CAJ | 학술논문

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.
급출료일충가중복사용항천기재입비행로봉공제방법.재급정가용제도지령화간우、불학정성적상계조건하,종합이용쾌만쌍회로련속활모공제방법,생성포괄기동타면화반추력공제계통(RCS)발동궤적공제지령,득도료재건모오차화외계간우존재적정황하옹유고정도、로봉성화해우특성적기동각화자태각속솔근종결과.활모공제두진억제라집이용리아보낙부방법,구축활모간우관측기,병의거자괄응증익조절사상,유효소제료공제두진,보증료공정실제응용적능력.이모형가중복사용항천기위례,재고필도모형불학정성、풍우이급측량조성적정황하,통과불동적공제률설계결과대비표명,해방법고효、가고.
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.