固体助推火箭助推段能量管理分析 -- 西北工业大学,2013,31(4):584-589
论文:2013,Vol:31,Issue(4):584-589
引用本文:
闫晓东, 吕石, 贾晓娟. 固体助推火箭助推段能量管理分析[J]. 西北工业大学
Yan Xiaodong, Lv Shi, Jia Xiaojuan. Energy Management Analysis of Ascent Phase for Solid Rocket Booster[J]. Northwestern polytechnical university

固体助推火箭助推段能量管理分析
闫晓东1,2, 吕石1, 贾晓娟1
1. 西北工业大学 航天学院, 陕西 西安 710072;
2. 航天飞行动力学技术重点实验室, 陕西 西安 710072
摘要:
高超声速滑翔飞行器是未来超远程打击的重要手段之一,为了实现快速响应,高超声速滑翔飞行器采用小型固体助推火箭发射。由于小型固体助推火箭采用耗尽关机方式,为了适应大小不同射程,主动段需要进行能量管理。文章基于高斯伪谱法实现了固体助推火箭助推段的弹道优化设计,并针对影响能量管理能力的因素进行了分析。分析结果表明,能量管理飞行中,采用小推力有助于提高能量管理能力,增大攻角及其角速率约束也可显著提高能量管理能力。最后,给出了主动段能量管理的俯仰角模型,为固体助推火箭助推段能量管理和制导方法设计提供了依据。
关键词:    固体助推火箭    能量管理    弹道    优化   
Energy Management Analysis of Ascent Phase for Solid Rocket Booster
Yan Xiaodong1,2, Lv Shi1, Jia Xiaojuan1
1. College of Astronautics, Northwestern Polytecnical University, Xi'an 710072, China;
2. Science and Technology on Aerospace Flight Dynamics Laboratory, Northwestern Polytechnical University, Xi'an 710072, China
Abstract:
Hypersonic Glide Vehicles (HGVs) will be an important means for long-range striking.Small solid rocket booster is developed to launch the HGV to implement fast response.It is necessary to manage the final ener-gy in order to meet diverse range demands.This paper conducts the ascent trajectory optimization with Gauss Pseu-do-spectral Method (GPM), and then analyzes the factors which decide energy management capability.The analy-sis results show preliminarily that:(1) low thrust in energy management phase leads to a higher capability of final energy management;(2) large value of angle of attack (AoA) constraint and angle velocity of AoA constraint in-creases the capability of final energy management evidently.Finally, this paper presents a pitch angle model for en-ergy management;provides, we believe, the principles for the ascent guidance of solid rocket with energy manage-ment considered.
Key words:    Solid Rocket Booster    Energy Management    Trajectory    Optimization   
收稿日期: 2012-10-29     修回日期:
DOI:
基金项目: 航天支撑技术基金(2013-HT-XGD-014)资助
通讯作者:     Email:
作者简介: 闫晓东(1981-),西北工业大学讲师,主要从事飞行器动力学与制导研究。
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