可重复使用航天器基于状态估计的再入飞行滑模控制器设计研究

给出了一种可重复使用航天器再入飞行鲁棒控制方法。在给定可用制导指令和干扰、不确定性的上界条件下，综合利用快慢双回路连续滑模控制方法，生成包括气动舵面和反推力控制系统（RCS）发动机的控制指令，得到了在建模误差和外界干扰存在的情况下拥有高精度、鲁棒性和解耦特性的气动角和姿态角速率跟踪结果。滑模控制抖振抑制逻辑利用李亚普诺夫方法，构筑滑模干扰观测器，并依据自适应增益调节思想，有效消除了控制抖振，保证了工程实际应用的能力。以某型可重复使用航天器为例，在考虑到模型不确定性、风扰以及测量噪声的情况下．通过不同的控制律设计结果对比表明，该方法高效、可靠。

Entry Control Using Sliding Modes and State Observer Synthesis for Reusable Launch Vehicle

A robust method for the implementation of entry control for reusable launch vehicle is presented.Given any feasible guidance commands and the bounds of uncertainties and disturbances,the method can generate control commands to each individual effectors including aerosurfaces and reaction control system(RCS) jets,featuring multiple-time-scale continuous sliding mode control,which meets the requirement with accurate,robust,and decoupled tracking of both the commanded aerodynamic angle and angular rate profiles in the presence of modeling uncertainties and external disturbances.Afterwards,utilizing sliding mode state observer via Lyapunov theorem with adaptive gain to achieve the estimation without high amplitude switching for more convenient implementation,the method enables the entry control system to reduce the control chattering significantly and enhance applicability remarkably.To compare with the pure sliding mode control,entry control law design and simulations for a reusable launch vehicle model with modeling uncertainties,wind gust,measuring noises are presented to demonstrate the capacity and reliability of this proposed method.