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- W1551472008 abstract "Abstract : The objectives were to evaluate the effects of propellant corrosivity and blast tube contraction ratio on candidate nozzle materials in high chamber pressure rocket motor environments (3,000 and 3,500 psia). A total of 16 lightweight aft closures and nozzles were designed, fabricated, and test fired. High velocity blast tubes with contraction ratios of 2.0 and 1.3, respectively, were used on all nozzles. The effects of propellant flame temperature and corrosivity were evaluated by testing with both 18% and 5% aluminized, 88% solids loaded CTPB propellants. The effects of both cylindrical and keyhole port grain configurations also were evaluated. Conventional state-of-the-art phenolic, elastomeric, graphite materials were used." @default.
- W1551472008 created "2016-06-24" @default.
- W1551472008 creator A5027864254 @default.
- W1551472008 date "1974-06-17" @default.
- W1551472008 modified "2023-10-06" @default.
- W1551472008 title "High Chamber Pressure Blast Tube and Nozzle Material Evaluation. Volume 1" @default.
- W1551472008 doi "https://doi.org/10.21236/ad0780531" @default.
- W1551472008 hasPublicationYear "1974" @default.
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