[1]杨 明,刘 明,郑 伟,等.空射近空间飞行器助推弹道规划方法[J].弹道学报,2019,(03):7-11.[doi:10.12115/j.issn.1004-499X(2019)03-002]
 YANG Ming,LIU Ming,ZHENG Wei,et al.Ascent Trajectory Planning for Air-launched Near Space Vehicle[J].Journal Of Ballistics,2019,(03):7-11.[doi:10.12115/j.issn.1004-499X(2019)03-002]
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空射近空间飞行器助推弹道规划方法()
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《弹道学报》[ISSN:1004-499X/CN:32-1343/TJ]

卷:
期数:
2019年03期
页码:
7-11
栏目:
出版日期:
2019-09-30

文章信息/Info

Title:
Ascent Trajectory Planning for Air-launched Near Space Vehicle
文章编号:
1004-499X(2019)03-0007-05
作者:
杨 明12刘 明12郑 伟1高 兴2陈志刚2
1.国防科技大学 空天科学学院,湖南 长沙 410073; 2.空间物理重点实验室,北京 100076
Author(s):
YANG Ming12LIU Ming12ZHENG Wei1GAO Xing2CHEN Zhigang2
1.College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China; 2.Science and Technology on Space Physics Laboratory,Beijing 100076,China
关键词:
空中发射 近空间飞行器 助推弹道 粒子群算法
Keywords:
air launching near space vehicle ascent trajectory particle swarm optimization
分类号:
TJ303.4
DOI:
10.12115/j.issn.1004-499X(2019)03-002
摘要:
为研究空射近空间飞行器低弹道快速入轨弹道规划问题,将空射近空间飞行器助推弹道分为投放段、一级飞行段、无动力滑行段、二级飞行段。一级飞行段采用最大可用过载快速拉起; 二级飞行段纵向剖面采用基于分段多项式的参数化控制方法,二级飞行段横向剖面设计了基于三角函数的参数化能量管理; 形成了多段多约束参数化助推弹道规划模型,采用改进粒子群算法对该问题进行求解。仿真结果表明:规划弹道满足过载、控制及分离等各类约束条件; 该方法具有很高的求解精度和较快的求解速度,能获得满足不同交班需求的参考弹道。
Abstract:
To study the planning approach of low-altitude rapid ascent trajectory for air-launched near-space vehicle,the ascent trajectory was divided into four phases such as dropping phase,the first powered phase,gliding phase and the second powered phase. To climb rapidly after the dropping,the maximum normal load was applied during the first powered phase. In order to satisfy the terminal constraints of the second powered phase,the time-varying longitudinal control variable was parameterized as a piece-wise polynomial,with a lateral energy management scheme based on triangle function. A parameter-programming problem with multiple phases and constraints was formulated,and the modified particle swarm optimization was employed to solve it. The simulation results show that the constraints of load,control and separation were well satisfied; this method can provide reference trajectories with high accuracy and computational efficiency for different constraints.

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备注/Memo

备注/Memo:
收稿日期:2019-03-19
作者简介:杨明(1985- ),男,博士研究生,研究方向为飞行器动力学、制导与控制。E-mail:yangmhitsat@126.com。
更新日期/Last Update: 2019-09-30