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.
本文采用大变形有限元方法进行纤维缠绕固体火箭发动机壳体的应力及爆破分析。
In this paper we employed the nonlinear finite element method to calculate the stress and bursting pressure of filament wound rocket motor case.
用于固体火箭发动机壳体和工业贮罐的纤维缠绕压力容器，爆破压强是重要的设计参数。
The burst pressure of filament wound pressure vessels which is applied to solid rocket motor case and gas tank in industry is an important design parameter.
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.
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.
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