以基于前掠翼布局及翼身融合一体化技术设计的W型无尾飞机为被控对象,采用线性二次型高斯/回路传输恢复LQG/LTR(Linear Quadratic Gaussian with Loop Transfer Recovery)多变量鲁棒控制方法完成了飞机横航向控制设计.该方法解决了由于...以基于前掠翼布局及翼身融合一体化技术设计的W型无尾飞机为被控对象,采用线性二次型高斯/回路传输恢复LQG/LTR(Linear Quadratic Gaussian with Loop Transfer Recovery)多变量鲁棒控制方法完成了飞机横航向控制设计.该方法解决了由于该特殊构型导致的本体不稳定,以及运动模型的不确定性、随机干扰下控制系统可能出现的不稳定和控制精度不够的问题.系统仿真结果表明,控制系统实现了横航向指令的精确跟踪,不但具有良好的鲁棒性,而且调节性能良好,满足W型无尾飞机横航向控制设计的要求.展开更多
Supersonic Tailless Aerial Vehicles(STAVs)will become an essential force in Penetrating Counter Air(PCA),but STAVs do not have the traditional horizontal and vertical tails,making pitch and yaw control difficult.The a...Supersonic Tailless Aerial Vehicles(STAVs)will become an essential force in Penetrating Counter Air(PCA),but STAVs do not have the traditional horizontal and vertical tails,making pitch and yaw control difficult.The attack angle and the sideslip angle need to be limited to ensure that the engine inlet and the aerodynamic rudder at the rear of the vehicle can work properly,which is the so-called security constraints.In addition,the tracking error of the aerodynamic angle needs to be limited to achieve effective attitude control or high-accuracy tracking of trajectories,which is the so-called performance constraints.To this end,an attitude control method that meets the needs of PCA has been devised,based on constraint definition,coupled constraints handling,and control law design.Firstly,mathematical descriptions of the security constraints,performance constraints,and control constraints are given.Secondly,two treatment methods,coupled command filter and coupled funnel control are proposed for the aerodynamic angle coupled constraint problem.Finally,based on Nonlinear Dynamic Inverse(NDI)design,the coupled funnel controller is designed and validated by simulation for two typical mission scenarios,high-altitude penetration and low-altitude surprise defence.The proposed control method not only satisfies the security and performance constraints of STAV attitude control but also is highly robust.展开更多
文摘以基于前掠翼布局及翼身融合一体化技术设计的W型无尾飞机为被控对象,采用线性二次型高斯/回路传输恢复LQG/LTR(Linear Quadratic Gaussian with Loop Transfer Recovery)多变量鲁棒控制方法完成了飞机横航向控制设计.该方法解决了由于该特殊构型导致的本体不稳定,以及运动模型的不确定性、随机干扰下控制系统可能出现的不稳定和控制精度不够的问题.系统仿真结果表明,控制系统实现了横航向指令的精确跟踪,不但具有良好的鲁棒性,而且调节性能良好,满足W型无尾飞机横航向控制设计的要求.
基金supported by the National Natural Science Foundation of China(No.62103439)the China Postdoctoral Science Foundation(No.2020M683716)+1 种基金the National Key Laboratory of Unmanned Aerial Vehicle Technology,Chinathe Youth Innovation Team of Shaanxi University,China.
文摘Supersonic Tailless Aerial Vehicles(STAVs)will become an essential force in Penetrating Counter Air(PCA),but STAVs do not have the traditional horizontal and vertical tails,making pitch and yaw control difficult.The attack angle and the sideslip angle need to be limited to ensure that the engine inlet and the aerodynamic rudder at the rear of the vehicle can work properly,which is the so-called security constraints.In addition,the tracking error of the aerodynamic angle needs to be limited to achieve effective attitude control or high-accuracy tracking of trajectories,which is the so-called performance constraints.To this end,an attitude control method that meets the needs of PCA has been devised,based on constraint definition,coupled constraints handling,and control law design.Firstly,mathematical descriptions of the security constraints,performance constraints,and control constraints are given.Secondly,two treatment methods,coupled command filter and coupled funnel control are proposed for the aerodynamic angle coupled constraint problem.Finally,based on Nonlinear Dynamic Inverse(NDI)design,the coupled funnel controller is designed and validated by simulation for two typical mission scenarios,high-altitude penetration and low-altitude surprise defence.The proposed control method not only satisfies the security and performance constraints of STAV attitude control but also is highly robust.
