[1]谢 磊,张洪波,周 祥,等.基于组合算法的运载火箭一子级动力垂直回收轨迹规划[J].控制与信息技术(原大功率变流技术),2019,(04):79-84.[doi:10.13889/j.issn.2096-5427.2019.04.013]
 XIE Lei,ZHANG Hongbo,ZHOU Xiang,et al.Trajectory Planning of First Stage Rocket Powered Vertical Recovery Using a Hybrid Optimization Method[J].High Power Converter Technology,2019,(04):79-84.[doi:10.13889/j.issn.2096-5427.2019.04.013]
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基于组合算法的运载火箭一子级动力垂直回收轨迹规划()
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《控制与信息技术》(原《大功率变流技术》)[ISSN:2095-3631/CN:43-1486/U]

卷:
期数:
2019年04期
页码:
79-84
栏目:
“中国飞行力学学术年会”专刊
出版日期:
2019-08-05

文章信息/Info

Title:
Trajectory Planning of First Stage Rocket Powered Vertical Recovery Using a Hybrid Optimization Method
文章编号:
2096-5427(2019)04-0079-06
作者:
谢 磊张洪波周 祥汤国建
(国防科技大学 空天科学学院,湖南 长沙 410073)
Author(s):
XIE LeiZHANG HongboZHOU XiangTANG Guojian
( College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, Hunan 410073, China)
关键词:
可重复使用运载火箭轨迹优化多约束遗传算法序列二次规划外罚函数法燃料最优
Keywords:
reusable rocket trajectory optimization multi-constraint genetic algorithm sequential quadratic programming(SQP) exterior penalty method optimal-fuel solution
分类号:
V448.2
DOI:
10.13889/j.issn.2096-5427.2019.04.013
文献标志码:
A
摘要:
标准轨迹设计是运载火箭一子级动力垂直回收制导方法研究的基础。文章针对标准轨迹设计,提出了一种基于外罚函数法、遗传算法与序列二次规划方法的组合算法。首先,将回收轨迹按照不同飞行特性分为5段,分别是:调姿段、高空滑翔段、动力减速段、气动减速段和着陆段;然后,采用外罚函数法将多约束问题转换为一个无约束问题,并利用遗传算法对其进行优化求解得到初始解;最后,在初始解的基础上,利用序列二次规划算法得到高精度的最优解。数值仿真结果表明,该方法可以优化出一条满足各项约束的回收轨迹,简单有效,具有较强的工程应用价值。
Abstract:
Standard trajectory design is the basis of rocket recovery guidance law. For this problem, a new hybrid optimization method combining the exterior penalty method, the genetic algorithm (GA) and the sequential quadratic programming (SQP) was proposed. Firstly, the recovery trajectory is divided into five phases: attitude adjustment phase, high-altitude gliding phase, power deceleration phase, atmospheric deceleration phase and powered landing phase. The multi-constraint problem is then transformed into an unconstrained problem by exterior penalty method, and the initial solution can be obtained by GA. Finally, to get a high accuracy optimal solution, a SQP method is employed. Numerical simulation results show that the proposed method can optimize a high accuracy recovery trajectory that satisfies various constraints, and it is simple and effective, which has a great value in the practical applications.

参考文献/References:

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备注/Memo

备注/Memo:
收稿日期:2019-05-15
作者简介:谢磊(1994—),男,硕士研究生,主要研究方向为飞行器动力学与控制;张洪波(1981—),男,教授,博士,主要研究方向为轨道力学、飞行器再入制导与控制。
基金项目:空间智能控制技术国家重点实验室基金项目(61422080106)
更新日期/Last Update: 2019-08-20