H2O2/Pentaborane
Propellant
Original archive entry. The text, images and links below are kept as they were written.
H2O2/Pentaborane propellant. Hydrogen peroxide in combination with pentaborane was studied or developed by the Russians in 1965-1975 as a propellant. Although potentially high performance and high density, it did not find application in any production engines. Both hydrogen peroxide and pentaborane were 'bad actors' - reacting explosively with minor impurities in the propellant systems.
Oxidizer: H2O2. Fuel: Pentaborane. Oxidizer Density: 1.440 g/cc. Oxidizer Freezing Point: -1 deg C. Oxidizer Boiling Point: 150 deg C. Fuel Density: 0.622 g/cc. Fuel Freezing Point: -47 deg C. Fuel Boiling Point: 62 deg C.
Subtopics
RD-502 Glushko H2O2/Pentaborane rocket engine. Experimental upper stage engine. Developed 1960-66. Experimental upper stage engine. Program stopped due to toxicity of propellants. Intended for Proton upper stage. First flight 1966.
Related
- Engines
- RD-502