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迭代制导情况下姿态控制系统稳定性分析方法研究 被引量:4

The Research on Stability Analysis of Attitude Control System in the Case of Iterative Guidance
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摘要 为了提高火箭的入轨精度和轨道适应能力,我国在新一代运载火箭末级中采用了迭代制导技术,俯仰、偏航程序角根据火箭运动状态和目标轨道参数实时变化,目前工程设计中仍按照固定程序角方式开展稳定性分析。本文推导出迭代制导程序角与火箭速度、位置之间的线性关系式,在国内首次提出了迭代制导情况下的稳定性分析方法,并以新一代运载火箭为例进行了实例计算,结果表明此分析方法正确、可行,具有一定的参考价值。 Aiming at the improvement of in-orbit precision and orbit adaptability, the iterative guidance technology is adopted in new generation launch vehicle of China. The pitch and yaw program attitude angles are changed, which are based on launch vehicle movement states and target orbit parameters in real time, but the stability analysis is still developed according to the form of fixed program attitude angles in to- day' s engineer design. In this paper, the linear relation functions of iterative guidance program angles and launch vehicle velocity and position are deduced, and the method of stability analysis in the case of iterative guidance is presented firstly in China. Then, the calculation example of new generation launch vehicle is demonstrated. The results indicate that the analysis method is correct and advisable, which has fair reference value.
作者 王辉 张宇
出处 《航天控制》 CSCD 北大核心 2012年第3期7-11,共5页 Aerospace Control
关键词 迭代制导 姿态控制系统 运载火箭 稳定性分析 Iterative guidance Attitude control system Launch vehicle Stability analysis
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  • 1彭献,刘晓晖,霍兵勇.最优控制理论在人车路磁流变半主动悬架中的应用[J].动力学与控制学报,2007,5(2):183-188. 被引量:3
  • 2李华滨.真空段迭代制导方法研究(学位论文)[M].,1992,3..
  • 3程国采.运载火箭显示制导的最优制导规律[J].宇航学报,1985,(6).
  • 4土星运载火箭的迭代制导概念[J].国外导弹技术,1980,5.
  • 5凌德海.近代制导[M].国防科大,1982年7月..
  • 6土星火箭迭代制导介绍[J].国外导弹技术,1980,3.
  • 7徐延万.控制系统(上).北京:中国宇航出版社,2005.
  • 8Deniel T. Martin And Russell F. Sievers. Saturn V Guidance,Navigation,and Targeting. J. SPACECRAFT, VOL. 4, NO. 7.
  • 9韩祝斋.用于大型运载火箭的迭代制导方法[J].宇航学报,1983,(1).
  • 10李华滨,李伶.小型固体运载火箭迭代制导方法研究[J].航天控制,2002,20(2):29-37. 被引量:17

共引文献58

同被引文献30

  • 1邱吉宝.航天器计算结构动力学展望[J].计算结构力学及其应用,1993,10(2):219-227. 被引量:8
  • 2陈世年.控制系统设计[M].北京:中国宇航出版社,2005:407.
  • 3张最良.弹道导弹的制导与控制[M].长沙:国防科技大学出版社,1981..
  • 4徐延万,余显昭,王永平,等.导弹与航天丛书控制系统(上)[M].北京:宇航出版社,1989.
  • 5Doris C Chandler,Isaac E Smith.Development of the Iterative Guidance Mode with Its Application to Various Vehicles and Missions[J].Journal of Spacecraft and Rockets,1967,4(7):898-903.
  • 6龙乐豪.液体弹道导弹与运载火箭系列——总体设计(上)[M].北京:中国宇航出版社,1989:15-30.
  • 7Berglund M D,Marin D, Wilkins M. The next'generation heavy-lift vehicle — The inaugural flightof the EELV delta IV heavy [C] // Collection ofTechnical Papers — AIAA Space 2005 Conferenceand Exposition. Reston: AIAA, 2005:817-825.
  • 8Slazer F A, Harvey J C,Sirko R J,etal. Delta IVlaunch vehicle growth options to support NASA, sspace exploration vision [J]. Acta Astronautica,2005,57(2-8):604-613.
  • 9Choi H D,Bang H. Adaptive control approach tothe attitude control of a flexible rocket [J]. ControlEngineering Practice, 2000,8(9) :1003-1010.
  • 10Voinot O, Apkarian P,Alazard D. Gain-schedulingcontrol of the launcher in atmospheric flight vialinear-parameter varying techniques [C] // AIAAGuidance, Navigation, and Control Conference andExhibit. Reston:AIAA, 2002.

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