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RS-27
Part of LR79 Family
RS-27
RS-27
Credit: Boeing / Rocketdyne
Rocketdyne LOx/Kerosene rocket engine. Out of production. Consisted of RS2701A/B main engine, and twin LR101-NA-11 verniers. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher; replaced the MB-3. First flight 1972. It completed its Delta service on the 6000 model in 1992, then continued as part of the Atlas MA- 5A powerplant until the retirement of the Atlas.

Status: Out of production. Date: 1971. Number: 108 . Thrust: 1,023.00 kN (229,979 lbf). Unfuelled mass: 1,027 kg (2,264 lb). Specific impulse: 295 s. Specific impulse sea level: 264 s. Burn time: 274 s. Height: 3.63 m (11.90 ft). Diameter: 1.07 m (3.51 ft).

The RS - 27 powerplant comprises an RS2701A/B main engine, and twin LR101 - NA - 11 verniers. Introduced in 1974 on the McDonnell Douglas' Delta 2000 series launcher it replaced the MB - 3 as the main system for that launcher. It completed it's Delta service on the 6000 model in 1992. and continues in service as part of the Atlas MA- 5A powerplant. First Flown: January 18th, 1974 on Delta 100/Skynet 2A. Flown: 107 Delta plus 8 Atlas to the end of 1993. Mounting: gimbaled-mounted for pitch/yaw control with gimbaled verniers for roll control. Engine Cycle: gas generator. Oxidizer: liquid oxygen at 250 kg/sec. Fuel: RP-1 hydrocarbon at 111 kg/sec. Mixture Ratio: 2.245:1. Oxidizer Turbopump: 1900 kW, 6784 rpm (7085 rpm at altitude), 70 atm discharge Pressure: Fuel Turbopump: 1289 kW, 70 atm discharge Pressure. Thrust: 971 kN sea level/1023 kN vacuum. Thrust Chamber Length: 219 cm (234 cm). Thrust Chamber Materials: 347 CRES austenitic stainless steel. Thrust Chamber Cooling: regenerative, two passes of fuel through 292 tubes. Combustion Chamber Pressure: 48 atm at injector end. Combustion Chamber Temperature: 3315 Celsius. Combustion Chamber Materials: 347 CRES austenitic stainless steel. Combustion Chamber Cooling: same as thrust chamber. Combustion Chamber Ignition: hypergolic fluid cartridge enclosed in burst diaphragms. Verniers: each LR101-NA-11 at 21.8 kg mass, 4.63/5.30 kN sea level/vac thrust, 209/246 sec sea level/vac Isp, 1.8 mixture ratio, 5.6 expansion ratio(9.8 cm exit diameter), 283 sec burn time. Designed for booster applications. Gas generator, pump-fed.

Thrust (sl): 915.500 kN (205,813 lbf). Thrust (sl): 93,357 kgf. Engine: 1,027 kg (2,264 lb). Chamber Pressure: 49.00 bar. Area Ratio: 8. Propellant Formulation: Lox/RP-1. Thrust to Weight Ratio: 102.389863547758. Oxidizer to Fuel Ratio: 2.245. Coefficient of Thrust vacuum: 1.79872892263639. Coefficient of Thrust sea level: 1.59872892263639.



Country: USA. Launch Vehicles: N-1, N-2, Delta 1000, Delta 4000, Delta 5000, Delta 2000, Delta 3000. Propellants: Lox/Kerosene. Stages: Delta Thor RS27, Delta Thor ELT. Agency: Rocketdyne. Bibliography: 225, 7534.

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