Ares Stage 2 home
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Model: CLV Stage 2. Gross Mass: 160,000 kg (350,000 lb). Empty Mass: 16,000 kg (35,000 lb). Thrust (vac): 2,333.000 kN (524,479 lbf). Isp: 465 sec. Burn time: 270 sec. Propellants: Lox/LH2. Diameter: 5.50 m (18.00 ft). Span: 5.50 m (18.00 ft). Length: 32.00 m (104.00 ft). Country: USA. No Engines: 1. Motor: SSME. Status: Study 2005.

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.

Model: Cargo LV Stage 2. Gross Mass: 227,036 kg (500,528 lb). Empty Mass: 19,343 kg (42,644 lb). Thrust (vac): 2,442.071 kN (548,999 lbf). Isp: 451 sec. Burn time: 370 sec. Propellants: Lox/LH2. Diameter: 8.40 m (27.50 ft). Span: 8.40 m (27.50 ft). Length: 22.74 m (74.60 ft). Country: USA. No Engines: 2. Motor: J-2S. Status: Study 2005.

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.

Model: Ares Stage 2. Gross Mass: 172,000 kg (379,000 lb). Empty Mass: 13,200 kg (29,100 lb). Thrust (vac): 1,113.000 kN (250,212 lbf). Isp: 465 sec. Burn time: 640 sec. Propellants: Lox/LH2. Diameter: 10.00 m (32.00 ft). Span: 10.00 m (32.00 ft). Length: 16.00 m (52.00 ft). Country: USA. No Engines: 1. Status: In development. First Flight: 1991.

Second stage proposed later in design stage by NASA for launch of CEV into low earth orbit. All masses estimated.

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