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针对一类带有挠性的吸气式高超声速飞行器设计具有传感器容错能力的控制器。飞行器机体的刚性模态和挠性模态之间的强耦合作用不仅仅会直接影响到气动力和气动力矩,而且还会造成传感器的测量误差,尤其是给攻角测量带来加性扰动的影响,这给基于状态反馈控制器的设计带来了极大挑战。因此,为了解决这个问题,引入了比例积分型状态观测器,利用系统的输入和受干扰的输出重构出原系统的状态,然后利用重构的状态设计保性能控制器,在稳定该高超声速飞行器模型的同时,也使得给定的二次性能指标达到其最小的上界。本文的主要贡献在于成功地改进了传统意义上的状态反馈方法,并消除了因为挠性模态影响造成的传感器测量误差所带来的影响,这在实际工程中具有重要的意义。文章最后给出的仿真结果显示出了比例积分型状态观测器具有较好的动态性能,以及保性能控制器出色地完成了该模型高度和速度通道对指令信号的跟踪任务。
Design of Controller with Sensor Fault Tolerance for a Class of Aspirated Hypersonic Vehicles with Flexibility. The strong coupling between the rigid and flexible modes of the aircraft body not only directly affects the aerodynamic and aerodynamic torques, but also causes errors in the measurement of the sensors, especially in the case of additive perturbations to the angle of attack measurements Impact, which poses a great challenge to the design of state feedback controller. Therefore, in order to solve this problem, a proportional-integral type state observer is introduced to reconstruct the state of the original system by using the input of the system and the output of the disturbance. Then, the state-of- At the same time, it also makes the given quadratic performance index reach its minimum upper bound. The main contribution of this paper is to successfully improve the traditional state feedback method and eliminate the influence of sensor measurement error caused by the flexible modal effect, which is of great significance in practical engineering. The simulation results presented at the end of this paper show that the proportional integral state observer has better dynamic performance, and the guaranteed cost controller performs the task of tracking the command signal well by the model height and velocity channel.