Engine Model: ATE. Propellants: N2O4/MMH. Thrust(vac): 20.000 kN (4,496 lbf). Isp: 347 sec. Mass Engine: 58 kg (127 lb). Diameter: 0.76 m (2.51 ft). Length: 1.72 m (5.64 ft). Chambers: 1. Chamber Pressure: 88.80 bar. Area Ratio: 400.00. Oxidizer to Fuel Ratio: 1.86. Thrust to Weight Ratio: 35.15. Country: USA. Status: Developed 1990's. Advance technology engine for maneuvering stages.