1. SRB

• Stage Number: 1. 1 x Shuttle Tank Gross Mass: 750,975 kg. Empty Mass: 29,930 kg. Thrust (vac): 0 kgf. Isp: 455 sec. Burn time: 480 sec. Isp(sl): 363 sec. Diameter: 8.7 m. Span: 8.7 m. Length: 46.9 m. Propellants: Lox/LH2 No Engines: 0. None

• Stage Number: 2. 1 x Shuttle C Gross Mass: 36,360 kg. Empty Mass: 34,380 kg. Thrust (vac): 696,905 kgf. Isp: 313 sec. Burn time: 120 sec. Isp(sl): 0 sec. Diameter: 6.3 m. Span: 6.3 m. Length: 21.0 m. Propellants: N2O4/MMH No Engines: 2. OME

• 44 - Jenkins, Dennis R,, Space Shuttle: The History of Developing the National Space Transportation System, Motorbooks International, ISBN 0-9633974-4-3, 1996.

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Shuttle C Credit: © Mark Wade. 5,612 bytes. 183 x 611 pixels.

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