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Engine Model: ATCRE. Propellants: Lox/LH2. Thrust(vac): 1,280.000 kN (287,750 lbf). Thrust(sl): 1,068.400 kN (240,186 lbf). Isp: 490 sec. Isp (sea level): 409 sec. Burn time: 298 sec. Chambers: 1. Chamber Pressure: 282.00 bar. Country: Germany. Status: Study 1985.
ATCRE used on Rocket Stages
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