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A Calculation Method of On-orbit Modes for Satellites with Rotating and Flexible Solar Arrays

A calculation method and technology of flexible satellites, applied in the field of flexible dynamic analysis of satellites

Active Publication Date: 2018-10-30
SHANGHAI SATELLITE ENG INST
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Problems solved by technology

Literature [1] gives the calculation method of the fundamental frequency of the flexible spacecraft free-flying state system, and Literature [2] gives the calculation method of the flexible satellite in-orbit unconstrained mode, but they are all for the satellite in some fixed configurations. The analysis is carried out, and the analysis is not carried out when the sun array rotates to different angles

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  • A Calculation Method of On-orbit Modes for Satellites with Rotating and Flexible Solar Arrays
  • A Calculation Method of On-orbit Modes for Satellites with Rotating and Flexible Solar Arrays
  • A Calculation Method of On-orbit Modes for Satellites with Rotating and Flexible Solar Arrays

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[0016] The present invention will be described in detail below in conjunction with specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0017] Such as figure 2 As shown, the on-orbit modal calculation of the flexible satellite provided by the present invention mainly includes: the establishment of the structural dynamics characteristic equation of the whole star system, the calculation of the coefficients of the equation, and the model of the whole star system under different rotation angle positions of the flexible solar array. There are three parts to the state calculation.

[0018] 1. Establish the structural dynamics characteristi...

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Abstract

The invention provides an on-orbit modal computing method for a rotatable flexible solar array satellite; a whole-satellite structural dynamics characteristic equation is made based on the establishment of a flexible satellite dynamics hybrid coordinate equation; when a flexible solar array rotates to a different angle, satellite rotational inertia and translational coupling coefficient and rotational coupling coefficient of the solar array relative to the center of whole-satellite gravity are calculated and substituted to the characteristic equation to solve a characteristic value, namely corresponding whole-satellite on-orbit modal frequency of the solar array in each mode. The problem of estimating on-orbit mode of a flexible satellite is solved, and the on-orbit mode of the flexible satellite is an important input to whole-satellite dynamics frequency-spectrum planning and is applicable to avoidance of the coupling resonance problem possibly occurring after a satellite is on orbit.

Description

technical field [0001] The invention relates to the flexible dynamic analysis of satellites, more specifically, to an on-orbit modal calculation method for satellites with rotating flexible solar arrays. Background technique [0002] Satellites generally use solar arrays with flexible characteristics to provide energy. In order to obtain the vertical irradiation of sunlight, the solar array will rotate continuously during the satellite's orbit, which will change the topology of the satellite and the mode of the whole star will change periodically. The periodic moving parts on the satellite may be close to the mode of the whole star. If the flexible solar array rotates to a specific position, and the frequency of the mode frequency of the whole star on orbit is close to the frequency of the periodic moving parts on the satellite, coupling vibration may occur. Seriously affect the satellite attitude stability. Therefore, in the satellite development stage, it is necessary to...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/15
CPCG16Z99/00
Inventor 吕旺向明江刘培玲邓泓朱海江宋效正
Owner SHANGHAI SATELLITE ENG INST
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