CAJ | 학술논문

为了提高再入制导的实时性和鲁棒性，设计一种标准轨迹跟踪制导方法。首先将参考轨迹的跟踪问题转化为轨迹状态调节问题，进一步转化为一个线性时变系统的最优控制问题；然后采用滚动时域控制结合基于间接 Legendre 伪谱法的最优反馈控制算法设计出一种易于在线实现的制导律。基于上述工作完成了亚轨道飞行器（suborbital reusable launch vehicle，SRLV）返回制导过程的3自由度数值仿真研究工作。数值算例说明，该制导方法在初始点状态存在较大范围偏差和气动参数存在较大误差的情况下具有良好的鲁棒性。
위료제고재입제도적실시성화로봉성，설계일충표준궤적근종제도방법。수선장삼고궤적적근종문제전화위궤적상태조절문제，진일보전화위일개선성시변계통적최우공제문제；연후채용곤동시역공제결합기우간접 Legendre 위보법적최우반궤공제산법설계출일충역우재선실현적제도률。기우상술공작완성료아궤도비행기（suborbital reusable launch vehicle，SRLV）반회제도과정적3자유도수치방진연구공작。수치산례설명，해제도방법재초시점상태존재교대범위편차화기동삼수존재교대오차적정황하구유량호적로봉성。
To improve the instantaneity and robust ness,a reference-trajectory guidance scheme for the re-entry is introduced.The trajectory tracking problem based on the obtained reference trajectory is converted into a trajectory state regulation problem which is actually an optimal control problem of a linear time varying sys-tem.And a robust guidance law combines the benefits of the indirect Legendre pseudo-spectral method and the receding horizon control method is applied to the problem.The three degree of freedom guidance for the reentry of suborbital reusable launch vehicle (SRLV)is implemented.Finally,numerical results indicate that the guidance scheme is robust to the presence of a wide range of initial uncertainties and aerodynamic parameters disturbance.