摘要
为了研究变体飞行过程中不同的气动结构对控制系统产生的影响,利用多刚体动力学对飞行器各个通道进行建模,通过对变体过程气动参数的研究,探寻变体飞行器不同变形状态的升阻比变化规律,推导了飞行器实现最佳控制品质的控制律。设计了线性二次型控制器,并通过Simulink进行仿真验证,结果表明:计算条件下变体飞行器的最佳升阻比可以改变36%,收敛快速性可以提高128.61%;通过变体,飞行器可以大幅度改变升阻特性,系统稳定性和收敛快速性都得到了很大提高。
In order to study the influence of different aerodynamic structures on the control system during morphing flight,the various channels of the morphing aircraft were modelled by using multi-rigid body dynamics.Through the study of aerodynamic parameters in the process of morphing,the lift-drag ratio variation rule of morphing aircraft was explored,and the optimal quality control-law of aircraft was deduced.The linear quadratic controller was designed and verified by Simulink.The results show that the optimal lift-to-drag ratio can be changed by 36%,and the rapidity can be increased by 128.61%.Through the morphing,the aircraft can effectively change the lift-to-drag ratio,and the system stability and convergence rapidity can be improved.
作者
杨博
窦婧文
曹振
YANG Bo;DOU Jingwen;CAO Zhen(School of Astronautics,Beijing University of Aeronautics and Astronautics,Beijing 102206,China;Beijing System Design Institute of Electro Mechanic Engineering,Beijing 100854,China)
出处
《弹道学报》
EI
CSCD
北大核心
2020年第1期83-90,96,共9页
Journal of Ballistics
关键词
变体飞行器
折叠翼
气动特性
控制系统
morphing aircraft
folding wings
aerodynamic characteristics
control system
