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Kalman filtering identification method of rotational inertia of large-scale flexible spacecraft

A flexible spacecraft and Kalman filter technology, applied in the field of spacecraft rotational inertia identification, can solve the problems of poor practicability and achieve the effect of good practicability and enhanced accuracy

Inactive Publication Date: 2019-06-11
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0003] In order to overcome the shortcomings of the poor practicability of the existing identification methods for the moment of inertia of spacecraft, the present invention provides a Kalman filter identification method for the moment of inertia of large-scale flexible spacecraft

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  • Kalman filtering identification method of rotational inertia of large-scale flexible spacecraft
  • Kalman filtering identification method of rotational inertia of large-scale flexible spacecraft
  • Kalman filtering identification method of rotational inertia of large-scale flexible spacecraft

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Embodiment Construction

[0059] refer to Figure 1-7 . The specific steps of the Kalman filter identification method for the moment of inertia of the large-scale flexible spacecraft of the present invention are as follows:

[0060] Step 1: Determine the observation equation between the identification parameters and the input and output measurement data.

[0061] Express the moment of inertia parameter to be identified as the inverse form of the parameter to be identified,

[0062]

[0063] x is a vector to be estimated, and each element corresponds to the six elements of the inverse matrix of the inertia matrix I. E.g, I corresponding to the inverse matrix of the inertia matrix xx corresponding elements.

[0064] For large-scale flexible spacecraft, the dynamic equation under small-angle maneuvering is

[0065]

[0066] Among them, I is the moment of inertia of the satellite, the parameter to be identified; is the angular acceleration of the spacecraft, P rot is the rotational rigid-fl...

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Abstract

The invention discloses a Kalman filtering identification method of rotational inertia of a large-scale flexible spacecraft for solving the technical problem that the existing identification method ofthe rotational inertia of the spacecraft has poor practicability. The technical scheme is as follows: for the large-scale flexible spacecraft, an observation equation is determined according to a dynamic equation under small angle maneuvering. Then, a PD controller using closed-loop control excitation is adopted to control a satellite to rotate for a set angle. According to the observation equation, the rotational inertia is identified by using the Kalman filtering. Since the Kalman filtering method is adopted, the rotational inertia is identified by considering the influence factors of the flexible coupling of the large-scale flexible spacecraft, and the in-orbit identification of the rotational inertia is achieved. The relatively large influence on the system caused by the large rigid-flexible coupling coefficient of the spacecraft, a flexible vibration attitude angle and an attitude angle velocity is reduced. The identified rotational inertia provides a basis for subsequent attitude control, enhances the accuracy of the spacecraft attitude control system, and has good practicability.

Description

technical field [0001] The invention relates to a method for identifying the moment of inertia of a spacecraft, in particular to a method for identifying the moment of inertia of a large-scale flexible spacecraft with a Kalman filter. Background technique [0002] The literature "Xu Wenfu, He Yong, Wang Xueqian, Liang Bin, Liu Yu. On-orbit identification method of spacecraft mass characteristic parameters [J]. Acta Astronautics, 2010, 31(8): 1906-1914" discloses a rigid body dynamics The model is based on the nonlinear optimization method based on PSO, which converts the parameter identification problem into a global optimization problem of the nonlinear system to identify the moment of inertia parameters of the spacecraft. The method described in the literature is applicable when the satellite is a rigid body, and does not consider the influence of the flexible coupling of large-scale flexible spacecraft on the identification of moment of inertia parameters; for large-scale...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M1/10
Inventor 刘睿周军李公军张军
Owner NORTHWESTERN POLYTECHNICAL UNIV