固体火箭发动机不稳定燃烧的速度耦合模型的研究  

AN INVESTIGATION ON VELOCITY COUPLING MODEL FOR UNSTABLE COMBUSTION IN SOLID ROCKET MOTORS

作　　者：吕振中[1] 

机构地区：[1]北京航空航天大学宇航学院

出　　处：《推进技术》1995年第6期1-10,共10页Journal of Propulsion Technology

摘　　要：由分析固体火箭发动机的高频不稳定燃烧的振幅和频率变化的复杂性开始，通过调整参数，得到在燃烧前期（即振荡燃烧的诱发期）呈现较单纯频率的振荡燃烧。利用中止燃烧试验，得到反映前期振荡燃烧的速度幅分布的烧去肉厚分布．从而由实验证明了：实际的固体火箭发动机中的振荡燃烧诱发期的主频率，并不是基频，而是高次谐波的纵向振荡。又通过内弹道计算分析，建立了不稳定燃烧＂速度耦合＂的理论模型。The research started from analyzing amplitude and frequency changes ofhigh-frequency unstable combustion in the solid rocket motors,and simple-frequency vibration combustion characteristics in the primary period of combustion were obtained byadjusting parameters of the solid rocket motor.A profile of burned web,which indicatesthe velocity amplitude distribution of vibration combustion in primary period,was alsoacquired by tests with combustion interruption.These demonstrated that the main frequency in inducing period of vibrant combustion of the actual solid rocket motor was thelongitudinal vibration of high-order harmonic instead of fundamental frequency.Thenthe velocity coapling model of unstable combustion was set up through analysis and calculation of the interior ballistics.

关 键 词：固体推进剂 火箭发动机 燃烧稳定性 振荡燃烧 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]