基于能量的再入飞行器轨迹设计与控制  

Energy-based Reentry Vehicles Trajectory Design and Control

作　　者：郝振华[1] 王伟[1] 李爱军[1] 倪晓彬[1] 

机构地区：[1]西北工业大学自动化学院,陕西西安710072

出　　处：《弹箭与制导学报》2004年第S3期125-129,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：航天预研基金及西北工业大学研究生创业种子基金资助(M016609);西工大英才培养计划资助项目(03XD0103)

摘　　要：研究基于参考阻力-能量剖面的第二代可重复使用航天器再入轨迹设计与控制算法。首先给出再入动力学原理、再入轨迹约束、再入问题描述及相应的假设,采用再入飞行器能量的分段线性化方法定义再入轨迹的阻力加速度剖面,并通过参数解析优化设计阻力-能量剖面。引入反馈线性化技术,设计自适应非线性跟踪控制律跟踪参考阻力剖面,同时考虑纵向和侧向控制,解决航向校正问题以满足末端能量管理段界面条件。This paper develops a methodology for the reentry trajectory design and control algorithm based on drag- vs-energy reference profile for the 2^(nd)Generation Reusable Launch Vehicles(RLV).First,the approach describes the entry dynamics principles,entry trajectory constrains,entry problem statement and assumption.Next,The entry trajectory is defined by a drag acceleration profile which is piecewise linear in the specific energy and obtained by solving an analytical parameter optimization problem very efficiently.The technique of feedback linearization is used to obtain an adaptive nonlinear tracking control law to track the reference drag profile.Lateral as well as longitudinal is considered in control,and the heading adjustment question is solved to satisfy the condition terminal area energy management(TAEM)interface.

关 键 词：可重复使用航天器 再入 轨迹 控制 反馈线性化 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]