MON/MMH
Propellant
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MON/MMH propellant. No rocket engines went into production using this propellant combination.
Optimum Oxidizer to Fuel Ratio: 2.27. Temperature of Combustion: 3,455 deg K. Density: 1.17 g/cc. Oxidizer Density: 1.370 g/cc. Fuel Density: 0.880 g/cc. Fuel Freezing Point: -52 deg C. Fuel Boiling Point: 87 deg C.
Subtopics
GSat Indian communications satellite bus. First launch 2001.04.18.
Insat 3 Indian communications satellite bus. The multipurpose satellite design provided telecommunications, television broadcasting, meteorological and search and rescue services. Communication, Meteorology satellite built by ISRO for Insat, India. Launched 2003. Used the Insat-2/-3 Bus bus.