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R-40A

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Status: In Production. Thrust: 3.87 kN (870 lbf). Unfuelled mass: 10 kg (23 lb). Specific impulse: 306 s. Height: 1.04 m (3.41 ft). Diameter: 0.52 m (1.70 ft).

This thruster was developed for Shuttle Orbiter orbit control. The vehicle carries 38 long scarf, short scarf, or no scarf configurations. Depending on the location. Applications: spacecraft orbital maneuvering, perigee kick engine. First Flown: April 1981 on the Columbia. Dry Mass: 10.25 kg. Length: 55.4 cm short scarf version, 103.9 cm for the long scarf, and 88.9 cm for the satellite version. with 100:1 Expansion Ratio: Maximum. Diameter: 30.9 cm long scarf version, and 51.8 cm for the satellite version with 100:1 Expansion Ratio: . Mounting : fixed . Engine Cycle: pressure-fed. Oxidizer: nitrogen tetroxide at 0.838 kg/sec at 16.4 atm. Fuel: MMH at 0.52 kg/sec at 16.4 atm. Mixture Ratio(O/F): 1.6. Thrust: 3870 N (range 3114 - 5338 N). Isp: 281 sec (306 sec for 120 expansion ratio). Expansion Ratio: 20 (40 - 150 available for satellite version). Exit Diameter: 267 mm (328 - 635 mm for satellite version). Chamber Pressure: 10.5 atm. Combustion Chamber: single chamber of silicide-coated columbium (niobium) with welded-on orthogonal and scarfed nozzle extension in same material with internal film cooling. Exterior insulated for buried installation. Started by electrical signal to on/off solenoid valve. Multiple doublet injector with hypergolic ignition.. Burn Time: max 500 sec for single burn, qualified to 15,319 sec life. 289 Ns min impulse bit..

Engine: 10 kg (23 lb). Chamber Pressure: 10.50 bar. Area Ratio: 100. Thrust to Weight Ratio: 38.43.