American orbital launch vehicle. Proposed Earth-to-Orbit Segment booster for Andrews CEV architecture. Consisted of an Atlas V core, two Zenit-2 booster strap-ons, and a new-development Lox/LH2 upper stage.
The new expendable Lox/LH2 upper stage would require development of a new RL-X engine. The stage would be 6.5 m in diameter and 17.6 m long, with a gross mass of 283,793 kg and a dry mass of 14,402 kg. All stages would be only partially fuelled for delivery of a low-earth orbit payload of 40 tonnes, with a gross lift-off mass of 865,950 kg in that configuration.
LEO Payload: 40,000 kg (88,000 lb) to a 300 km orbit at 28.00 degrees. Payload: 22,000 kg (48,000 lb) to a translunar trajectory. Launch Price $: 240.000 million in 2005 dollars.
Status: Design 2005.
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Gross mass: 1,213,618 kg (2,675,569 lb).
Payload: 40,000 kg (88,000 lb).
Height: 84.70 m (277.80 ft).
Diameter: 5.40 m (17.70 ft).
Span: 17.00 m (55.00 ft).
Apogee: 300 km (180 mi).
CEV Andrews American manned spacecraft. Study 2005. The Andrews Crew Exploration Vehicle (CEV) design adopted NASA's preferred Apollo CM re-entry vehicle shape, but combined it with a mission module crew cabin to minimize the CEV's mass. More...
Atlas V The Atlas V launch vehicle system was a completely new design that succeeded the earlier Atlas series. Atlas V vehicles were based on the 3.8-m (12.5-ft) diameter Common Core Booster (CCB) powered by a single Russian RD-180 engine. These could be clustered together, and complemented by a Centaur upper stage, and up to five solid rocket boosters, to achieve a wide range of performance. More...
Associated Manufacturers and Agencies
Andrews American manufacturer of rockets and spacecraft. Andrews, USA. More...
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