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Rotating member disturbance compensation method based on momentum wheel

A technology for rotating parts and disturbance compensation, applied in the direction of instruments, adaptive control, control/adjustment systems, etc., can solve the problems of not considering the inconsistency between the control cycle and the compensation cycle, and not mentioning the implementation method of the on-orbit project, so as to achieve the realization of on-orbit The effect of rail real-time compensation control

Active Publication Date: 2013-08-07
BEIJING INST OF CONTROL ENG
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AI Technical Summary

Problems solved by technology

[0007] The above method has the following disadvantages: the disturbance compensation technology is based on the compensation of component motion design laws, but does not involve the disturbance compensation of dynamic unbalance and static unbalance. The problem that the control cycle is inconsistent with the compensation cycle

Method used

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  • Rotating member disturbance compensation method based on momentum wheel
  • Rotating member disturbance compensation method based on momentum wheel
  • Rotating member disturbance compensation method based on momentum wheel

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Embodiment Construction

[0032] Such as figure 1 As shown, the present invention provides a technique for compensating the disturbance of rotating components based on the momentum wheel, which includes the following steps:

[0033] (1) Perform interference analysis on the rotating parts;

[0034] (2) determining the disturbance compensation function of the rotating part;

[0035] (3) Design an implementation method of interference compensation based on time-slice interrupt calls;

[0036] (4) Fusion of compensation torque and attitude control torque;

[0037] (5) Determine the way to output the control voltage to the I / O port of the momentum wheel, so as to realize the interference compensation of the rotating parts.

[0038] There are two ways to perform interference analysis on the rotating parts:

[0039] 1) Analyze according to the principle of dynamics; perform dynamic analysis on the rotating part according to the installation position, direction of rotation, speed and dynamic / static unbalan...

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Abstract

The invention provides a rotating member disturbance compensation method based on a momentum wheel. The rotating member disturbance compensation method includes (1) performing disturbance analysis to the rotating member; (2) determining disturbance compensation functions of the rotating member; (3) designing a realizing method of invoked disturbance compensation on the basis of time slice interruption; (4) performing fusion of a compensation torque and an attitude control torque; and (5) determining a manner of outputting control voltage to an I / O (input / output) port of the momentum wheel so as to realize the disturbance compensation to the rotating member. By the rotating member disturbance compensation method, attitude control accuracy is improved while fuel consumption of jet propulsion system compensation is reduced; since attitude control periods and control computer time slice interrupt laws are combined in the rotating member disturbance compensation method, hardware sources are fully utilized; and the problem of inconsistence of control periods and compensation periods is solved through a manner of combination of hardware and software, and compensation control in orbit in real time is realized.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control, and relates to a method for compensating interference of rotating parts based on momentum wheels. Background technique [0002] With the continuous improvement of space mission requirements, the structure of spacecraft is becoming more and more complex, while the control performance index is getting higher and higher. This type of spacecraft often has rotating parts, such as microwave scatterometers, microwave radiometers, scanning mirrors, etc. The rotation or movement of the parts will introduce interference. If the interference directly acts on the spacecraft platform without compensation, it will reduce the attitude control system. The stability and pointing accuracy of the spacecraft can even stimulate the vibration of flexible accessories (such as solar panels), causing the attitude of the spacecraft to oscillate. For this reason, measures must be taken to compensate for the inter...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B13/04
Inventor 王新民袁军张俊玲王胜刚綦艳霞姚宁程莉赵性颂周剑敏张辉
Owner BEIJING INST OF CONTROL ENG
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