摘要
针对大展弦比飞翼布局柔性飞行器在刚体和弹性自由度动力学强耦合情况下的控制问题,对相应的强耦合动力学特性与相应的控制方法展开研究.采用自由-自由模态法表征飞翼刚柔运动之间的惯性耦合;采用偶极子网格法和有理函数近似法完成广义非定常气动力计算;应用线性二次型最优控制方法进行飞行机动与弹性变形的联合控制律设计.与无控情况相比,闭环控制可有效减缓飞行器俯仰方向的阵风扰动至原来的40%.研究结果表明,飞行器一阶弯曲模态短周期之间存在明显动力学耦合.设计的闭环控制律可使动态弹性变形量始终向有助于减缓扰动方向变化.
This research investigated the dynamic properties of a flying wing aircraft with high aspect ratio and strong coupling between the flight dynamics and the aeroelasticity,and the corresponding control method.The inertial coupling between rigid-body DoF motion and elastic DoF motion were addressed by free-free modes of the whole aircraft.The double lattice vortex method and the rational function approximation(RFA)method were used for unsteady aerodynamic calculation.LQR method was used for the combined control law design to control the flight dynamics and elastic deformation simultaneously.Compared with the uncontrolled case,the designed close-loop control law could effectively reduce 60%of the pitching angle disturbance.It can be concluded that there is significant dynamic coupling between the short period and the first bending aeroelastic mode.The combine control law can generate dynamic elastic deformation which is always helpful to disturbance alleviation in the dynamic process.
作者
张硕
王正杰
陈昊
ZHANG Shuo;WANG Zheng-jie;CHEN Hao(School of Mechatronical Engineering,Beijing Institute of Technology,Beijing 100081,China)
出处
《北京理工大学学报》
EI
CAS
CSCD
北大核心
2020年第2期157-162,共6页
Transactions of Beijing Institute of Technology
基金
国家自然科学基金资助项目(11672033)。
关键词
飞翼布局
刚柔耦合
飞行动力学
飞行控制
LQR
flying wing configuration
rigid-flexible coupling
flight dynamics
flight control
LQR
