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以火箭橇作为过载加载平台和回收载体,通过结构强度及振动模态仿真确定火箭橇系统结构,设计推力控制方案满足试验弹道要求,建立了固体发动机火箭橇地面过载模拟试验方法。在国内首次开展了全尺寸固体发动机火箭橇试验,橇体大于16g的航向过载持续时间约为2.258 s,满足设计要求,试验全程监测并采集到发动机压强及振动数据。被试发动机在过载条件下出现了与飞行试验相似的压强振荡特性,复现了导弹飞行过载诱发的固体发动机不稳定燃烧现象。
The rocket sled was used as overload loading platform and recovery carrier, the structure of rocket sled system was determined by structural strength and vibration modal simulation, and the thrust control scheme was designed to meet the requirements of test trajectory. A simulation test method for ground overloading of solid rocket sled was established. The first full scale solid rocket sled test was carried out in China. The duration of heading overloading greater than 16g was about 2.258 s, which meets the design requirements. During the test, the engine pressure and vibration data were collected and monitored. Under the condition of overload, the tested engine appeared the similar pressure oscillation characteristics as the flight test, which reflected the unstable combustion of the solid engine induced by the missile flight overload.