|
|
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。
|
|
| 相关功能 |
|
|
|
|
| 作者相关文章 |
|
| 闫晓东 在本刊中的所有文章 |
| 吕石 在本刊中的所有文章 |
| 贾晓娟 在本刊中的所有文章 |
|
|
|
|
|
|
|
|
参考文献: |
|
|
[1] George Richie.The Common Aero Vehicle-Space Delivery System of the Future.AIAA Space Technology Conference & Exposition, Albuquerque, NM, 1999
[2] Terry Phillips.A Common Aero Vehicle Model, Description, and Employment Guide.http: //www.dtic.Mil/matris/sbir/ sbir041/srch/af031a.doc, 2003: 1-10
[3] Julia Rothman, Erika Siegenthaler.Responsive Space Launches the F215 Microsatellite Launch Vehicle.AIAA 1st Responsive Space Conference.Los Angeles, 2003
[4] Scott Schoneman, Lou Amorosi, Mike Laidley, et al.Minotaur I Demonstration of Responsive for the TacSat22 Mission.AIAA5th Responsive Space Conference.Los Angeles, 2007
[5] 闫晓东, 唐 硕.亚轨道飞行器返回轨道设计方法研究.宇航学报, 2008, 29(2): 467-471 Yan Xiaodong, Tang Shuo.An Alternative Method of Entry Trajectory Design for Suborbital Launch Vehicle.Journal of Astronautics, 2008, 29(2): 467-471 (in Chinese)
[6] 闫晓东, 唐 硕.基于反馈线性化的亚轨道飞行器返回轨道跟踪方法.宇航学报, 2008, 29(5): 1546-1555 Yan Xiaodong, Tang Shuo.Entry Tracking Law for Suborbital Launch Vehicle via Feedback Linearization.Journal of Astronautics, 2008, 29(5): 1546-1555 (in Chinese)
[7] Ross I M, Fahroo F.A Perspective on Methods for Trajectory Optimization.Proceedings of the AIAA/AAS Astrodynamics Specialist Conference, Monterey, 2002 |
|
|
|
|
|
|
|
