含多正弦扰动的航天器无拖曳控制系统性能极限研究
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摘要
本文研究了航天器无拖曳控制系统的性能极限问题.将空间环境扰动描述为一个阶跃分量、一个平稳随机分量和多个正弦分量的线性组合,利用残余非保守力的稳态方差度量扰动抑制性能,并运用Wiener-Hopf设计方法求解最小灵敏度函数.为确保残余非保守力的渐近平稳性,将最小灵敏度函数表示为反馈系统的频域拓扑结构,并推导了闭环系统的极限指标.结合无拖曳控制指标,讨论了加速度计模式下的传感器、执行器的指标分解问题.
This paper is to contribute to the understanding of performance limitations for spacecraft drag-free control system. Environmental disturbance is modeled as a linear combination of a step component, a stationary stochastic component and several sinusoids with different frequencies. Disturbance rejection is measured by the steady-state variance of the residual non-gravitational force, and Wiener-Hopf design method is used to solve the minimizing sensitivity function. To guarantee the asymptotic stationary of the residual non-gravitational force, the minimizing sensitivity function accounting for the toplogical structure of the feedback system is used to derive the limiting performance. By using the drag-free control requirement, performance budgeting of actuator and sensor in accelerometer mode are discussed.
This paper is to contribute to the understanding of performance limitations for spacecraft drag-free control system. Environmental disturbance is modeled as a linear combination of a step component, a stationary stochastic component and several sinusoids with different frequencies. Disturbance rejection is measured by the steady-state variance of the residual non-gravitational force, and Wiener-Hopf design method is used to solve the minimizing sensitivity function. To guarantee the asymptotic stationary of the residual non-gravitational force, the minimizing sensitivity function accounting for the toplogical structure of the feedback system is used to derive the limiting performance. By using the drag-free control requirement, performance budgeting of actuator and sensor in accelerometer mode are discussed.
引文
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[12]LANGE B.The drag-free satellite[J].AIAA Journal,1964,2(9):1590–1606.
[13]LI J,BENCZE W J,DEBRA D B,et al.On-orbit performance of gravity probe B drag-free translation control and orbit determination[J].Advances in Space Research,2007,40(1):1–10.
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[15]CHEN J,QIU L,TOKER O.Limitations on maximal tracking accuracy[J].IEEE Transactions on Automatic Control,2000,45(2):326–331.
[16]CANUTO E,MOLANO A,MASSOTTI L.Drag-free control of the GOCE satellite:noise and observer design[J].IEEE Transactions on Control Systmes Technology,2010,18(2),501–509.
[17]NG C N,YOUNG P C.Recursive estimation and forecasting of nonstationary time series[J].Journal of Forecasting,1990,9(9):173–204.
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[19]FICHTER W,SCHEICHER A.Closed loop performance and limitations of the LISA pathfinder drag-free control system[C]//AIAA Guidance,Navigation and Control Conference and Exhibit.Hilton Head,South Carolina:AIAA,2007:1–17.
[2]ARMANO M,AUDLEY H,AUGERC G,et al.The LISA pathfinder mission[J].Journal of Physics:Conference Series,2015,610(1):1–18.
[3]CANUTO E.Drag-free and attitude control for the GOCE satellite[J].Automatica,2008,44(7):1766–1780.
[4]YOULA D C,BONGIORNO J J,JABR H A.Modern Wiener-Hopf design of optimal controllers,part I:the single-input-output case[J].IEEE Transactions on Automatic Control,1976,21(1):3–13.
[5]DAVISON D E,KABAMBA P T,MEERKOV S M.Limitations of disturbance rejection in feedback systems with finite bandwidth[J].IEEE Transactions on Automatic Control,1999,44(6):1132–1144.
[6]MIDDLETON R H.Trade-offs in linear control system design[J].Automatica,1991,27(2):281–292.
[7]GOODWIN G C,SALGADO M E,YUZ J I.Performance limitations for linear feedback system in the presence of plant uncertainty[J].IEEE Transastions on Automatic Control,2003,48(8):1312–1319.
[8]BAKHTIAR T,HARA S.H2 regulation performance limitations for SIMO linear time-invariant feedback control systems[J].Automatica,2008,44(3):659–670.
[9]MARTINS N C,DAHLEH M A,DOYLE J C.Fundamental limitations of disturbance attenuation in the presence of side information[J].IEEE Transactions on Automatic Control,2008,52(1):56–66.
[10]MARTINS N C,DAHLEH M A.Feedback control in the presence of noisy channel:“Bode-like”fundamental limitations of performance[J].IEEE Transactions on Automatic Control,2008,53(7):1604–1615.
[11]LI D P,HOVAKIMYAN N.Bode-like integral for stochastic switched systems in the presence of limited information[J].Automatica,2013,49(1):1–8.
[12]LANGE B.The drag-free satellite[J].AIAA Journal,1964,2(9):1590–1606.
[13]LI J,BENCZE W J,DEBRA D B,et al.On-orbit performance of gravity probe B drag-free translation control and orbit determination[J].Advances in Space Research,2007,40(1):1–10.
[14]GUILHERME M S,FILHO W C L,THEIL S.Strategies for in-orbit calibration of drag-free control systems[J].Aerospace Science and Technology,2008,12(5):365–375.
[15]CHEN J,QIU L,TOKER O.Limitations on maximal tracking accuracy[J].IEEE Transactions on Automatic Control,2000,45(2):326–331.
[16]CANUTO E,MOLANO A,MASSOTTI L.Drag-free control of the GOCE satellite:noise and observer design[J].IEEE Transactions on Control Systmes Technology,2010,18(2),501–509.
[17]NG C N,YOUNG P C.Recursive estimation and forecasting of nonstationary time series[J].Journal of Forecasting,1990,9(9):173–204.
[18]ASTROM K J.Introduction to Stochastic Control Theory[M].New York and London:Academic Press,1970.
[19]FICHTER W,SCHEICHER A.Closed loop performance and limitations of the LISA pathfinder drag-free control system[C]//AIAA Guidance,Navigation and Control Conference and Exhibit.Hilton Head,South Carolina:AIAA,2007:1–17.