考虑推力损失的运载火箭主动段容错控制
2024,46(4):54-62
谢昌霖
国防科技大学 空天科学学院, 湖南 长沙 410073，xiechanglin96@126.com
杨述明
国防科技大学 空天科学学院, 湖南 长沙 410073
程玉强
国防科技大学 空天科学学院, 湖南 长沙 410073
国防科技大学 空天科学学院, 湖南 长沙 410073，xiechanglin96@126.com
杨述明
国防科技大学 空天科学学院, 湖南 长沙 410073
程玉强
国防科技大学 空天科学学院, 湖南 长沙 410073
摘要：
运载火箭上升段易出现推力下降等动力系统故障,传统的控制方法在干扰性较大场合难以满足高精度、高稳定的控制需求。本文进行了运载火箭自适应增广控制与模糊PD控制方法的研究,并分析两者的控制特性；提出一种基于模糊规则的动态切换控制算法,通过计算自适应PD控制与模糊PD控制的输出量加权,得到系统的最优控制方案；将控制力矩重构与动态切换控制算法结合,进行火箭容错控制研究。结果表明,基于模糊规则的动态切换控制算法能有效提高姿态控制品质,相比于其他控制方法,偏航角最大偏差减小20%以上,系统响应时间至少快15%,且控制过程中未出现振荡。
运载火箭上升段易出现推力下降等动力系统故障,传统的控制方法在干扰性较大场合难以满足高精度、高稳定的控制需求。本文进行了运载火箭自适应增广控制与模糊PD控制方法的研究,并分析两者的控制特性；提出一种基于模糊规则的动态切换控制算法,通过计算自适应PD控制与模糊PD控制的输出量加权,得到系统的最优控制方案；将控制力矩重构与动态切换控制算法结合,进行火箭容错控制研究。结果表明,基于模糊规则的动态切换控制算法能有效提高姿态控制品质,相比于其他控制方法,偏航角最大偏差减小20%以上,系统响应时间至少快15%,且控制过程中未出现振荡。
基金项目：
国家自然科学基金资助项目(51206181)
国家自然科学基金资助项目(51206181)
Fault tolerant control of launch vehicle boost phase considering thrust loss
XIE Changlin
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,xiechanglin96@126.com
YANG Shuming
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
CHENG Yuqiang
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China,xiechanglin96@126.com
YANG Shuming
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
CHENG Yuqiang
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha 410073, China
Abstract：
The launch vehicle is prone to power system faults such as thrust drop in the ascending stage, and the traditional control method is difficult to meet the requirements of high precision and high stability control in the case of large interference. In this research, the adaptive augmentation control and fuzzy PD control of launch vehicle were studied, and their control characteristics were analyzed. A dynamic switching control algorithm based on fuzzy rules was proposed, and by calculating the output weight of adaptive PD control and fuzzy PD control, the optimal control scheme of the system was obtained. The control torque reconstruction and the dynamic switching control algorithm were combined to carry out fault-tolerant control research. The results show that the dynamic switching control algorithm based on fuzzy rules can effectively improve the attitude control quality. Compared with other control methods, the maximum yaw angle deviation is reduced by more than 20%, the system response time is at least 15% faster, and there is no oscillation in the control process.
The launch vehicle is prone to power system faults such as thrust drop in the ascending stage, and the traditional control method is difficult to meet the requirements of high precision and high stability control in the case of large interference. In this research, the adaptive augmentation control and fuzzy PD control of launch vehicle were studied, and their control characteristics were analyzed. A dynamic switching control algorithm based on fuzzy rules was proposed, and by calculating the output weight of adaptive PD control and fuzzy PD control, the optimal control scheme of the system was obtained. The control torque reconstruction and the dynamic switching control algorithm were combined to carry out fault-tolerant control research. The results show that the dynamic switching control algorithm based on fuzzy rules can effectively improve the attitude control quality. Compared with other control methods, the maximum yaw angle deviation is reduced by more than 20%, the system response time is at least 15% faster, and there is no oscillation in the control process.
收稿日期：
2022-04-12
2022-04-12
