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本文报导一种航天发动机的高空模拟点火试验。这种发动机综合利用了几种先进技术:90%固体燃料的端羟基聚丁二烯/铝粉/过氯酸铵/奥克托金推进剂;在凯夫拉壳体内的头端满装药;无支撑的整体喉部和收敛段入口;特轻的喷管和用充气膨胀的作动筒展开的可延伸出口锥。这次试验结束了法国欧洲动力公司和美国联合工艺公司化学系统分部之间为期两年的分工协作的研究和试制工作。所达到的比冲值被认为是复合推进剂在样机发动机中的一个最高记录。
This article reports a high-altitude simulated ignition test of a space engine. This engine utilizes several advanced technologies: Hydroxy terminated polybutadiene / aluminum powder / ammonium perchlorate / octoxonium propane at 90% solid fuel; full charge at Kevlar housing ; An unsupported monolithic throat and convergent section inlet; a very lightweight nozzle and an extendable exit cone that expands with an inflated ram. The trial ended the two-year division of labor collaboration between French-European power company and United Technologies Corp.’s systems division. The specific impulse achieved is considered to be one of the highest records of composite propellants in prototype engines.