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完成了使用碳纤维增强环氧树脂壳体和少烟、含硝铵复合推进剂的空空导弹火箭发动机的设计验证计划。介绍了包括材料选择和固定金属部件的方法在内的发动机壳体结构设计。完成了包括环境和操纵破坏试验在内的发动机壳体结构试验。对于整个发动机，进行了隔热、粘接、推进剂性能、药柱设计和发动机壳体性能的设计验证。试验了六种不同飞行质量的发动机，项目包括极限温度下点火、环境载荷、在具有发射弯曲力矩、老化和后力脉动的情况下点火。还使用两种发动机进行钝感弹药试验，即快速自燃和撞击试验。
Completed the design verification program of the air-to-air missile rocket engine using carbon fiber reinforced epoxy shell and less smoke, ammonium nitrate-containing composite propellant. The structural design of the engine housing, including material selection and method of fixing metal parts, is introduced. Complete the engine casing structure test, including environmental and handling damage tests. For the entire engine, design verification of thermal insulation, bonding, propellant performance, pellet design, and engine housing performance was performed. Six engines of different flight qualities were tested. The project included ignition at ultimate temperature, ambient loading, and ignition with launch bending moments, aging and aft force pulsation. Two engines were also used for the insensitive ammunition test, namely rapid spontaneous combustion and impact test.