基于匹配渐进展开的跳跃式再入解析预测-校正制导律设计

doi:10.7527/S1000-6893.2015.0143

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基于匹配渐进展开的跳跃式再入解析预测-校正制导律设计

崔乃刚¹, 黄荣¹, 傅瑜², 韩鹏鑫³

1. 哈尔滨工业大学航天学院, 哈尔滨 150001;
2. 北京宇航系统工程研究所, 北京 100076;
3. 中国运载火箭技术研究院研究发展中心, 北京 100076

收稿日期:2015-04-27 修回日期:2015-05-25 出版日期:2015-08-15 发布日期:2015-06-01
通讯作者: 崔乃刚男, 博士, 教授, 博士生导师。《航空学报》第七、八届编委。导弹攻防对抗等。Tel: 0451-86412766 E-mail: Cui_Naigang@163.com E-mail:Cui_Naigang@163.com
作者简介:黄荣男, 博士研究生。主要研究方向: 飞行器总体设计, 轨迹优化与制导控制。Tel: 0451-86412766 E-mail: I_amhaungrong@163.com
基金资助:
国家自然科学基金(61403100); 中央高校基本科研业务费专项资金(HIT.NSRIF.2015037)

Design of analytical prediction-correction skip entry guidance law based on matched asymptotic expansions

CUI Naigang¹, HUANG Rong¹, FU Yu², HAN Pengxin³

1. School of Astronautics, Harbin Institute of Technology, Harbin 150001, China;
2. Beijing Institute of Astronautical Systems Engineering, Beijing 100076, China;
3. Research and Development Center, China Academy of Launch Vehicle Technology, Beijing 100076, China

Received:2015-04-27 Revised:2015-05-25 Online:2015-08-15 Published:2015-06-01
Contact: 10.7527/S1000-6893.2015.0143 E-mail:Cui_Naigang@163.com
Supported by:
National Natural Science Foundation of China (61403100); Fundamental Research Funds for the Central Universities (HIT.NSRIF.2015037)

摘要/Abstract

摘要：

为了适应低升阻比飞行器再入返回的大航程要求,针对大气跳跃再入飞行环境复杂并难以直接获得解析解的特点,基于匹配渐进展开法设计了一种跳跃式再入解析预测-校正制导方法。首先分析了低升阻比飞行器大气跳跃再入轨迹的飞行剖面和制导分段方法;然后分别推导了其运动方程以重力作用为主导的外解和以气动力作用为主导的内解的渐进展开形式,并通过匹配获得了统一的封闭解析表达式;接着基于此解析解实时预测飞行器的剩余航程,并通过不断迭代升阻比垂向分量以满足最后的落点精度;最后针对跳跃再入飞行的不同阶段设计了不同的制导策略以获得最终的倾侧角指令。仿真结果表明采用跳跃式再入返回技术,阿波罗指令舱的航程能够达到8 348 km,而解析预测-校正制导律的落点精度为0.338 km,证明了此方法的有效性。

关键词: 低升阻比, 大气跳跃再入, 匹配渐进展开, 解析预测-校正, 制导

Abstract:

In order to adapt to the demand of the long range for the entry return of low lift-drag ratio aircraft, and considering the difficulty of obtaining the analytical solution directly due to the complex flying environment of the atmospheric skip entry, an analytical prediction-correction skip entry guidance law based on the matched asymptotic expansion method is designed. The flight profile and guidance section method of low lift-drag ratio aircraft atmospheric skip entry flight are given at first. Then the outer expansions for the gravitational-dominated region and the inner expansions for the aerodynamic-dominated region are derivated respectively, and the closed-form analytical composite expansions of the governing equations are obtained by matching the asymptotic expansions. Based on the analytical expansions, the range-to-go to the target is computed in real time, and the vertical-lift-drag ratio component is adjusted using a secant iteration method until the predicted downrange error is satisfied. Finally, different guidance strategies are designed for different stages of skip entry flight to obtain the terminal command of bank angle. The simulation results show that the range of Apollo command module can be 8 348 km with technology of skip entry return, while the landing error of the analytical prediction-correction guidance law is 0.338 km, which prove the effectiveness of the method.

Key words: low lift-drag ratio, atmospheric skip entry, matched asymptotic expansions, analytical prediction-correction, guidance

中图分类号:

V448

崔乃刚, 黄荣, 傅瑜, 韩鹏鑫. 基于匹配渐进展开的跳跃式再入解析预测-校正制导律设计[J]. 航空学报, doi: 10.7527/S1000-6893.2015.0143.

CUI Naigang, HUANG Rong, FU Yu, HAN Pengxin. Design of analytical prediction-correction skip entry guidance law based on matched asymptotic expansions[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, doi: 10.7527/S1000-6893.2015.0143.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于匹配渐进展开的跳跃式再入解析预测-校正制导律设计

Design of analytical prediction-correction skip entry guidance law based on matched asymptotic expansions

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