The effect on circumgyration of carbon grain and the ablation of nose-tip during re-entry of stratagem missile is analyzed according to thermal transfer theory, thermo-aerodynamics and N-S equation.
根据气动热力学、传热传质学、N - S方程，分析了战略导弹再入时端头帽烧蚀与碳颗粒的旋转效应，研究结果表明碳颗粒的旋转有利于防热。
At the same time, the effect of stress path circumgyration on shear modulus decreases gradually along with the increase of shear strain.
同时由应力路径旋转对模量的影响也随着剪切应变的增加而逐渐衰减。
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