固体发动机飞行性能分析与重构

Flight performance analysis and reconstruction of SRM

在固体发动机研制过程中,发现利用飞行遥测参数计算的某末级发动机性能结果与基于地面试验的内弹道模型得到的结果存在偏差,这一偏差会影响发动机性能评定乃至火箭射程。对国内外固体火箭发动机飞行性能分析和重构方法及主要的结果进行了分析,对于特定的发动机需固化一种飞行性能重构分析方法,为提高发动机性能重构分析的精度,需要提高发动机喷管喉径烧蚀规律的预示水平,同时需要考虑飞行过程中消极质量变化以及沉积对发动机比冲的影响。最后,对发动机飞行性能分析重构后续需要着重开展的研究提出了建议。

The literature on Solid Rocket Motor （SRM） reveals that the performance of an upper SRM calculated by using remote flight test data is significantly different from that by using the internal ballistic model based on ground tests.Such difference has great effect on SRM performance evaluation and the rocket range.In the paper,the available literature data on flight performance analysis and reconstruction of SRM have been summarized.Moreover, these methods are analyzed and compared.For a certain motor, the same method should be used.The erosion of the nozzle,the change of the negative weight during the flight and the deposition of the motor will affect the flight performance of the motor.Finally ,some relevant key research tasks needed in the near future are sug- gested.