提出了一种旋转固体火箭发动机的内弹道计算方法。
A method of internal ballistic calculation for spinning solid rocket motor has been presented in this paper.
本文的研究成果和结论对旋转固体火箭发动机飞行器的章动不稳定性问题具有十分重要的意义和实用价值。
The results achieved and the conclusions drawn in this thesis are of great importance and applicable in the nutation instability phenomenon of solid rocket motor spacecraft.
因此对旋转固体火箭发动机尾部点火过程的数值模拟中，需要考虑点火器生成的高温粒子对点火过程的影响。
So the hot particles produced by the igniter should be considered in the numerical simulation of the ignition of the rotating RSM with the aft-end igniter.
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