摘要
柔性飞行器(Flexible Flying Wing Aircraft,FFWA)因具有高升力系数、低阻力系数等优点而受到广泛关注。受到结构动力学和刚体动力学的耦合作用,飞行器容易发生弹性形变,给柔性飞行器的建模造成困难,也给控制系统的设计带来挑战。为此,针对飞翼布局柔性飞行器模型,研究了一种自适应输出反馈控制方法,并在飞翼布局柔性飞行器上进行仿真验证。首先,搭建飞翼布局柔性飞行器纵向动力学模型,并进行配平;然后,对非线性纵向动力学模型线性化得到线性飞行器模型;然后,设计包括基于观测器的基线设计和基于修正闭环参考模型的参数自适应在内的自适应输出反馈控制器,总体上保证了存在不确定参数时的稳定性和跟踪性能;最后,验证了输出反馈控制器在加入修正闭环参考模型时的优越性能。仿真结果表明,运用输出反馈控制能够很好地处理飞行器模型存在不确定参数的问题,并且加入修正闭环参考模型能够提高控制器的参数自适应性能。
Flexible flying wing aircraft has attracted extensive attention because of its high lift coefficient and low drag coefficient.Due to the coupling of aircraft structural dynamics and rigid body dynamics,aircraft is prone to elastic deformation,which not only makes it difficult to model flexible aircraft,but also brings challenges to the design of control system.Therefore,an adaptive output feedback control method is designed for the flexible aircraft model of the flying wing configuration,and the simulation application is carried out on the flexible flying wing aircraft.Firstly,the longitudinal dynamic model of flexible flying wing aircraft is constructed and the trim analysis is carried out.Then,the nonlinear longitudinal dynamic model is linearized to obtain the linear aircraft model.Then,an adaptive output feedback controller is designed,including observer based baseline design and parameter adaptation based on modified closed-loop reference model.The overall design ensures the stability and tracking performance in the presence of large parameter uncertainty.Finally,the superior performance of the output feedback controller under the condition of parameter adaptation with modified closed-loop reference model is verified.The simulation results show that the output feedback control can well deal with the parameter uncertainty of the aircraft model,and adding the modified closed-loop reference model can improve the parameter adaptive performance of the controller.
作者
王民泰
曹云峰
周嘉麒
WANG Min-tai;CAO Yun-feng;ZHOU Jia-qi(Nanjing University of Aeronautics and Astronautics,Aerospace Academy,Nanjing 210000,China)
出处
《指挥控制与仿真》
2022年第4期105-111,共7页
Command Control & Simulation
