MON/UDMH
Propellant
Original archive entry. The text, images and links below are kept as they were written.
MON/UDMH propellant. No rocket engines went into production using this propellant combination.
Optimum Oxidizer to Fuel Ratio: 2.72. Temperature of Combustion: 3,490 deg K. Density: 1.14 g/cc. Oxidizer Density: 1.370 g/cc. Fuel Density: 0.793 g/cc. Fuel Freezing Point: -57 deg C. Fuel Boiling Point: 63 deg C.
Subtopics
- MUT Rocketdyne MON/UDMH rocket engine. Satellite maneuvering motor. Developed 2005. New technology motor with improved thrust/weight ratio and use of mixed oxides of nitrogen oxidizer with a much lower freezing point than N2O4.
Related
- Engines
- MUT