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 five-segment version of the shuttle solid rocket booster would be mated with a Lox/LH2 upper stage powered by a single J-2S 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. In the initial September 2005 design the 160 tonne upper stage was powered by an expendable version of the Shuttle SSME engine and supported by a Russian-type open Warren-truss interstage. A relatively unmodified single four-segment shuttle solid rocket booster would provide the first stage. By August 2006 the expense of the SSME and weight growth in the CEV forced NASA to switch to the J-2S engine powering a 127 tonne second stage, and a five-segment version of the SRB in the first stage. A conventional 'American' interstage was now shown.

Manufacturer: NASA. LEO Payload: 24,500 kg (54,000 lb). to: 160 km Orbit. at: 28.00 degrees. Payload: 25,000 kg (55,000 lb). to a: ISS 51.6 deg orbit trajectory. Associated Spacecraft: Orion. Liftoff Thrust: 13,963.443 kN (3,139,107 lbf). Total Mass: 907,000 kg (1,999,000 lb). Core Diameter: 3.77 m (12.36 ft). Total Length: 94.20 m (309.00 ft). Span: 5.50 m (18.00 ft).