非对称变翼飞行器复合控制系统设计  

Compound Control System Design for Asymmetric Morphing-Wing Aircraft

作　　者：郭建国[1] 吴林旭 周军[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,西安710072

出　　处：《宇航学报》2018年第1期52-59,共8页Journal of Astronautics

摘　　要：针对非对称变翼飞行器的姿态控制问题,提出了一种复合控制系统的设计方法。基于非对称变翼的姿态动力学模型,将变翼作为一种主动控制方式,提出了非对称变翼的使用条件,并采用逻辑函数设计了气动舵和变翼的复合控制分配策略。利用扩张干扰观测器估计了变翼过程中的扰动,采用全局滑动模态的变结构控制方法,设计了姿态复合控制系统,抑制了变形过程中参数的剧烈变化和变形引起的附加扰动。通过仿真,一方面与固定翼飞行器对比,校验了非对称变翼控制的有效性;另一方面通过气动数据的正负拉偏,验证了控制器对气动参数的摄动有良好的鲁棒性。Aiming at the attitude control of an asymmetric morphing-wing aircraft, a compound control system is proposed. Based on the dynamic model of the asymmetric morphing-wing aircraft, the morphing wing is regarded as a new active control mechanism and the condition of using the asymmetric morphing wing is determined. A control strategy for the allocation of the control commands is designed by the logic function. The disturbance caused by the morphing wing is estimated by the extended disturbance observer and the variable structure control method with global sliding mode is used to design the compound control system which restrains the violent changes in parameters and disturbance during the process of morphing. According to the simulation, compared to the fixed-wing aircraft, the effectiveness of the asymmetric morphing wing is assessed and the robustness of the controller is also evaluated by the perturbation of the parameters.

关 键 词：变翼飞行器 非对称 复合控制 控制指令分配 全局滑动模态 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]