Effect of composition on combustion of solid propellants during a rapid pressure decrease
National Aeronautics and Space Administration, 1962 - Science - 13 pages
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30-percent-fine blend 70-percent-coarse adiabatic aluminized aluminum or ammonium ammonium perchlorate concentration ammonium perchlorate particle binder concentration binder type burning-rate exponent burning-rate exponent n bustion carboxylic monomer chamber gas mass chamber pressure 50 CHAMBER-PRESSURE DECAY Ciepluch Coarse ammonium perchlorate combus combustion luminosity copolymer of butadiene creased effect extinguish combustion F Aluminum flame temperature flame thickness gas temperature ground potassium fluoride heat conducted Lewis Research Center mass addition maximum time required microns nium perchlorate oxidizer particle percent ammonium perchlorate percent and extinguish perchlorate was increased polyurethane pounds per square powder pressure 50 percent pressure drop pressure transient propellant burning rate propellant components propellant composition propellant surface propellant-strand burning rate Propellants Containing pyrolysis rapid pressure decrease rate of mass rate of pressure reduce chamber pressure reference propellant replacing binder required to reduce Solid Propellant solid-propellant combustion square inch absolute surface temperature temperature during steady thermal conductivity Type Weight percent