MON/Hydrazine
Propellant
Original archive entry. The text, images and links below are kept as they were written.
MON/Hydrazine propellant. Mixed Oxides of Hydrazine (N2H4) found early use as a fuel, but it was quickly replaced by UDMH.
Optimum Oxidizer to Fuel Ratio: 1.4. Temperature of Combustion: 3,325 deg K. Density: 1.19 g/cc. Oxidizer Density: 1.370 g/cc. Fuel Density: 1.008 g/cc. Fuel Freezing Point: 2.00 deg C. Fuel Boiling Point: 113 deg C.
Subtopics
- Dual Mode-Liquid Apogee Engine TRW MON/Hydrazine rocket engine. In Production. 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.