高升阻比再入飞行器阻力加速度设计及跟踪制导  

Drag Acceleration Design and Tracking Guidance for High L/D Reentry Vehicle

作　　者：蔺君 黄盘兴 何英姿[1,2] LIN Jun;HUANG Panxing;HE Yingzi(Beijing Institute of Control Engineering,Beijing 100094,China;Key Laboratory of Science and Technology on Space Intelligent Control,Beijing 100094,China.)

机构地区：[1]北京控制工程研究所,北京100094 [2]空间智能控制技术重点实验室,北京100094

出　　处：《空间控制技术与应用》2020年第1期16-23,36,共9页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(61873029)。

摘　　要：以无量纲能力为函数,采用参数化表示的分段线性函数描述标称阻力加速度剖面.在部分近似下,得到以无量纲能量描述的再入纵向航程解析解.将热流、过载、动压约束转化为阻力加速度剖面的边界值,利用全局优化方法,得到满足给定射程的阻力加速度剖面.通过调整目标函数阻尼因子,得到更为光滑的阻力加速度剖面,并将其作为标称阻力加速度剖面.基于反馈线性化方法,设计非线性跟踪控制器,实现对标称阻力加速度剖面的跟踪.设计航向角误差走廊,通过航向角误差调整倾侧角符号,控制飞行器横向航程.以CAV-H飞行器为例,设计数值仿真算例.仿真结果表明,最优阻力加速度剖面可满足再入约束及航程需求,跟踪控制器可快速求解制导指令,具有良好的跟踪性能.In this paper,the reference trajectory defined by drag profile is parameterized as piecewise linear function of energy.With some approximations,an analytical solution for downrange distance is obtained.The heat flow,overload and dynamic pressure constraints are transformed into the boundary value of the drag acceleration profile,and the global optimization method is used to obtain the drag acceleration profile that satisfies the given downrange.The reference drag profiles are smoothed for better feasibility by adjusting the objective function damping factor.A nonlinear control law based on feedback linearization is developed for trajectory tracking.The azimuth angle error corridor is designed,and the sign of bank angle symbol is adjusted by the azimuth angle error to control the lateral range.A numerical example is provided based on CAV-H.The simulation results show that the optimal drag acceleration profile can meet the reentry constraints and range requirements,and the tracking controller can quickly solve the guidance command and has good tracking performance.

关 键 词：阻力加速度 跟踪控制 反馈线性化 标称轨迹制导 全局优化 航向角误差走廊 

分 类 号：V448[航空宇航科学与技术—飞行器设计]