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描述函数理论及其在航天中的应用 被引量:1

Describing Function Theory and Its application in Aerospace
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摘要 在分析非线性系统时,描述函数作为一种古典的频域方法,具有许多优点。描述函数分析准则的修正赋予描述函数理论新的内涵,并为挠性航天器非线性喷嘴控制系统设计分析提供了一种有效手段,以谐波描述函数理论为基础,探讨了脉冲调制器描述函数的区域线性化,并对挠性航天器的姿态控制系统进行设计、分析,使航天器的姿态控制系统满足稳定性、控制精度等性能,并具有一定的鲁棒稳定性。 As a classical frequency method,Describing Function(DF)has numerous advantages when it is applied in analysis nonlinear systems.The modification of DF analysis principle gives a new content to the design of the nonlinear jet control system of flexible spacecraft.On the basis of harmonic DF theory,it explores the DF regional linearization.It designs and analyses the attitude control system of flexible spacecraft,as well satisfying its performance such as stability,control accuracy,furthermore,certain robust stability.
出处 《哈尔滨工业大学学报》 EI CAS CSCD 北大核心 1997年第6期42-45,49,共5页 Journal of Harbin Institute of Technology
基金 高等学校博士学科点专项科研基金
关键词 非线性控制 脉冲调制 描述函数 航天 姿态控制 Nonlinear control describing function pulsed modulate robust stability
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参考文献2

  • 1耿云海,九五全国飞行力学年会,1995年
  • 2李卫平,应用非线性控制,1992年,98页

同被引文献9

  • 1MILLAR R A, VIGNERON F R. Attitude stability of a pseudo- rate jet- controlled flexible spacecraft[Y]. Guid- ance and Control, 1979,2:111-118.
  • 2SCOTT E D. Pseudo-rate sawtooth-pulse reset control system analysis and design[y]. Journal of Spacecraft and Rockets, 1967,4(6) :781-785.
  • 3GUNTER MALICH. Effects of structural flexibility on a reaction jet satellite attitude control system[R]. Toronto: University of Toronto Institute for Aerospace Studies, 1975:1-33.
  • 4BRAIN DANOWSKY, PETER M THOMPSON. Nonlin- ear analysis of aeroservoelastic models with free play us- ing describing functions[J]. Journal of Aircraft, 2013, 50 (2) : 329-336.
  • 5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,1999:297.316.
  • 6KROVEL T D. Optimal tuning of PWPF modulator for at- titude control[D]. Trondheim: Norwegian University of Science and Technology, 2009.
  • 7WANG X SH, WANG D W, ZHU S Q, et al. Fractional describing function analysis of pwpf modulator[J]. Mathe- matical Problems in Engineering, 2013,34( 1 ) : 130-137.
  • 8MILLAR R A, VIGNERON F R. Attitude stability of flex- ible spacecraft which use dual time constant feedback lag network pseudo-rate control[C]//6th Communications Sat- ellite Systems Conference. Montreal: AIAA, 1976: 1-9.
  • 9李洋,仇原鹰,张军,彭福军.一种挠性航天器的自适应姿态控制与振动控制[J].振动与冲击,2009,28(12):178-182. 被引量:6

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