机翼不对称损伤飞机在大侧滑角下的操稳特性研究  

Research on High Sideslip Angle Stability and Control of Wing-damaged Asymmetric Aircraft

作　　者：程鹏飞[1] 吴成富[1] 郭月[2] 

机构地区：[1]西北工业大学无人机特种技术重点实验室,西安710065 [2]西北工业大学自动化学院,西安710072

出　　处：《火力与指挥控制》2015年第4期27-32,共6页Fire Control & Command Control

基　　金：国家自然科学基金(61201320);解放军总装预研基金资助项目(513250202)

摘　　要：对某小型电动无人机(以下简称SEPUAV)在其左翼破损40%面积矩下的操稳特性进行详细分析。首先在此损伤下典型大侧滑角定常工作点附近进行特殊的小扰动线性化,然后进行特征根和飞行运动模态的分析;其次对此特殊构型SEPUAV进行操稳特性、时频响应特性进行分析。分析结果表明:左翼破损40%面积矩SEPUAV出现特有运动模态并影响全部纵侧向运动状态的响应;部分传递函数出现较多非最小相位零点从而导致初始响应发生反向;部分通道的Bode图中出现多个波峰波谷并有相角提前等现象。分析结果对后续容损飞行控制器的设计起到铺垫的作用。This paper mainly presents a detailed analysis on flight dynamics of a small electric-powered UAV （SEPUAV） with 40 % left wing’s area moment loss. Firstly,special small perturbation linearization under high angle of sideslip is developed. The eigenvalues and flight motion modes are analyzed. Next the stability and control performance,time and frequency response characteristics are analyzed. The results are as follows： the specific motion modes appear and affect the responses of all longitudinal-lateral-directional motion-states; some transfer functions have more non-minimum phase zeros which make the initial responses be reversed; more peaks-and-troughts in different frequency and phase advance appear in the Bode diagrams of some channels. The analysis against wing-damaged UAV plays an fundamental role in developing a damage tolerant flight controller further.

关 键 词：机翼不对称损伤 飞行运动模态 操稳特性 时频响应特性 强耦合飞行动力学 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程]