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A method for determining the effect of simulated in-orbit boundaries on spacecraft in-orbit dynamics

A technique for determining and simulating dynamic characteristics, applied in the direction of instruments, etc., can solve problems such as the influence of transfer function, and achieve the effect of improving the technical level

Active Publication Date: 2019-12-03
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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Problems solved by technology

A certain type of satellite in China did not use a specially designed simulated free boundary when performing micro-vibration tests, so the influence of boundary conditions was analyzed by comparing the transfer functions, and the results showed that the transfer function of the frequency band below 30Hz has a significant impact

Method used

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  • A method for determining the effect of simulated in-orbit boundaries on spacecraft in-orbit dynamics
  • A method for determining the effect of simulated in-orbit boundaries on spacecraft in-orbit dynamics
  • A method for determining the effect of simulated in-orbit boundaries on spacecraft in-orbit dynamics

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Embodiment Construction

[0033] The present invention will be described in further detail below in conjunction with the accompanying drawings, but this is only exemplary and not intended to limit the protection scope of the present invention.

[0034] see figure 1 , figure 1 A flow chart of the method of determining the influence of simulated on-orbit boundaries on the on-orbit dynamics of a spacecraft is shown. Wherein, the method for determining and simulating the influence of the on-orbit boundary on the spacecraft's on-orbit dynamic characteristics of the present invention includes the following main steps:

[0035] (1) Establish the finite element model of the free-boundary spacecraft on orbit.

[0036] According to the given spacecraft structural design parameters and ground micro-vibration test status, use general-purpose finite element modeling software, such as MSC. Modeling of materials, etc., to establish a finite element model of the spacecraft, such as figure 2 As shown in Fig. 1, chec...

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Abstract

The invention discloses a method for determining the influence of a simulated on-orbit boundary on on-orbit dynamic characteristics of a spacecraft. The method includes the steps of performing a modalanalysis and a micro-vibration dynamic response analysis by establishing finite element models of an on-orbit free-boundary spacecraft and a simulated free-boundary spacecraft respectively, extracting modal frequencies, modal shapes and micro-vibration responses of key measurement points of the spacecrafts, then, performing a deviation comparison and analysis on the obtained modal frequencies, mode shapes, and micro-vibration responses of the key measurement points, and determining the influence of the simulated on-orbit boundary on the on-orbit dynamic characteristics and responses of the spacecraft. The method of the invention realizes the quantitative evaluation of the influence of the simulated on-orbit free boundary on the on-orbit dynamic characteristics and dynamic responses of thespacecraft in a ground micro-vibration test of the spacecraft, and improves the ground micro-vibration test technology level of the spacecraft.

Description

technical field [0001] The invention belongs to the technical field of spacecraft micro-vibration tests, in particular to a determination method for simulating the influence of on-orbit free boundaries on spacecraft on-orbit dynamic characteristics during spacecraft ground micro-vibration tests. Background technique [0002] Micro-vibration refers to the high-speed rotation of the rotating parts on the star, the stepping motion of the drive mechanism of the large controllable component, the ignition of the thruster during the orbit change and attitude adjustment, and the disturbance induced by the alternating cold and heat of the large flexible structure entering and leaving the shadow, etc. Both will cause the star to produce a disturbance response with small amplitude and high frequency. Most spacecraft have micro-vibration disturbance sources. Due to the small amplitude and high frequency of micro-vibration dynamics environmental effects, they will not have obvious effect...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M7/00
CPCG01M7/00
Inventor 刘明辉岳志勇韩晓健何玲李栋冯国松王栋马功泊
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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