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.
本文设计的高速旋转固体火箭发动机内置动态参数记录仪，着重解决火箭发动机在高速旋转状态下压力测试问题。
High speed rotation solid propellant rocket motor recording apparatus which we designed is going to resolve pressure testing of rocket motor in high speed rotation.
本文从实验和数值模拟两方面，对静止和旋转增程固体火箭发动机补燃室燃烧流场进行了研究。
The combustion flow field in secondary combustion chamber for static and spinning extended solid rocket ramjet were studied experimentally and numerically in detail.
高速旋转试验台是模拟底排一火箭复合增程炮弹内的固体火箭发动机实验设计的。
The estimation of extend-range solid rocket motor in high speed rotation is a key technique.
高速旋转试验台是模拟底排一火箭复合增程炮弹内的固体火箭发动机实验设计的。
The estimation of extend-range solid rocket motor in high speed rotation is a key technique.
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