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CLV Stage 2
Part of Cargo LV Stage 2 Family
LOx/LH2 propellant rocket stage. Second stage originally proposed by Thiokol for launch of the CEV into low earth orbit. Also could be used as trans-Mars injection stage on the Cargo LV. Nominal single engine; alternatively 7 RL10-derived engines. All masses estimated.

Status: Study 2005. Thrust: 2,333.00 kN (524,479 lbf). Gross mass: 160,000 kg (350,000 lb). Unfuelled mass: 16,000 kg (35,000 lb). Specific impulse: 465 s. Burn time: 270 s. Height: 32.00 m (104.00 ft). Diameter: 5.50 m (18.00 ft). Span: 5.50 m (18.00 ft).



Country: USA. Engines: SSME. Propellants: Lox/LH2.

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