中国从1958年开始复合固体推进剂火箭发动机的探索和研制工作。
China has undertaken to research and develop composite solid propellant rocket motors since 1958.
介绍了固体火箭发动机壳体裙的结构、用途及采用复合材料裙体的优点。
Both the structure and the use of solid rocket motor case skirts are presented. The advantages of the composite skirts are introduced.
VARTM工艺成型的固体火箭发动机壳体复合材料连接裙段构件纤维体积含量较低，复合材料力学性能不佳。
The composite skirts for solid rocket motor shells fabricated by VARTM (VacuumAssisted Resin Transfer Molding) had poor mechanical properties because the fiber volume fraction was very small.
直径300毫米的固体推进剂火箭发动机采用了复合推进剂端燃药柱。
The 300mm diameter solid propellant rocket motor employs a composite propellant end burning grain.
高速旋转试验台是模拟底排一火箭复合增程炮弹内的固体火箭发动机实验设计的。
The estimation of extend-range solid rocket motor in high speed rotation is a key technique.
高速旋转试验台是模拟底排一火箭复合增程炮弹内的固体火箭发动机实验设计的。
The estimation of extend-range solid rocket motor in high speed rotation is a key technique.
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