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A Method of Realizing Three-Axis Stable Control of Satellite Using Single Control Moment Gyro and Two Flywheels

A technology for controlling torque gyro and three-axis stabilization, which is applied in the field of satellite attitude control and can solve problems such as inability to accurately output command torque.

Active Publication Date: 2021-08-03
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

[0003] Since the control moment gyro is realized by changing the output direction of angular momentum, when only one control moment gyro is working normally on the star, when the control moment gyro outputs the torque in the X direction, it will also generate torque in the Z direction, and the two directions The torque ratio generated is related to the current angular position of the frame, so the required command torque cannot be accurately output

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  • A Method of Realizing Three-Axis Stable Control of Satellite Using Single Control Moment Gyro and Two Flywheels
  • A Method of Realizing Three-Axis Stable Control of Satellite Using Single Control Moment Gyro and Two Flywheels
  • A Method of Realizing Three-Axis Stable Control of Satellite Using Single Control Moment Gyro and Two Flywheels

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Embodiment Construction

[0043] The present invention proposes a system control method in the case of failure of multiple actuators for satellites using flywheels and control moment gyroscopes ("CMG" for short) as the main actuators for attitude control; there is only one control moment gyroscope on the satellite. And under the effective situation of two reaction flywheels, the present invention can realize attitude stability control.

[0044] against figure 1 , figure 2 As shown in the effective actuator configuration satellite, the following control method is proposed. image 3 It is a schematic diagram of the installation of the control moment gyro relative to the satellite body, O G x G Y G Z G The definition of is as follows: the origin is the geometric center of the control torque gyroscope, Z G The axis is the angular momentum output direction of the inner rotor when the frame angle is 0°, Y G Axis is the forward rotation direction of the outer frame, XG The axes are determined by the r...

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Abstract

The invention relates to a method for realizing satellite three-axis stable control with a single control moment gyroscope and two flywheels. The ground measurement and control station remotely controls the satellite using a thruster to control the attitude; according to the CMG inner rotor speed instruction, the angular momentum corresponding to the CMG inner rotor speed is obtained ;According to the position of the CMG outer frame and the effective rotational speed commands of the two flywheels, set the target angular momentum of magnetic unloading; , calculate the changed angular momentum control command, solve the CMG frame angle: allow single CMG control, select single CMG access, effective two flywheel access, use flywheel to control satellite attitude. For a satellite using a flywheel and a control moment gyroscope as the main actuators for attitude control, the invention can realize attitude stability control under the condition that only one control moment gyroscope and two reaction flywheels are effective on the satellite.

Description

technical field [0001] The invention belongs to satellite attitude control technology, relates to the satellite attitude control technology of "flywheel + control torque gyroscope" combined executive mechanism, in particular to a method for realizing satellite three-axis stable control through a single control moment gyroscope and two flywheels. Background technique [0002] Manipulation laws represent the distribution or solution of control torque commands. Since the torque output of the reaction flywheel is generated by the change of angular momentum, its manipulation method is relatively simple. For the control moment gyroscope, its steering law needs to be designed according to different requirements. [0003] Because the control moment gyro is realized by changing the output direction of angular momentum, when only one control moment gyro is working normally on the star, the control moment gyro will generate torque in the Z direction while outputting the torque in the ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/28B64G1/24
CPCB64G1/286B64G1/28B64G1/245
Inventor 刘德庆吴德安张涛张增安高四宏周胜良
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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