高过载条件下固体火箭发动机工作稳定性研究

Research on the Working Stabilization of Solid Rocket Motor Under High Overload

针对高过载条件下固体火箭发动机的燃烧特性,利用燃速方程编程计算,得出了过载条件下含铝复合推进剂燃速增加系数,分析了过载与燃速增大变化规律,并采用非均匀燃面计算方法模拟不同过载条件下发动机的内弹道性能,结果表明,过载对发动机内弹道性能影响不明显,但会影响特定部位燃速增大导致的装药偏烧,有必要加强该部位的热防护。

Based on the combustion characteristic of solid rocket motor under high overload , the data of the burning rate augmentation of the HTPB propellants on the overload is acquired by computing burn-ing rate equation, and the law of burning rate augmentation changed with overload is analyzed .The inter-nal ballistic performance under different overload is computed by the irregular burning surface calculation method.The result shows that, the overload has little effect on the internal ballistics performance , but could increase the burning rate of specific areas and lead to the grain burning eccentrically .it is necessary to strengthen heat safety design for these areas .