侧喷流直接力控制的运载器姿态稳定问题研究  

Research on Attitude Stabilization Problem for Control System with Lateral Jet

作　　者：孙平[1] 刘昆[1] 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《宇航学报》2009年第5期1902-1906,共5页Journal of Astronautics

摘　　要：利用侧向喷流对小型固体运载器进行姿态稳定控制具有降低运载器成本和提高起飞质量的优点。研究具有开关型姿态控制发动机的运载器的姿态稳定问题。首先分析了系统的特点和控制器设计问题,建立了控制模型。然后应用描述函数对系统的非线性特性进行伪线性化,通过几何方法分析Nyqu ist图中系统线性部分与非线性部分描述函数的关系实现鲁棒极限环控制器,给出控制器形式和参数范围,最后针对时域、频域综合指标,运用精英非支配解排序遗传算法对控制器参数进行优化。仿真结果表明系统具有良好的动态、稳态性能,控制器具有很强的鲁棒性。Launch vehicles with lateral thrust have the merits of low cost and higher available load. This paper studied attitude stabilization problem for launch vehicles with on-off actuators. At first, the characteristics and the main control problem for the system were analyzed, and the control model was established. Then the nonlinear element was quasi-linearized via a Describing Function （DF） approach and the design of robust limit cycle controller was realized by shaping the loop in the Nyquist plot. After that, a multi-objective optimization problem involving time-domain and frequency-domain objectives was presented. The solutions were found using the elitist non-dominated GA （ NSGA-II）. The simulation results show that the closed loop system attains high dynamic performance and steady state performance and the controller has excellent robustness performance.

关 键 词：描述函数 鲁棒极限环 多目标优化 姿态稳定 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]