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Optimal control method for single frame moment gyro group for spacecraft wide angle maneuver control

A moment gyro and single-frame technology, applied in attitude control and other directions, can solve problems that have not yet been seen

Inactive Publication Date: 2005-04-13
TSINGHUA UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0021] 2. Although Singular configuration of gyro group The problem has received some attention, but currently for SGCMG 'benefit' Singular configuration and 'Detrimental' exotic configurations not differentiated
However, there is no literature on this

Method used

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  • Optimal control method for single frame moment gyro group for spacecraft wide angle maneuver control
  • Optimal control method for single frame moment gyro group for spacecraft wide angle maneuver control
  • Optimal control method for single frame moment gyro group for spacecraft wide angle maneuver control

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Embodiment Construction

[0176] The general process of spacecraft attitude control: first determine the current attitude quaternion of the spacecraft through the attitude determination system attitude angular velocity In the module of calculating the control torque, through the current state quantity and the required state quantity (Λ * (t), ω * (t)) to calculate the required control torque vector M * (t). Signal M * (t) is passed to the SGCMG control law module. Solved by the new control law designed followed by Submit to the hardware to realize the rotation control of the spacecraft through SGCMG. Finally the attitude determination system will determine new attitude parameters and repeat the process (see Figure 9 , the SGCMG control law module in the figure is the content of the present invention).

[0177] The purpose of the simulation calculation is to test the rationality and feasibility of the SGCMG control law. Although the test does not involve specific hardware, the performa...

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Abstract

The invention provides an optimal control method for single frame moment gyro group for spacecraft wide angle maneuver control characterized in that, during the process of attitude control, the gyroscope having the highest frame angular speed is selected, then a minimum frame angular speed is obtained from the gyroscope as the control frame angular speed for rapid large angle power-propelled control, when guaranteeing the gyroscope frame angular speed is lower than the given propulsion generator rotational speed limit, the lost motion frame angular speed and correction coefficient can be designed to give the gyroscope group dynamic formation a predetermined final frame angle quantity, finally the optimum control angular speed and optimum lost motion angular speed are multiplied by the correction coefficient for summing, which can obtain the optimum value of the frame angular speed.

Description

technical field [0001] The invention relates to the technical field of spacecraft attitude dynamics and control. [0002] SGCMG: Single Gimbal Control Moment Gyroscopes. Single frame moment gyroscope ( figure 1 ). It consists of a high-speed rotating flywheel, a frame supporting the flywheel, and a motor that drives the frame to rotate. Generally, the rotational speed of the flywheel is a certain value, and the control is realized by selecting the rotational speed of the frame drive motor. In other words, the problem of designing the SGCMG control law is actually the problem of choosing a reasonable frame speed. Background technique: [0003] The large-angle attitude control of the spacecraft is the key to the spacecraft's completion of specific missions. Its control accuracy and speed directly affect the completion of spacecraft application tasks. Since the 1970s, some high-precision large-scale spacecraft in the United States and Russia (Soviet Union) (such as: the s...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08
Inventor 刘辉
Owner TSINGHUA UNIV
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