近空间可变翼飞行器爬升/巡航段切换控制

Sliding Mode Switching Control of Ascent/Cruise Phase for Near Space Vehicle

近空间可变翼飞行器在不同飞行段进行模态切换过程中,由于飞行状态会发生突变,不同模态下控制器结构参数发生变化,难以设计一个通用控制器保证两个模态及模态切换过程的稳定性和平滑性。若直接进行两个模态控制器硬切换,会导致飞行器的控制律参数发生跳变,从而引起飞行状态发生突变,影响模态切换过程的稳定性和平滑性,致使系统不稳定,造成飞行事故。以爬升段末到巡航段初为例,设计一种基于惯性环节的快速双幂次滑模切换控制器。首先对切换前后的滑模面进行淡化处理,得到切换控制律的滑模面,然后针对新的滑模面设计滑模切换控制律,最后对比分析直接切换和快速双幂次滑模切换。仿真结果表明快速双幂次滑模切换控制方法具有良好的跟踪控制效果。

In the process of modal switching between different phases of flight, the parameters of the controller in different modes may change due to the sudden change of flight state, thus it is difficult to design a general controller to ensure the stability and smoothness of the switching process of both the modes. Direct switching between the two modal controllers may cause jumping of the control law parameters of the aircraft, and result in sudden change of the flight state, which will then affect the stability and smoothness of the modal switching process, make the system unstable and cause flight accident. In this paper, a fast double-power sliding mode switching controller based on inertia is designed taking the switching from the end climbing section to the initial cruise section as the example. Firstly, the sliding surface of the sliding mode before and after switching is used to get the sliding surface of the switching control law, and then the sliding mode switching control law is designed for the new sliding surface. Finally, the simulation results show that the fast double-power switching control method has a good tracking control effect.