微型姿控固体推力器阵列点火算法

刘旭辉; 方蜀州; 刘书杰; 罗莉; 权恩

微型姿控固体推力器阵列点火算法

1.
北京理工大学宇航学院, 北京 100081
2.
中国航天科技集团公司中国空间技术研究院北京控制工程研究所, 北京 100190

基金项目: "十一五"民用航天预先研究项目(微型固体推力器阵列技术研究)

计量
- 文章访问数: 1497
- HTML浏览量: 4
- PDF量: 9
- 被引次数: 0
出版历程
- 收稿日期: 2010-06-28
- 修回日期: 2010-08-23
- 刊出日期: 2011-07-28

Ignition algorithm of solid propellant micro-thruster array for attitude control

1.
School of Aerospace Engineering, Beijing Institute of Technology,Beijing 100081,China
2.
Beijing Institute of Control Engineering,China Academy of Space Technology, China Aerospace Science and Technology Corporation,Beijing 100190,China

摘要

摘要: 对用于微型卫星姿态控制的固体推力器阵列的组合点火问题进行了研究,分析了微型固体推力器阵列的工作性能,建立了组合点火问题的数学模型,设计了基值组合算法和阵列规划算法两种点火算法,并利用Matlab/Simulink对设计的算法进行了仿真.结果表明:阵列规划算法计算准确,快速有效,并且提高了阵列中推力器的利用率.
- 点火算法 /
- 姿态控制 /
- 微型固体推力器阵列 /
- 基值组合算法 /
- 阵列规划算法
Abstract: The study on ignition algorithm of solid propellant micro-thruster array for attitude control of micro-satellite was made and described in this paper.The performance capabilities of solid propellant micro-thruster array were analyzed and the theoretical model was set up,then two kinds of ignition algorithms, that were combined base value algorithm and array programming algorithm, were proposed and verified by simulation using Matlab/Simulink.The simulation shows that, array programming algorithm is accurate and fast, also can improve the utilization efficiency of thrusters in the array.
- ignition algorithm /
- attitude control /
- solid propellant micro-thruster array /
- combined base value algorithm /
- array programming algorithm

HTML

参考文献(14)

[1]	Larangot B,Conédéra V,Dubreuil P,et al.Solid propellant microthruster:an alternative propulsion device for nanosatellite //Proceedings of the Conference on Aerospace Energetic Equipment.Avignon France: ,2002:10-19.
[2]	Chaalane A,Larang t B,Rossi C,et al.Main directions of solid propellant micro-propulsion activity at LAAS .AIAA Paper 2004-6706,2004.
[3]	Kwon S,Lee J,Hoon L D.Design and performance evaluation of components of micro solid propellant thruster .Fort Lauderdale,USA:The 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit,2004.
[4]	Green A A.Demonstration and quantitative characterization of a MEMS fabricated propulsion system for the next generation of microspacecraft .AIAA-2001-0009,2001.
[5]	Zhang K L,Chou S K,Ang S S.Performance prediction of a novel solid-propellant microthruster[J].Journal of Propulsion and Power,2006,22(1):56-63.
[6]	Alexeenko A A,Levin D A,Girnelshein S F,et al.Numerical study of flow structure and thrust performance for 3-D MEMS-based nozzles .AIAA-2002-3194,2002.
[7]	Wu M H,Yetter R A,Yang V.Development and characterization of ceramic micro chemical propulsion and combustion systems .AIAA-2008-0966,2008.
[8]	尤政,张高飞,林杨,等.MEMS 固体化学推进器设计与建模研究[J].光学精密工程,2005,13(2):117-126. YOU Zheng,ZHANG Gaofei,LIN Yang,et al.Design and modeling of MEMS-based solid propellant propulsion[J].Optics and Precision Engineering,2005,13(2):117-126.(in Chinese)
[9]	屠善澄.卫星姿态动力学与控制[M].2版.北京:中国宇航出版社,1998:178-179.
[10]	Lewis D H,Jr.,Janson S W,Cohen R B,et al.Digital micropropulsion[J].Sensors and Actuators:Physical,2000,80(2):143-156.
[11]	章仁为.卫星轨道姿态动力学与控制[M].北京:北京航空航天大学出版社,1997:141-155.
[12]	张景瑞.灵敏航天器快速倾斜机动的MCMG参数和力矩估算[J].清华大学学报(自然科学版),2007,47(11):2037-2040. ZHANG Jingrui.Estimation of MCMG parameters and torques for rapid slewing maneuver of agile spacecraft[J].Journal of Tsinghua University(Science and Technology),2007,47(11):2037-2040.(in Chinese)
[13]	Rossi C,Do Conto T,Estève D C,et al.Design,fabrication and modelling of MEMS-based microthrusters for space application[J].Smart Materials and Structures,2001,10(6):1156-1162.
[14]	李国勇.最优控制理论及参数优化[M].北京:国防工业出版社,2006:118-123.