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Cargo LV Stage 2
LOx/LH2 propellant rocket stage. Trans-lunar injection stage proposed by NASA for Project Constellation exploration of moon and Mars. It would use shuttle external tank tooling. All masses estimated.

Status: Study 2005. Thrust: 2,442.07 kN (548,999 lbf). Gross mass: 227,036 kg (500,528 lb). Unfuelled mass: 19,343 kg (42,644 lb). Specific impulse: 451 s. Burn time: 370 s. Height: 22.74 m (74.60 ft). Diameter: 8.40 m (27.50 ft). Span: 8.40 m (27.50 ft).

No Engines: 2.



Subtopics

CLV Stage 2 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.

Country: USA. Engines: J-2S. Propellants: Lox/LH2.

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