基于非线性优化控制理论的民用飞机失速恢复控制  

Aircraft Stall Recovery of Civil Aircraft Based on the Nonlinear Optimal Control Theory

作　　者：王爽[1] 詹浩[1] 孔祥骏 

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国民航科学技术研究院航空安全技术中心,北京100028

出　　处：《航空工程进展》2014年第2期251-256,268,共7页Advances in Aeronautical Science and Engineering

基　　金：国家自然科学基金-民航联合基金(61039002)

摘　　要：民用飞机在进入大迎角浅失速后,气动力会出现滞环、陡降等强非线性现象,航迹也变得不稳定。为解决上述问题,利用分支分析方法分析飞机临近失速区时的控制特点,指出其振荡区域,多配平点等;根据非线性最优化控制理论,设计大迎角失速区的自动恢复控制器,用Galerkin近似算法,计算次优控制器参数,并对飞机下降航迹的进入失速和恢复进行仿真验证。结果表明:控制器可以很好地控制飞机改出浅失速状态,恢复正常航迹。When the civil aircraft fall into the area of stall angle of attacks, air force will show hysteresis, steep drop and other strong nonlinear characteristics, and the track becomes unstable. To solve the problem, bifurca- tion analysis method is applied to analyze the control characteristics of aircraft near stall region, and its oscilla- tion region, multi-equilibrium points are obtained. Based on the nonlinear optimal control theory, aircraft stall recovery at high angle of attack is designed. With the Galerkin algorithm, the suboptimal controller parameters are claculated, and the simulation of the aircraft falling into stall and recovery when descending is verified. The results show that the controller can be well controlled to recovery from the stall and resume normal track.

关 键 词：民用飞机 非线性 最优化控制 失速 GALERKIN 

分 类 号：V249[航空宇航科学与技术—飞行器设计]