高超声速变外形飞行器建模与有限时间控制

针对高超声速变外形飞行器变形带来的参数摄动大、变形过程建模难、外界干扰复杂等大不确定问题，研究了一类可变后掠飞行器建模与姿态控制问题，设计了一种有限时间控制方案。针对变外形飞行器建立了带有变形量的面向姿态控制的三自由度模型，该模型能够反映出变外形飞行器的内在影响。分析了变外形飞行器在典型状态下的气动特征，并给出了连续变形关键气动数据可行处理方案。针对可连续变形的飞行器设计了一套有限时间控制方案，并证明了系统稳定性。进一步考虑控制律中用到的指令微分项，设计了有限时间指令收敛滤波器。利用扩张状态观测器，估计不易测量状态和“综合扰动”。以考虑复杂干扰下的高超声速变外形飞行器为对象进行仿真，结果表明：所设计的控制方案可解决不同变形速率下、存在复合干扰的飞行器姿态控制问题。

Modeling and finite-time control for hypersonic morphing flight vehicle

The attitude control of hypersonic morphing flight vehicles cause problems of large uncertainties, such as time-varying parameter perturbation, difficulty in modeling deformation process, and complex "lumped disturbances". To address these problems, a control-oriented model for variable-sweep wing hypersonic flight vehicles is established, and a finite-time control scheme is proposed. Firstly, a three-degree-of-freedom model is established for attitude control, which can reflect the influence caused by deformation. Secondly, the aerodynamic characteristics of the hypersonic morphing flight vehicle in some typical states are analyzed, and a feasible method for the key aerodynamic data of continuous deformation is developed. Thirdly, a finite-time control scheme is designed for the continuously deformable vehicle, and the system stability is demonstrated. Further, the finite-time convergence filter is designed, considering the command differentiation term used in the control law. An extended state observer is also used to estimate the unmeasurable states and the "lumped disturbances". Finally, numerical simulations are performed with complex disturbances, and the results show that the proposed control scheme can solve the attitude control problem for the vehicle with complex disturbances at different deformation rates.