Multi-redundancy satellite intelligent attitude control assembly and working method thereof

A multi-redundancy, satellite technology, applied in the aerospace field, can solve problems such as affecting the normal operation of spacecraft, inability to adjust attitude, and spacecraft failure.

Pending Publication Date: 2021-06-11
湖南揽月机电科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Obviously, when one of the reaction flywheels or the magnetic torquer fails, the attitude of the axis cannot be adjusted, th

Method used

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  • Multi-redundancy satellite intelligent attitude control assembly and working method thereof
  • Multi-redundancy satellite intelligent attitude control assembly and working method thereof
  • Multi-redundancy satellite intelligent attitude control assembly and working method thereof

Examples

Experimental program
Comparison scheme
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Embodiment Construction

[0034] like figure 1 As shown, this multi-redundant satellite intelligent attitude control component includes: a box body 1, a reaction flywheel group 2, a magnetic torque device group 3, a magnetic torque device coil 4, a control board 5, a gyroscope 6,

[0035] The box body is provided with a magnetic torque device coil installation groove 11 and a control board installation groove 12;

[0036] The reaction flywheel group includes the first reaction flywheel group, the second reaction flywheel group, the third reaction flywheel group and the fourth reaction flywheel group. These four reaction flywheel groups are respectively in the four corners of the box body. Each reaction flywheel group includes The X-axis reaction flywheel 21, the Y-axis reaction flywheel 22, and the Z-axis reaction flywheel 23, wherein the X-axis reaction flywheel and the Y-axis reaction flywheel are installed on the side wall of the box;

[0037] The magnetic torquer group performs magnetic unloading ...

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PUM

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Abstract

The invention discloses a multi-redundancy satellite intelligent attitude control assembly. The assembly comprises a box body (1), reaction flywheel sets (2), a magnetic torquer set (3), a magnetic torquer coil (4), a control panel (5) and gyroscopes (6), and the box body is provided with a magnetic torquer coil mounting groove (11) and a control panel mounting groove (12); the reaction flywheel sets include a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set which are arranged at the four corners of the box body respectively, each reaction flywheel set comprises an X-axis reaction flywheel (21), a Y-axis reaction flywheel (22) and a Z-axis reaction flywheel (23), and the X-axis reaction flywheel and the Y-axis reaction flywheel are installed on the side wall of the box body; the magnetic torquer set is used for performing magnetic unloading on the reaction flywheels and comprises an X-axis magnetic torquer and a Y-axis magnetic torquer which are mounted on a bottom plate of the box body and are symmetrically distributed; the magnetic torquer coil is installed in the magnetic torquer coil mounting groove of the box body and is in the Z-axis direction; the control panel is arranged in the center of the box body and is mounted in the control panel mounting groove; and the three gyroscopes are all installed on the bottom plate in the box body. The invention also provides a working method of the assembly.

Description

technical field [0001] The invention relates to the technical field of aerospace, in particular to a multi-redundant satellite intelligent attitude control component and a working method of the multi-redundant satellite intelligent attitude control component. Background technique [0002] Attitude control actuators of spacecraft such as satellites, earth observation platforms, spacecraft, and space telescopes require small size, light weight, long life, low power consumption, and high reliability. At present, the spacecraft attitude control system includes: reaction flywheel, magnetic torque device, nine-axis sensor actuator, etc.; reaction flywheel, magnetic torque device, generally use three as a group to control the attitude of the spacecraft in three axes . Obviously, when one of the reaction flywheels or the magnetic torquer breaks down, the attitude of the axis cannot be adjusted, thereby affecting the normal operation of the entire spacecraft, and even causing the fa...

Claims

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Application Information

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IPC IPC(8): B64G1/24B64G1/28B64G1/10
CPCB64G1/244B64G1/283B64G1/10B64G1/369
Inventor 杜金榜侯建军
Owner 湖南揽月机电科技有限公司
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