结合算例说明了该方法在固体火箭发动机结构完整性分析中的适用性。
Calculating examples are given to illustrate the application of the method on structure integral analysis of solid rocker motor.
根据航空发动机结构完整性大纲，对于断裂关键件必须进行损伤容限设计分析。
According to aeroengine structure integrity program, fracture critical components must be analysed with damage tolerance concept.
该文的结果对固体火箭发动机装药结构完整性分析计算有重要的实用价值。
The results of this paper are of practical significance to grain structural integrity analysis and computation of solid rocket engines.
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