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Method for inhibiting vibration of satellite solar panel substrates by aid of solid micro-thruster arrays

A micro-thrust and solar panel technology, which is applied to the vibration reduction of aerospace vehicles, aircraft, motor vehicles, etc., can solve the problems of large size and mass, small driving force, etc., to simplify the design process, solid micro-thrust less effect

Inactive Publication Date: 2018-02-23
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Existing satellite active vibration control actuators are too large in size and mass to be installed on the satellite solar panels (for example, the jet actuator needs a large gas storage tank), and the driving force is too small (for example, the piezoelectric sheet actuates device) problem

Method used

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  • Method for inhibiting vibration of satellite solar panel substrates by aid of solid micro-thruster arrays
  • Method for inhibiting vibration of satellite solar panel substrates by aid of solid micro-thruster arrays
  • Method for inhibiting vibration of satellite solar panel substrates by aid of solid micro-thruster arrays

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Embodiment

[0103] A method of using a solid micro-thruster array of the present invention to suppress the vibration of satellite solar panels, the process is as follows image 3 shown, including the following steps:

[0104] Step 1: Install the solid micro-thruster array on the front and back sides of the selected position of the satellite solar panel, and configure the vibration sensor and the solid micro-thruster array in alignment.

[0105] The present invention will use the independent mode space control method to convert the first two order bending modes of the solar panel, such as Figure 4 , as the controlled mode, and the remaining modes as the residual modes. The vibration equation of the solar panel in the modal coordinate system can be written as:

[0106]

[0107] Among them, ξ i , ω i and r i Respectively represent the damping ratio, natural frequency and modal force of the i-th mode of the sailboard, q i is the i-th modal coordinate and satisfies the modal superpos...

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Abstract

The invention discloses a method for inhibiting vibration of satellite solar panel substrates by the aid of solid micro-thruster arrays. The method has the advantages that flexible satellite attitudekinetic equations with the solid micro-thruster arrays are created, joint active vibration controllers for the solid micro-thruster arrays and attitude flywheels are designed, accordingly, the vibration of the satellite solar panel substrates can be quickly inhibited, flexible satellites can be quickly stabilized after being disturbed, and the method is speedy.

Description

technical field [0001] The invention belongs to the field of active vibration control of spacecraft, and relates to the vibration control of satellite flexible accessories, in particular to a method for suppressing vibration of satellite solar panels by using a solid micro-thruster array. Background technique [0002] With the widespread application of composite materials on satellites, the mass of the satellite's flexible accessories, such as antennas and solar panels, will be reduced. However, these lightweight structures have the characteristics of low damping and low natural frequency, which are easy to excite undesired vibrations after satellite attitude maneuvers or disturbances, resulting in reduced attitude stability and damage to flexible structures. Due to the continuous improvement of the performance requirements of spacecraft, the traditional passive vibration control can no longer meet the demand, which makes the closed-loop active vibration control develop rapi...

Claims

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Application Information

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IPC IPC(8): B64G1/44
CPCB64G1/426B64G1/44B64G1/228
Inventor 杨博樊子辰苗峻赵晓涛
Owner BEIHANG UNIV
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