摘要
根据现代控制理论，对多输入多输出气动伺服弹性系统的鲁棒稳定性进行研究．分别采用小增益原理和最小奇异值理论两种方法，对涉及飞行器互相耦合的横滚和偏航回路的控制系统进行分析，得出了气动伺服弹性系统抵抗建模误差、保持鲁棒稳定的范围．这两种方法都分别给出了稳定性判据，根据判据可以确定其鲁棒稳定性（或稳定裕度）．作为系统扰动的表达形式，文中还对系统不确定性矩阵进行了描述．算例是在某ＡＣＴ战斗机的计算模型上完成的，两种方法的计算结果取得了一致．
Research on a multiinput-multioutput(MIMO) aeroservoelastic (ASE) system was presented on the basis of modern control theory. The small gain theory and minimal singular value theory were applied to the control system which was equipped with the coupled roll and yaw loop. The stability scope of the aeroservoelastic system to resisted the model error was obtained. Both the methods gave the stability criteria respectively and according to the criteria the robust stability(or stability margin) could be defined. As an expression of turbulence the system uncertainty matrix was described. The above two methods result in the same result on the model of an ACT combat airplane.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
1999年第4期447-450,共4页
Journal of Beijing University of Aeronautics and Astronautics
基金
航空科学基金
