固体火箭发动机非线性燃烧不稳定分析方法

Nonlinear combustion instability analysis method of solid rocket motor

基于预估非线性燃烧不稳定的能量守恒方法,结合燃烧室流动控制方程,推导了发动机压强振荡幅值和平均压强的非线性耦合方程,用于预测固体火箭发动机的非线性燃烧不稳定特征:压强振荡的极限振幅和平均压强上升。针对圆柱形装药内孔燃烧固体火箭发动机,建立了物理模型和数学模型,实现了非线性稳定性的数值计算,对Blomshield的脉冲试验发动机数据进行数值计算,与试验结果进行对比吻合较好,验证了模型和算法的可行性。对燃烧室半径、燃速等敏感性参数进行了分析,得到了这些参数对发动机稳定性的影响。

A nonlinear instability prediction method based on energy balance theory was derived to predict nonlinear combustion characteristics of solid rocket motor： limit cycle and DC shift. A cylindrical solid rocket motor was selected to construct the physical and mathematical model. Blomshield＇s stability testing was chosen to validate the model and calculation program. The calculation results agree well with the experimental data in a certain degree. The sensitivity of important parameters such as chamber radius and burning rate was analyzed to study their effects on the instability of the motor.