Spacecraft high-accuracy speediness attitude maneuver method based on single gimbal control moment gyro (SGCMG) and reaction wheel (RW)

An attitude maneuvering and spacecraft technology, applied in attitude control, instrumentation, adaptive control, etc., can solve problems such as large control torque, difficult RW to achieve expected results, and low control accuracy

Active Publication Date: 2013-05-08
HARBIN INST OF TECH
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Problems solved by technology

The characteristic is that the generated control torque is large, but the control accuracy is relatively low, and it is generally used in the attitude control of lar

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  • Spacecraft high-accuracy speediness attitude maneuver method based on single gimbal control moment gyro (SGCMG) and reaction wheel (RW)
  • Spacecraft high-accuracy speediness attitude maneuver method based on single gimbal control moment gyro (SGCMG) and reaction wheel (RW)
  • Spacecraft high-accuracy speediness attitude maneuver method based on single gimbal control moment gyro (SGCMG) and reaction wheel (RW)

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specific Embodiment approach 1

[0075] Specific implementation mode 1. Combination figure 1 Illustrate this specific embodiment, the spacecraft high-precision fast attitude maneuver method based on SGCMG and RW, it is realized by the following steps:

[0076] Step 1. According to the formula:

[0077] ω r = θ r i x i y i z

[0078] Obtain the reference angular velocity ω of the spacecraft r ;

[0079] Where: θ r Indicates the magnitude of the reference angular velocity along the direction of the Euler axis; i x ...

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Abstract

The invention discloses a spacecraft high-accuracy speediness attitude maneuver method based on a single gimbal control moment gyro (SGCMG) and a reaction wheel (RW) and relates to a spacecraft high-accuracy speediness attitude maneuver method which is used for achieving spacecraft high-accuracy speediness attitude maneuver. According to the method, a control moment gyro (CMG) and the RW are used as a combination executing mechanism to achieve the spacecraft high-accuracy speediness attitude maneuver. Angular speed of winding around an Euler main shaft is divided into three sections. Needed controlling torque is generated through the CMG in an accelerating section and a braking section. After a constant speed section and the braking section are finished, a compensate torque generated by the RW is adopted to guarantee that the angular speed is kept near a steady state value so that the spacecraft high-accuracy speediness attitude maneuver is achieved. The method is suitable for the attitude maneuver condition that a spacecraft is provided with the CMG and the RW so that rapid maneuver of the spacecraft is achieved and attitude directing in high accuracy and stability are guaranteed. The method is suitable for maneuver control of the spacecraft.

Description

technical field [0001] The invention relates to a high-precision and fast attitude maneuvering method for a spacecraft. Background technique [0002] The actuator of the spacecraft control system through the exchange of angular momentum usually has a flywheel and a control moment gyro (CMG). and dual frame control moment gyro (DGCMG). [0003] The speed of RW is zero when it is not working, and it generates control torque by accelerating or decelerating. The characteristic is that the generated torque is small, but the control precision is high, and it is usually applied to high-precision three-axis stabilized satellites. [0004] SGCMG has only one frame, and the rotation speed of the rotor is constant. It generates gyro torque through the rotation of the frame, and then acts on the spacecraft body. The characteristic is that the generated control torque is large, but the control accuracy is relatively low, and it is generally used in the attitude control of large spacec...

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Application Information

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IPC IPC(8): G05D1/08G05B13/04
Inventor 孙兆伟杨云刚王峰曹喜滨潘小彤李冬柏庞博李太平宁明峰岳程斐袁勤
Owner HARBIN INST OF TECH
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