固体火箭发动机径向泄压过程中燃速对内弹道预示的影响  

Effects of burning rate on interior ballistic prediction of SRM during radial decompression

作　　者：刘春红[1] 余贞勇[1] 胡乃合[1] 

机构地区：[1]中国航天科技集团公司四院,西安710025

出　　处：《固体火箭技术》2006年第4期254-256,265,共4页Journal of Solid Rocket Technology

摘　　要：用参数辨识法对某径向泄压固体火箭发动机的瞬态参数进行了辨识,得出了该发动机泄压过程的瞬态燃速公式和泄压孔流量系数。利用零维瞬态内弹道模型和辨识所得参数,对另一台发动机的径向泄压过程进行了预示,预示结果与发动机实测数据吻合良好,证明了该方法的正确性和适用性。在此基础上,分析了燃速对径向泄压过程内弹道预示的影响。结果显示,在发动机径向泄压过程中,采用瞬态燃速更能反映发动机的实际工作过程。The transient parameters of a solid rocket motor during radial decompression were determined by identification techniques, and the formula for transient burning rate and discharge coefficient of decompression pore were obtained. Also, the radial decompression process of another SRM was predicted by means of the 0-D interior ballistic model and identification parameters, and the results were consistent with the measured data. This method is proved to be correct and applicable. On the basis of the results, the effects of burning rate on the interior ballistic properties were analyzed. The results show that the transient burning rate can reflect actual working process of the motor during radial decompression.

关 键 词：固体火箭发动机 瞬态参数辨识 内弹道 燃速 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]