1.前言作为火箭/冲压发动机固体燃料的组成,在第一篇报告中作了介绍。从经济性、制造安全性考虑,在金属燃料中选择了铝。为了在一次燃烧室保持自燃性,在采用过氯酸铵作氧化剂时,粘合剂与氧化剂的比为50/40,铝的添加量为50％。另外,用试制的含铝50％的推进剂对火箭/冲压发动机进行了模拟试验,得到了约900秒的比推力。 1. Introduction The composition of the rocket / ramjet solid fuel is described in the first report. In terms of economy and manufacturing safety, aluminum was selected as the metal fuel. In order to maintain self-ignitability in the primary combustion chamber, when ammonium perchlorate was used as an oxidant, the binder to oxidizer ratio was 50/40 and the amount of aluminum added was 50%. In addition, a rocket / ramjet engine was tested with a prototype propellant containing 50% aluminum and a specific thrust of about 900 seconds was obtained.