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Self-compensating method for dynamic and still unbalancing disturbance moment of satellite rotating part

A technology of disturbing torque and rotating parts, which is applied in the direction of motor vehicles, aerospace vehicle guidance devices, aerospace equipment, etc., can solve the problems of high configuration and control performance requirements of the attitude control system, and great difficulty in structural trimming, etc., to achieve Simplify the development process, facilitate engineering realization, and achieve low-cost effects

Inactive Publication Date: 2017-04-26
SHANGHAI ENG CENT FOR MICROSATELLITES
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  • Application Information

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Problems solved by technology

However, for rotating parts with large inertia, fast speed and irregular shape, it is very difficult to trim the structure. After trimming, there will still be a large dynamic and static unbalance interference in the rotating surface. If the satellite attitude control system is used to actively suppress it, for The configuration and control performance requirements of the attitude control system are very high

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  • Self-compensating method for dynamic and still unbalancing disturbance moment of satellite rotating part
  • Self-compensating method for dynamic and still unbalancing disturbance moment of satellite rotating part
  • Self-compensating method for dynamic and still unbalancing disturbance moment of satellite rotating part

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[0088] This example describes the specific implementation of the embodiment of the present invention for a specific type of satellite.

[0089] The structure of the satellite includes rotating parts. When the satellite is in orbit, the working speed of the rotating part is 20rpm, that is, the rotational angular velocity is ω 0 =2π / 3rad / s. Rotating components are balanced using a dynamic balancing machine.

[0090] According to the technology of the present invention, through the following steps, the dynamic and static unbalanced disturbance moment of the satellite rotating parts is self-compensated.

[0091] Step 1, install the first offset momentum wheel and the second offset momentum wheel on the surface of the rotating component, the rotation axes of the two offset momentum wheels are all perpendicular to the rotation axis of the rotating component, and the rotation axis of the first offset momentum wheel is in line with O c The included angle of X is φ=0°, and the rotati...

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Abstract

The invention discloses a self-compensating method for a dynamic and still unbalancing disturbance moment of a satellite rotating part. The dynamic and still unbalancing disturbance moment produced by quick rotating of the rotating part on a satellite can influence the stability of the satellite and reduce the control precision of the satellite. A traditional method for eliminating a dynamic and still unbalancing disturbance moment of a rotating part comprises the steps that the rotating part is subjected to dynamic balancing, and then, active control over dynamic and still unbalancing disturbance is conducted through a satellite attitude control system. The traditional method has limitation to application of rotating parts which are large in inertia, high in rotating speed and irregular in shape. According to the self-compensating method for the dynamic and still unbalancing disturbance moment of the satellite rotating part, two small bias momentum wheels are arranged on the rotating part of the satellite, and the rotating speed of the two bias momentum wheels is set according to the on-orbit calibration result of dynamic and still unbalancing disturbance so that the dynamic and still unbalancing disturbance moment produced during rotating of the rotating part can be eliminated. The self-compensating method is simple, obvious in effect and low in cost, and engineer achieving can be facilitated.

Description

technical field [0001] The invention belongs to the technical field of spacecraft attitude control, and relates to a method for eliminating dynamic and static unbalanced disturbance moments of a satellite with rotating parts. Background technique [0002] With the continuous expansion of the application field of modern satellites, the loads on the star, especially the loads of the detection application, have an increasing demand for the rotating mechanism, and there are more and more rotating parts on the star, and the inertia requirements of the rotating parts are getting larger and larger. , the rotational speed requirement is getting faster and faster. [0003] When the rotating parts on the star rotate, they will form the interference torque and angular momentum in the axial direction of the rotation axis, which can be offset by configuring the balance wheel on the satellite body and synchronously counter-rotating. However, the center of mass deviation and uneven mass d...

Claims

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Application Information

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IPC IPC(8): B64G1/28
CPCB64G1/285
Inventor 谢祥华严玲玲张锐刘剑胡志强祁海铭赵璟本立言何夏维
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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