高能固体火箭发动机冲击燃烧特性研究

为研究高能固体火箭发动机冲击燃烧特性，采用火箭撬平台作为加载装置对高能发动机施加冲击载荷，通过调节火箭撬速度获得不同速度下高能发动机的宏观反应特性；采用热力耦合计算模型对试验过程进行仿真，仿真中考虑推进剂在应力作用下温升引起的自热反应热源，通过计算发动机撞击靶板过程中推进剂内温度变化情况，分析推进剂反应的剧烈程度，判断发动机的反应特性，获得发动机的反应机理. 研究表明高能发动机以不低于100 m/s速度撞击靶板推进剂均会发生点火，点火位置位于发动机内孔；随着撞击速度的增加，点火延迟时间减小.

Shock-Combustion Performance of High Energy Solid Rocket Motor

In order to study the shock-combustion performance of the solid rocket motor, the sled platform as loading device was used to apply shock load to the high energy solid rocket motor, regulated the velocity of the sled to obtain the macroscopic reactive characteristics of the high energy rocket shock combustion. The experiment process was simulated by means of the thermo-mechanical coupling calculation mode, which considering the propellant self-heated reaction heat source aroused by temperature rised under stress effection. Through calculating temperature change of the propellant when the motor struck target board, the action severe degree of the propellant was analysed, the reactive characteristics of solid rocket motor was judged and the reaction mechanism was obtained. The result shows that the propellant will be ignited when the striking velocity larger then 100 m/s, the ignition position occurs on the bore of the motor, the ignition delay time reduces with the increase of the striking velocity.