组合动力飞行器模态转换段推阻匹配与控制律设计

Design of push⁃drag matching and control law for combined⁃power aircraft in modal conversion section

针对组合动力飞行器在进行模态转换时,发动机推力的损失以及进气道进气时对飞行器周围气流的影响,导致飞行器本体动力学特性呈现出强烈的非线性、耦合性和模型不匹配性等问题。文中根据涡喷发动机和冲压发动机输出推力随流量变化的关系,提出一种流量分配方案补偿了发动机动力切换时的推力损失。考虑到组合动力飞行器模态转换段动力学的复杂性,采用L1鲁棒自适应控制实现飞行器的内环增稳,采用蒙特卡洛打靶方式验证控制律的鲁棒性。仿真实验证明,设计的控制律具有一定鲁棒性。

In allusion to the influence of the engine thrust loss and the air inflow at air inlet on air flow around the aircraft during the mode conversion of the combined⁃power aircraft,which may cause that the dynamic characteristics of the aircraft body presents strong nonlinearity,coupling and model mismatch,a flow distribution scheme is proposed to compensate for the thrust loss at power switching of the engine according to the relationship that the output thrust of the turbojet engine and the ramjet engine changes with the flow rate.In consideration of the complexity of dynamics at the mode conversion section of the combined⁃power aircraft,the adaptive control of L1 robust is used to achieve inner ring stabilization,and the Monte Carlo target shooting way is used to verify the robustness of the control law.The simulation experiments show that the designed control low has a certain robustness.