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本文根据弹性力学和气体动力学导出了计算固体火箭发动机自由装填装药临界弹性模量的基本公式及其计算方法,该方法对推进剂是可压缩的或是不可压缩的均适用。
Based on the theories of elasticity and gas dynamics, this paper derives the basic formula for calculating the critical elastic modulus of solid rocket motor and its calculation method, which is applicable to both compressible and incompressible propellants.