Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

---

R-1E engine

---

R-1E Credit: Aerojet Redmond

AKA: R-1E. Status: In Production. Number: 1 . Thrust: 110 N (20 lbf). Unfuelled mass: 3.70 kg (8.10 lb). Specific impulse: 280 s. Burn time: 1,500 s. Height: 0.28 m (0.92 ft). Diameter: 0.15 m (0.50 ft).

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.

Engine: 3.70 kg (8.10 lb). Chamber Pressure: 7.40 bar. Area Ratio: 26. Thrust to Weight Ratio: 3.02.