基于STLS的卫星惯量矩阵在轨估计

中国空间科学技术 ›› 2010, Vol. 30 ›› Issue (6): 31-38.

基于STLS的卫星惯量矩阵在轨估计

林佳伟^1,2, 王平¹

（1 北京控制工程研究所，北京 100190) (2 空间智能控制技术国家级重点实验室，北京 100190)

收稿日期:2009-06-17 修回日期:2009-08-10 出版日期:2010-12-25 发布日期:2010-12-25
通讯作者: 林佳伟现为中国空间技术研究院控制理论与控制工程专业在读博士研究生。
作者简介:林佳伟 1982年生，2006年获中国空间技术研究院导航、制导与控制专业硕士学位，现为中国空间技术研究院控制理论与控制工程专业在读博士研究生。研究方向为航天器在轨辨识。

In orbit Estimation of Satellite inertial matrix using STLS

LIN Jia-Wei^1,2, WANG Ping¹

(1 Beijing Institute of Control Engineering, Beijing 100190) (2 National Laboratory of Space Intelligent Control, Beijing 100190)

Received:2009-06-17 Revised:2009-08-10 Published:2010-12-25 Online:2010-12-25

摘要/Abstract

摘要： 提出了一种采用结构总体最小二乘（Structured total least squares, STLS）进行卫星惯量矩阵在轨估计的方法，与当前估计方法相比，该方法在考虑敏感器测量噪声时能获得一致估计。首先由动量守恒定律得到估计方程，针对该方程的特点定义了惯量矩阵的STLS估计，并使用结构总体最小范数（Structured total least norm, STLN）算法进行求解。证明了当噪声为高斯分布时该STLS估计为极大似然估计，给出了该STLS估计具有一致性的充分条件，仿真结果验证了文章所提估计方法的有效性。

关键词: 结构总体最小二乘, 结构总体最小范数, 极大似然估计, 一致估计, 惯量矩阵, 在轨估计, 卫星姿态控制

Abstract: Dynamics equations of inertial matrix estimation were deduced. The structured total least norm (STLN) algorithm was used to estimate the parameters. Theoretical analysis shows that the STLS solution is maximum likelihood estimate when the sensor noise is Gaussian. This method has two advantages over existing methods: sensor noise is considered and the consistency of the estimate is proved.

Key words: Structured total least squares, Structured total least norm, Maximum likelihood estimate, Consistent estimate, Inertial matrix, In orbit estimation, Satellite attitude control

林佳伟, 王平. 基于STLS的卫星惯量矩阵在轨估计[J]. 中国空间科学技术, 2010, 30(6): 31-38.

LIN Jia-Wei, WANG Ping. In orbit Estimation of Satellite inertial matrix using STLS[J]. Chinese Space Science and Technology, 2010, 30(6): 31-38.

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参考文献

［1］PECK M. Mass properties identification for spacecraft with powerful damping[C]. AAS Paper 99-430, AAS/AIAA Astrodynamics Specialist Conference, Girdwood, Alaska, 1999. ［2］PSIAKI L M. Estimation of a spacecraft's attitude dynamics parameters by using flight data\[J\]. Journal of Guidance, Control and Dynamics, 2005, 28(4): 594-603. ［3］LEE A Y, Wertz J A. In-flight estimation of the Cassini spacecraft's inertia tensor[J]. Journal of Spacecraft and Rockets, 2002, 39(1): 153-155. ［4］BORDANY R, STEYN W H, Crawford M. In-orbit estimation of the inertia matrix and thruster parameters of UoSAT12[C]. 14th AIAA/USU Conference on Small Satellites, Logan, 2000. ［5］TANYGIN S, WILLIAMS T. Mass property estimation using coasting maneuvers[J]. Journal of Guidance, Control, and Dynamics, 1997, 20(4): 625-632. ［6］PALIMAKA J, BURLTON B V. Estimation of spacecraft mass properties using angular rate gyro data[C]. AIAA/AAS Astrodynamics Conference, 1992. ［7］BERGMANN E V, DZIELSKI J. Spacecraft mass property identification with torque-generating control\[J\]. Journal of Guidance, Control, and Dynamics, 1990, 13(1): 99-103. ［8］WILSON E, SUTTER D W, Mah R W. Motionbased mass-and thrusterproperty identification for thrustercontrolled spacecraft[C]. Proceedings of the 2005 AIAA Infotech@Aerospace Conference, Arlington, Virginia, Sep. 2005. ［9］BERGMANN E V, WALKER B K, LEVY D R. Mass property estimation for control of asymmetrical satellites[J]. Journal of Guidance, Control, and Dynamics, 1987, 10(5): 483-491. ［10］PAYNTER S J, BISHOP R H. Adaptive nonlinear attitude control and momentum management of Spacecraft[J]. Journal of Guidance, Control, and Dynamics, 1997, 20(5): 1025-1032. ［11］AHMED J, COPPOLA V T, Bernstein D S. Adaptive asymptotic tracking of spacecraft attitude motion with inertia matrix identification[J]. Journal of Guidance, Control, and Dynamics, 1998, 21(5): 684-691. ［12］林佳伟, 王平. 零动量卫星惯量矩阵的在轨辨识[C]. 北京:中国航天可持续发展高峰论坛暨中国宇航学会第三届学术年会, 2008.LIN JIAWEI, WANG PING. Inorbit identification of the inertia matrix of zero momentum satellite[C]. Beijing:China Aerospace Summit Forum of Sustainable Development and 3rd Annual Meeting of Chinese society of Astronautics, 2008. ［13］DE MOOR B. Total least squares for affinely structured matrices and the noisy realization problem[J]. IEEE Trans. Signal Process. 1994, 42 (11): 3104-3113. ［14］LEMMERLING P. Structured total least squares: analysis, algorithms and applications[D]. ESAT/SISTA, K.U. Leuven, 2001. ［15］ABATZOGLOU T, MEMDEL J, HARADA G. The constrained total least squares technique and its application to harmonic superresolution[J]. IEEE Trans. Signal Process. 1991, 39(5): 1070-1087. ［16］ROSEN J, PARK H, GLICK J. Total least norm formulation and solution of structured problems[J]. SIAM J. Matrix Anal. Appl. 1996, 17(1): 110-126. ［17］KUKUSH A, MARKOVSKY I, VAN HUFFEL S. Consistency of the structured total least squares estimator in a multivariate errors-in-variables model[J]. J. Statist. Plann. Inference, 2005, 133 (2): 315-358. ［18］PINTELON R, SCHOUKENS J. System identification: a frequency domain approach[M]. New York: IEEE Press, 2001.

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