| 空天飞行器返回滑翔段在线制导方法 |
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| 引用本文： | 周宏宇,王小刚,赵亚丽,崔乃刚.空天飞行器返回滑翔段在线制导方法[J].宇航学报,2021,42(2):175-184. |
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| 作者姓名： | 周宏宇 王小刚 赵亚丽 崔乃刚 |
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| 作者单位： | 1. 哈尔滨工业大学航天学院，哈尔滨 150001；2. 北京航天晨信科技有限公司，北京 102308 |
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| 基金项目： | 中国博士后科学基金(2019M661290) |
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| 摘 要： | 针对空天往返飞行器的返回滑翔段在线制导问题，设计了一种新的滑翔段飞行剖面，实现了滑翔段终端交班高度、位置和倾角约束的自动满足，减少了在线制导算法中需处理的约束数量。推导了滑翔段运动状态、过程约束和性能指标的解析表达式，获得了剩余航程和终端速度间的函数关系。在此基础上，提出了一种双层在线制导方法：内层解析重构飞行剖面，同时通过解析确定路径点来改变剩余航程的变化率，进而对终端交班速度进行控制；外层借助解析表达式，使用粒子群优化算法(PSO)和改进共轭梯度法(CGM)优化飞行剖面，从而满足过程约束和指标要求。最后通过数学仿真验证了方法的正确性。
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| 关 键 词： | 空天飞行器 返回滑翔 在线制导 解析动力学 优化算法 |
| 收稿时间： | 2020-03-14 |
Online Guidance for Aerospace Vehicle in ReturnGliding
Phase |
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| ZHOU Hong yu,WANG Xiao gang,ZHAO Ya li,CUI Nai gang.Online Guidance for Aerospace Vehicle in ReturnGliding
Phase[J].Journal of Astronautics,2021,42(2):175-184. |
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| Authors: | ZHOU Hong yu WANG Xiao gang ZHAO Ya li CUI Nai gang |
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| Affiliation: | 1. School of Astronautics, Harbin Institute of
Technology, Harbin 150001, China;2. Beijing Aerocim Technology
Co., Ltd, Beijing 102308, China |
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| Abstract: | This paper studies the online gliding guidance law for
aerospace vehicles in the return phase. A new flight profile in the gliding
phase is proposed initially, according to which the constraints on the
altitude, the heading angle, the flight path angle and the range to go that are necessary for smooth transition to the terminal area
energy management, can be automatically satisfied, thus reducing the number of
constraints addressed in the guidance law. The accurate analytical solutions in
the gliding phase are deduced. In addition, the analytical expressions of the
path constraints and the performance indexes are obtained, and the dissipation
in the velocity is analytically represented with respect to the range to go. Then a double loop guidance law is proposed based on these analytical expressions.
In order to meet the terminal velocity, the inner loop revises the profile
analytically and controls the range to go by determining the waypoint. In order to satisfy the path
constraints and optimize the trajectory, the outer loop optimizes the profile
with a particle swarm optimization method and an improved conjugate gradient
method with analytical expressions. Finally, the numerical simulation
demonstrates the effectiveness of the proposed online guidance law. |
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| Keywords: | Aerospace vehicle Reentry gliding Online guidance Analytical dynamics Optimization algorithm |
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