TRW MON/Hydrazine rocket engine. 0.454 kN. In Production. Isp=314s. First Flight: April 1991. Burn Time 24,000 sec total, with a 3600 sec maximum single burn. Hypergolic ignition via 28 V current to an on/off bi-propellant torque motor valve.
Mounting: fixed. Engine Cycle: pressure-fed at 15 atm. Oxidizer: MON 3-flow rate at 0.076 kg/sec. Fuel: high purity hydrazine-flow rate at 0.071 kg/sec. O/F Ratio: 1.070:1. Cooling Method: radiation.
Engine: 4.80 kg (10.50 lb). Chamber Pressure: 7.00 bar. Area Ratio: 204. Thrust to Weight Ratio: 9.58.
Status: In Production.
More... - Chronology...
Unfuelled mass: 4.80 kg (10.50 lb).
Height: 0.56 m (1.84 ft).
Diameter: 0.30 m (0.99 ft).
Thrust: 454 N (102 lbf).
Specific impulse: 315 s.
Burn time: 3,600 s.
Associated Manufacturers and Agencies
TRW American manufacturer of rockets, spacecraft, and rocket engines. TRW Corporation, Redondo Beach, CA, USA. More...
MON/Hydrazine Mixed Oxides of Nitrogen - Nitric oxide (NO) is a low-boiling cryogenic gas. Both the liquid and the solid are blue. Solutions of NO in nitrogen tetroxide sharply depress the freezing point of the high-melting oxidiser. The mechanism of depression is believed to involve the formation of N2O3, which is soluble in nitrogen tetroxide. Solutions are called mixed oxides of nitrogen (MON), and have been used as oxidisers for liquid-rocket engines. Various concentrations have been considered. However, the high vapour pressure of MON limits the concentration of NO in N2O4 to about 30 per cent. Aside from the high vapour pressure of MON, the material is quite similar to nitrogen tetroxide. Hydrazine (N2H4) found early use as a fuel, but it was quickly replaced by UDMH. It is still used as a monopropellant for satellite station-keeping motors. More...
Home - Browse - Contact
© / Conditions for Use