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针对固体火箭发动机的推力矢量控制系统的需求,分析了扰流片系统的工作原理,设计了圆弧型扰流片;根据扰流片的安装位置关系,推导了扰流片摆角与伸入喷管出口流场高度的关系式;对加载单个圆弧型扰流片的喷管三维流场进行数值模拟,得到扰流片产生气动力的大小随扰流片伸入流场高度的变化规律;并通过固体火箭发动机的点火试验,验证所设计的扰流片系统在阶跃响应和正弦加载下的动态特性。结果表明:扰流片推力矢量控制系统在最大偏转角度38°时,阶跃响应时间为55ms,最大偏差0.6°,超调量2.02%;偏转角8°时,正弦加载测得系统带宽10Hz。
According to the demand of the thrust vector control system of solid rocket motor, the working principle of the spoiler system is analyzed and the arc-type spoiler is designed. According to the installation position of the spoiler, the spoiler angle and extension The relationship between the flow field height and the height of the nozzle is obtained. The numerical simulation of the three-dimensional flow field of the nozzle with a single circular arc spoiler is carried out. The variation of the aerodynamic force The dynamic characteristics of the designed spoiler system under step response and sinusoidal loading were verified by the ignition test of solid rocket motor. The results show that the step response time is 55 ms, the maximum deviation is 0.6 ° and the overshoot is 2.02% when the spoiler thrust vector control system is at the maximum deflection angle of 38 °. When the deflection angle is 8 °, the system bandwidth is measured at 10 Hz.