Lox/Hydyne
Propellant
Original archive entry. The text, images and links below are kept as they were written.
Credit: NASA
Lox/Hydyne propellant. Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidizer for large space launchers.Hydyne was a propellant blend pushed rather vigorously by the Redstone arsenal in the late 1950's, but it found little application. Hydyne was a 60 per cent, by weight, mixture of UDMH and 40 weight percent diethyltrianine (DETA).
Optimum Oxidizer to Fuel Ratio: 1.73. Temperature of Combustion: 3,585 deg K. Density: 1.02 g/cc. Oxidizer Density: 1.140 g/cc. Oxidizer Freezing Point: -219 deg C. Oxidizer Boiling Point: -183 deg C. Fuel Density: 0.860 g/cc. Fuel Freezing Point: -84 deg C. Fuel Boiling Point: 64 deg C.
Subtopics
A-7 Rocketdyne LOx/Hydyne rocket engine. Out of Production. Version of Redstone engine for Jupiter-C test vehicle, with Hydyne fuel and 140 seconds burn time. Flew 1956-1959. Gas generator, pump-fed. Thrust 370 kN at sea level.
Jupiter C stage LOx/Hydyne propellant rocket stage. Redstone missile, stretched, modified with different propellants to serve as first stage of IRBM nose cone/orbital test vehicle.
Related
- Engines
- A-7
- Stages
- Jupiter C stage