高速飞行器横侧向耦合振荡发散机理及控制策略研究  

Research on Lateral Coupling Oscillation Divergence Mechanism and Control Strategy of High-speed Aircraft

作　　者：孙超逸 刘全军 王颖 刘秀明 Sun Chao-yi;Liu Quan-jun;Wang Ying;Liu Xiu-ming(Science and Technology on Space Physics Laboratory,Beijing,100076)

机构地区：[1]空间物理重点实验室,北京100076

出　　处：《导弹与航天运载技术》2022年第4期35-38,共4页Missiles and Space Vehicles

摘　　要：高速飞行器在同时满足偏航动稳定判据和横向控制偏离判据的前提下,仍有可能出现横侧向耦合振荡发散的问题,针对此问题进行机理分析,得出原因是荷兰滚模态零极点配置关系不理想,并提出通过增加副翼反馈侧滑角的控制策略来避免横侧向耦合振荡。最后,通过仿真验证了控制策略的有效性。On the premise of satisfying the C_(n,dyn)^(β) and the lateral control departure parameter criterion, the high-speed aircraft may still have the problem of lateral coupling oscillation divergence. The mechanism of this problem is analyzed and the reason is concluded which is the unsatisfactory relationship between the zero and pole of the Dutch roll mode. A control strategy of increasing the sideslip angle feedback is proposed to avoid the lateral coupling oscillation. Finally, the effectiveness of the control strategy is verified by simulation.

关 键 词：横侧向耦合 振荡发散 控制策略 

分 类 号：V448[航空宇航科学与技术—飞行器设计]