BERYLLIZINE PROPELLANT PERFORMANCE EVALUATION.
Abstract
This report presents the results of the effort conducted under the Air Force Rocket Propulsion Laboratory in-house program, Project Pinnacle. Experimental tests were conducted with the fuels alumizine and beryllizine, and the oxidizers N2O4 and 98% H2O2 at a thrust level of 5000 lbs and at chamber pressures of 500 to 1300 psia to determine the combustion characteristics and thrust chamber performances of these metallized fuels. Initial effort' used N2O4/alumizine 33 to evaluate injector design, hardware durability and performance. Later, the program evaluated the effects of chamber pressure, metal loading, characteristic lengths, and injector design on the performance of the nitrogen tetroxide/beryllizine system. A very limited number of tests were conducted with the hydrogen peroxide/alumizine and beryllizine system to evaluate injector performance. The fuels used in these investigations were prototype formulations made with state-of-the-art materials and processes. Initial testing was conducted with gelled fuels; however, due to the difficulties encountered in the formulation of a beryllizine gel, a majority of the test firings were made with an emulsified fuel. These fuels were not suitable for long-term storage due to excessive gas evolution rates and mechanical instability. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1968
- Accession Number
- AD0393497
Entities
People
- Albert Tatkenhorst