Satellite posture all-round controlling method based on magnetic moment device and flywheel

A technology of magnetic torquer and satellite attitude, which is applied in the field of all-round attitude control during the orbiting stage of satellites by using magnetic torquer and flywheel, which can solve problems such as low reliability and short life, and achieve improved safety, reduced power consumption, Effects of Improving Reliability and On-Orbit Lifetime

Inactive Publication Date: 2011-01-05
HARBIN INST OF TECH
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] In order to solve the problems of low reliability and short service life of the existing satellite attitude omnidirectional control te

Method used

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  • Satellite posture all-round controlling method based on magnetic moment device and flywheel
  • Satellite posture all-round controlling method based on magnetic moment device and flywheel
  • Satellite posture all-round controlling method based on magnetic moment device and flywheel

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Experimental program
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specific Embodiment approach 1

[0014] Specific implementation mode 1. Combination figure 1 , 2 image 3 with Figure 4 Describe this embodiment, the omni-directional satellite attitude control method based on the magnetic torque device and the flywheel, the specific process is as follows:

[0015] Set the controller parameters according to the control system requirements; the controller parameters include satellite controller differential coefficient vector Kd=[Kdx Kdy Kdz] T , Satellite controller proportional coefficient vector Kp=[Kpx Kpy Kpz] T , Vector dead zone uncontrolled angle value Theta and satellite angular velocity limit coefficient Limit60 during attitude capture;

[0016] Close the control command sent to the magnetic torque device 4 at the T-t moment of each control cycle until the end of this cycle, then utilize the magnetometer 2 to measure the vector Bb=[Bbx Bby Bbz] of the local magnetic field strength in the satellite body coordinate system T , utilize the gyroscope 1 to measure th...

specific Embodiment approach 2

[0022] Specific implementation mode 2. This implementation mode is a further description of specific implementation mode 1. According to the requirements of the control system, the specific process of setting the controller parameters is as follows:

[0023] Set satellite controller differential coefficient vector Kd and satellite controller proportional coefficient vector Kp according to control theory:

[0024] Kp=Wc 2 *Ib,

[0025] Kd=2keci*Wc*Ib

[0026] Among them, Wc is the system frequency, keci is the system damping ratio, Ib=[Ibx Iby Ibz] T is the moment of inertia vector of the satellite;

[0027] The limit coefficient Limit60 of the satellite angular velocity when setting the attitude capture is:

[0028] Limit60=2keci*WLimit / Wc

[0029] Among them, Wlimit is the upper limit value of attitude maneuver angular velocity;

[0030] Assuming that under the damping condition of the magnetic torque device 4, the vector dead zone non-control angle value Theta is set a...

specific Embodiment approach 3

[0031] Specific embodiment three, combine image 3 This embodiment is described. This embodiment is a further description of Embodiment 2, and the vector dead zone non-control angle value Theta is 18°.

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Abstract

The invention discloses a satellite posture all-round controlling method based on a magnetic moment device and a flywheel, relating to an all-round posture controlling method for completing a satellite orbit-injection phase by using the magnetic moment device and the flywheel. The invention solves the problems of low reliability and short service life of the traditional satellite posture all-round controlling technology. The satellite posture all-round controlling method comprises the following steps of: 1, setting controller parameters according to the requirement of a control system; 2, measuring a geomagnetic field intensity vector Bb, a satellite angular velocity vector Wb and a solar azimuth, and sending the measured data to a satellite controller; 3, calculating an expected control moment vector Tm and a control magnetic moment vector Mm, and sending the control magnetic moment vector Mm to the magnetic moment device; 4, acquiring an effective solar azimuth vector Alfa; 5, calculating a control input moment vector Tw and sending to the flywheel; and 6, jointly completing the satellite posture all-round control by the magnetic moment device according to the control magnetic moment vector Mm and the flywheel according to the control input moment vector Tw. The invention is suitable for the field of satellite posture control.

Description

technical field [0001] The invention relates to the technical field of spacecraft attitude control, in particular to a method for controlling the omnidirectional attitude of a satellite in orbit by using a magnetic torque device and a flywheel. Background technique [0002] At present, small satellites have broad application prospects in many fields and are favored by countries all over the world. The initial attitude capture and all-round attitude control of satellites generally use jet control. Its main task is to control the attitude of the satellite in each working stage to ensure The accuracy of attitude pointing, the current attitude control system is complex in configuration, heavy in weight, and high in cost, and its application on small satellites is subject to certain restrictions. Using magnetic torquer and flywheel to capture initial attitude and all-round attitude is the core technology of long-life and high-reliability small satellites, and it has always been t...

Claims

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Application Information

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IPC IPC(8): B64G1/32B64G1/28
Inventor 耿云海陈雪芹曹喜滨孙兆伟李东柏李化义
Owner HARBIN INST OF TECH
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