Periodic disturbance torque identification and compensation method

A technology of interference torque and compensation method, applied in the field of spacecraft, can solve problems such as satellite interference and vibration of flexible accessories, and achieve the effect of simple and reliable method

Active Publication Date: 2022-08-02
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

At the same time, if the frequency of the disturbance moment is close to some frequencies of the flexible accessories on the satellite, it may cause the vibration of the flexible accessories and cause greater interference to the satellite.

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  • Periodic disturbance torque identification and compensation method
  • Periodic disturbance torque identification and compensation method
  • Periodic disturbance torque identification and compensation method

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Embodiment Construction

[0031] Attached to the following Figures 1 to 5 The method for identifying and compensating the periodic disturbance torque, the electronic device and the readable storage medium proposed by the present invention will be further described in detail with reference to the specific embodiments. The advantages and features of the present invention will become more apparent from the following description. It should be noted that the accompanying drawings are in a very simplified form and all use inaccurate scales, and are only used to facilitate and clearly assist the purpose of explaining the embodiments of the present invention. For the purpose, features and advantages of the present invention to be more clearly understood, please refer to the accompanying drawings. It should be noted that the structures, proportions, sizes, etc. shown in the drawings in this specification are only used to cooperate with the contents disclosed in the specification, so as to be understood and re...

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Abstract

The invention provides a periodic interference torque identification and compensation method, which is used for phase identification and torque compensation of the periodic interference torque received by the satellite, applying a control torque with a fixed amplitude and a known period to the satellite, and compensating the moment on the satellite. The flywheel sends a feedforward compensation torque command to arbitrarily specify the initial phase of the compensation torque, including: measuring the satellite angular velocity in real time and extracting the angular velocity fluctuation range; when the angular velocity fluctuation range is greater than the first preset threshold, it is determined that phase shift control is required , carry out phase scanning with the initial phase as the starting point, during the phase scanning process, update the feedforward compensation torque according to the current phase; when the angular velocity fluctuation range is reduced to the second preset threshold, it is determined to end the phase movement control, and the current phase is For the disturbance torque phase, the feedforward compensation torque is updated according to the disturbance torque phase. The invention can realize the identification and compensation of the periodic interference moment of the satellite, and improve the control precision of the satellite.

Description

technical field [0001] The invention relates to the technical field of spacecraft, in particular to a periodic disturbance torque identification and compensation method. Background technique [0002] With the continuous development of space missions, satellites have more and more functions, and the control system design has higher and higher requirements for satellite control accuracy and attitude stability. For some large rotating parts on the satellite, when the satellite rotates at high speed, due to the existence of the offset of the center of mass, the satellite will be subjected to periodic disturbance torque, which will affect the attitude stability of the satellite to a certain extent. At the same time, if the frequency of the interference moment is close to some frequencies of the flexible attachment on the satellite, it may cause the vibration of the flexible attachment, which will bring greater interference to the satellite. [0003] Therefore, it is necessary to...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/24
CPCB64G1/244B64G1/245
Inventor 张文政陈殿印张泽涛刘刚张家巍
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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