| R-1E | ||
Designer: Marquardt. Propellants: N2O4/MMH. Thrust(vac): 110 N (20 lbf). Isp: 280 sec. Burn time: 1,500 sec. Mass Engine: 3.70 kg (8.10 lb). Diameter: 0.15 m (0.50 ft). Length: 0.28 m (0.92 ft). Chambers: 1. Chamber Pressure: 7.40 bar. Area Ratio: 26.00. Thrust to Weight Ratio: 3.02. Country: USA. Status: In Production. A 110 N hypergolic thruster was developed as the Space Shuttle Orbiter's vernier attitude control and orbit adjust thruster. There are six employed in conjunction with the 38 3870 N R-40 thrusters. Applications: Shuttle Orbiter Vernier, satellite orbit adjust. First Flown: April 1981 on Columbia. Length: 279 mm, 312 mm satellite version. Maximum Diameter: 15.2 cm satellite version, 14 cm Shuttle version. Mounting: fixed. Engine Cycle: pressure-fed at 15 atm (range 6.8-27.2 atm). Oxidizer: nitrogen tetroxide at 0.0256 kg/sec. Fuel: monomethyl hydrazine at 0.0354 kg/sec. Mixture Ratio(O/F): 1.65 (range 1-2.7). Thrust: 110 N (range 67-155.7 N). Combustion Chamber: single chamber. Expansion Ratio: min ratio of 26 with orthogonal and scarfed nozzles. Combustion Chamber Construction: made of silicide-coated columbium (niobium) and insulated for buried installation.. Ignition: started by electrical signal to on/off solenoid valve. Single doublet injector with hypergolic ignition.. Burn Time: min 82,000 secs demonstrated. 0.89 Ns min impulse bit. Bibliography and Further Reading
| ||
|
Contact us with any corrections, additions, or comments. Conditions for use of drawings, pictures, or other materials from this site.. To contact astronauts or cosmonauts. © Mark Wade, 1997 - 2007 except where otherwise noted. |
|
Encyclopedia Astronautica topic index 0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z |