运载火箭入轨段的自抗扰预测制导方法  

Active disturbance rejection predictive guidance method for launch vehicle in enter-orbit segment

作　　者：熊静炜 张洪波[1,2] XIONG Jingwei;ZHANG Hongbo(National University of Defense Technology,Changsha 410073,China;Hunan Provincial Key Laboratory of Aerospace Cross-Domain Flight Vehicle System and Control Technology,Changsha 410073,China)

机构地区：[1]国防科技大学,湖南长沙410073 [2]空天跨域飞行器总体与控制技术湖南省重点实验室,湖南长沙410073

出　　处：《飞行力学》2024年第1期1-7,共7页Flight Dynamics

摘　　要：运载火箭的入轨段运动对入轨精度的影响很大,为避免扰动干扰,提出了一种自抗扰预测制导方法。首先,基于运载火箭三自由度模型,引入平均重力场、简化终端约束的处理形成了改进的轨迹规划算法,加快了收敛速度,能够适应在线轨迹规划的需要。然后,设计了自抗扰轨迹跟踪器,与在线轨迹规划算法结合形成了自抗扰预测制导方法。数值仿真结果表明,所提自抗扰预测方法在应对推力故障及其他典型偏差干扰时均有较高的入轨精度和鲁棒性,可为运载火箭入轨段制导控制系统的适应性提供参考。As the motion of launch vehicle during the enter-orbit segment has a great influence on the orbiting accuracy,in order to cope with the perturbation situations,an active disturbance rejection predictive guidance method is proposed.Firstly,based on the three-degree-of-freedom model of the launch vehicle,an improved trajectory planning algorithm is formed by introducing average gravity field and simplifying terminal constraints,which accelerates the convergence speed and satisfies the needs of online trajectory planning.Then,an active disturbance rejective trajectory tracker is designed,combining with the online trajectory planning algorithm,an active disturbance predictive guidance method is formed.The numerical simulation indicates that the proposed method has a high orbiting accuracy and robustness in dealing with thrust fault and other typical deviation disturbances,which can provide a reference for the adaptability of the guidance control system during the enter-orbit segment of the launch vehicle.

关 键 词：运载火箭 入轨段制导 轨迹在线规划 自抗扰控制 预测制导 

分 类 号：V448.1[航空宇航科学与技术—飞行器设计]