---Swigert

CLV Credit: © Mark Wade

Shuttle-derived launch vehicle design selected by NASA Administrator Mike Griffin to boost the manned CEV Crew Exploration Vehicle into low earth orbit. A single shuttle solid rocket booster would be mated with an upper stage in the 160 tonne class, powered by a single SSME engine.

Several proposals were made in 2004 for a shuttle-derived booster to launch cargo payloads of 18 tonnes, or the manned CEV Crew Exploration Vehicle into low earth orbit. A single shuttle solid rocket booster would be mated with an upper stage in the 100 tonne class. NASA's own studies led it to a similar vehicle, but with a larger upper stage and a 25 tonne payload. The upper stage was supported by a Russian-type open Warren-truss interstage.

Manufacturer: NASA. LEO Payload: 25,000 kg. to: 500 km Orbit. at: 51.6 degrees. Associated Spacecraft: CEV. Liftoff Thrust: 1,034,000 kgf. Total Mass: 780,000 kg. Core Diameter: 3.77 m. Total Length: 88.54 m. Span: 5.50 m.

• Stage Number: 1. 1 x Shuttle RSRM Gross Mass: 590,000 kg. Empty Mass: 88,000 kg. Thrust (vac): 1,174,713 kgf. Isp: 267 sec. Burn time: 123 sec. Isp(sl): 235 sec. Diameter: 3.77 m. Span: 5.10 m. Length: 45.46 m. Propellants: Solid No Engines: 1. RSRM Other designations: Redesigned Solid Rocket Motor. Status: In production. Comments: After the Challenger disaster the redesigned solid rocket motors had a slight reduction in performance due to reliability improvements.

• Stage Number: 2. 1 x CLV Stage 2 Gross Mass: 160,000 kg. Empty Mass: 16,000 kg. Thrust (vac): 238,000 kgf. Isp: 465 sec. Burn time: 270 sec. Diameter: 5.50 m. Span: 5.50 m. Length: 32.00 m. Propellants: Lox/LH2 No Engines: 1. SSME Status: Study 2005. Comments: Second stage proposed by NASA for launch of CEV into low earth orbit. All masses estimated.