DEVELOPMENT OF HIGH-ENERGY METALLIZED PROPELLANTS.
Final rept. 1 May 65-31 Aug 66,
AEROJET-GENERAL CORP SACRAMENTO CA
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N2O4Beryllizine-21I and 98 H2O2Beryllizine-28II, were investigated in a 1000-lb thrust test assembly operated at 500-1100 psia chamber pressure to develop techniques for ignition and efficient combustion of the metal. Ignition was achieved by the use of an injector concept that involves a two-part design. Each of the two types of injectors designed for the investigations contained a central hot-core section within a second, peripheral injection area. By operating the hot-core at a high mixture ratio, the temperature of combustion of the oxidizer with the hydrazine in the fuel was high enough to ignite the suspended beryllium. The peripheral section of the injector was operated at such a mixture ratio as to produce an over-all ratio favorable to high efficiency of combustion. The flow properties of Beryllizine-21 were also investigated. Alumizine-43G was also examined for comparison purposes and the data show that these two fuels have similar flow properties. The chemical compatibility investigations showed that, in general, the purest beryllium powders were the most compatible with hydrazine. The impurities that were most suspect as sources of evolved gas were beryllium carbide and magnesium. By combining the use of the new gelling agents with the water-treatment of the beryllium powder, the formulation of chemically stable Beryllizine formulations was made possible.
- Rocket Propellants
- Liquid Rocket Propellants