高超声速飞行器再入段滚转控制及鲁棒性分析  

Roll Control and Robustness Analysis for Hypersonic Vehicle in Reentry Phase

作　　者：刘军[1] 黄一敏[1] 孙春贞[1] 尹亮亮[1] 

机构地区：[1]南京航空航天大学,南京210016

出　　处：《电光与控制》2014年第7期81-85,共5页Electronics Optics & Control

基　　金：基本科研业务费专项研究基金(56XZA12008)

摘　　要：高超声速飞行器再入段保持大迎角下滑过程中,航向失稳、荷兰滚发散、副翼操纵反效,为保证大迎角再入段飞行安全需要研究大迎角下滚转控制。针对大迎角下副翼操纵反效问题,提出了"改善LCDP的副翼控制滚转"与"方向舵控制滚转"两种控制策略,并利用结构奇异值快速分析两种滚转控制策略的鲁棒性,最后通过仿真对比两种滚转控制策略的控制品质与鲁棒性。仿真结果表明,标称状态下两种滚转控制策略均能完成滚转控制,但在考虑气动参数摄动情况下,方向舵控制滚转的鲁棒性明显优越于改善LCDP的副翼控制滚转。The hypersonic vehicle has numerous control problems such as heading and Dutch roll instability, roll reverse in reentry phase due to high angle of attack. In order to ensure flight safety, it＇s necessary to study the roll control in large angle of attack. Firstly, two kinds of roll control strategies are presented in this paper, which are improved LCDP roll control by aileron and roll control by rudder. Then, the structured singular value is applied to analyze the robustness of them. Finally, control quality and robustness of the two roll control strategies are compared with each other by simulation. The simulation results show that they are both efficient to control roll angle in the nominal state, but the latter roll control strategy is more robust than the former one considering the perturbation of aerodynamic parameters.

关 键 词：高超声速飞行器 再入段 LCDP 滚转控制 结构奇异值 

分 类 号：V448[航空宇航科学与技术—飞行器设计]