运载火箭推力下降后的控制力矩重构分析  

Analysis on control torque reconstruction of launch vehicle after thrust drop

作　　者：程玉强[1] 崔孟瑜 谢昌霖 杨述明[1] CHEN Yuqiang;CUI Mengyu;XIE Changlin;YANG Shuming(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,湖南长沙410073

出　　处：《火箭推进》2023年第1期21-28,共8页Journal of Rocket Propulsion

摘　　要：针对现役捆绑火箭在飞行中发生推力突降的问题,提出了一种基于改进单纯形法的控制分配策略。利用故障前后火箭控制力矩相等的思想,将推力下降后火箭发动机摆角的重新分配问题转化为目标函数约束下的线性分配问题,通过改进单纯形法进行了有效求解。结果表明,偏航角在关机故障发生后可以迅速恢复至平衡状态,滚转角在小幅抖震后同样快速到达稳定,该方法可以有效地改善火箭突发推力下降后控制能力减弱的问题,并维持故障后火箭姿态的平稳,对运载火箭姿态重构研究具有理论意义与工程应用价值。Aiming at the problem of sudden thrust drop for active service strap-on rocket during flight,a control allocation method based on improved simplex method is proposed.Based on the idea that the control torque of the rocket is equal before and after the failure,the redistribution problem of rocket engine swing angle after thrust drop is transformed into a linear distribution problem under the constraint of objective function,which is effectively solved by the improved simplex method.The results show that the yaw angle can quickly return to the equilibrium state after the shutdown failure,and the roll angle can also quickly return to stability after a small buffeting.This algorithm can effectively improve the weakening of the control ability after the sudden thrust drop of the rocket engine,and maintain the stability of the rocket attitude after the failure.The research content has theoretical significance and engineering application value for the attitude reconstruction of launch vehicle.

关 键 词：推力下降 控制力矩 控制分配 改进单纯形法 姿态重构 

分 类 号：V249[航空宇航科学与技术—飞行器设计]