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本报告论述了有关M-1试验场E试验区所使用的大型低温推进剂系统的分析研究与操作实践。该试验设施供M-1液氢/液氧发动机燃料和氧化剂涡轮泵组件冷流研制试验,是由航空喷气发动机通用公司AETRON分公司根据航宇局路易斯研究中心和航空喷气发动机通用公司液体火箭发动机试验站共同制定的标准而设计的。在设计工作中,冯·卡曼中心(属喷气通用公司)在热及应力分析方面给予了大力的支持。本报告的大部分涉及在冯·卡曼中心利用航空喷气发动机通用公司的热分析计算机进行的热和应力分析。报告的其余部分涉及液体火箭发动机试验站对加利福尼亚州萨克拉门托城的试验设施所取得的实际操作经验。
This report addresses the analytical research and operational practices of large cryogenic propellant systems used in the E-zone at M-1. The test facility for the M-1 liquid hydrogen / liquid oxygen engine fuel and oxidant turbo pump cold flow test developed by General Aviation Jet Engine Company AETRON branch according to NASA Louis Research Center and Jet Engine General Liquid Rocket Engine Test station jointly developed standards and design. In the design work, the von Karman Center (Jet General Company) gave strong support in the field of thermal and stress analysis. Much of this report relates to thermal and stress analysis at AVON Kaman using thermal analysis computers from Jet Engine General Motors. The remainder of the report relates to the hands-on experience of the liquid rocket engine test station at the test facility in Sacramento, California.