Method for realizing satellite three-axis attitude control by combining available flywheels with magnetic torquer in case of flywheel underactuation

A magnetic torque device and three-axis attitude technology, which is applied to aircrafts, aerospace vehicles, motor vehicles, etc., can solve the problem that the flywheel system cannot provide three-axis attitude control torque, and no longer has three-axis attitude control capabilities. The effect of easy engineering implementation, improved reliability, and simple method

Active Publication Date: 2017-03-29
SHANGHAI AEROSPACE CONTROL TECH INST
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Problems solved by technology

When any one or any two flywheels fail, the flywheel system will not be able to provide three-axis attitude control torque, so the attitude control system degenerates into a typica

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  • Method for realizing satellite three-axis attitude control by combining available flywheels with magnetic torquer in case of flywheel underactuation
  • Method for realizing satellite three-axis attitude control by combining available flywheels with magnetic torquer in case of flywheel underactuation
  • Method for realizing satellite three-axis attitude control by combining available flywheels with magnetic torquer in case of flywheel underactuation

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[0021] According to the available situation of the actual flywheel and the current geomagnetic field vector, the inventive method defines the magnetic control matrix Γ(b) and the wheel control matrix K w , the three-axis command magnetic moment for attitude control is calculated. The final magnetic current control command can be obtained by summing the magnetic current command for attitude control and the magnetic current command for magnetic unloading, while the available flywheel continues to execute the control command given by the corresponding wheel control algorithm.

[0022] Specifically attached figure 1 And attached figure 2 Take the common flywheel and magnetic torque device installation configuration as an example. The system is equipped with three flywheels and three magnetic torque devices. The three flywheels are installed orthogonally along the three main axes of the body coordinate system ObXbYbZb, and the three magnetic torque devices are respectively parall...

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Abstract

A Method for realizing satellite three-axis attitude control by combining available flywheels with a magnetic torquer in case of flywheel underactuation comprises the following steps: (1) determining a magnetic control matrix Gamma(b) according to a geomagnetic field intensity vector B measured by a magnetometer, and determining a flywheel control matrix Kw according to the actual availability conditions of flywheels; (2) calculating a magnetic electric current command Izk=Kic*Mzk for three-axis attitude control; (3) calculating a magnetic electric current command Ixz=Kic*Mxz for three-axis magnetic unloading; and (4) calculating a magnetic torquer command Ick=Izk+Ixz, wherein when the magnetic torquer performs attitude control according to the magnetic torquer command, the available counteractive flywheels continue to perform attitude control based on a command torque Tc. According to the method, when only any two or even one flywheel is available in a system, the two or one available flywheel is combined with the three-axis magnetic torquer to realize high-precision satellite three-axis attitude control. The method is suitable for long-term earth pointing control or long-term sun pointing control and is also suitable for wide-angle maneuvering control of any attitude of a satellite.

Description

technical field [0001] The invention belongs to the field of spacecraft attitude control and relates to a satellite three-axis attitude control method when the flywheel is under-driven. Background technique [0002] Modern small satellites generally do not carry a jet system, and the reaction flywheel has become the main actuator for high-performance attitude stabilization control and large-angle attitude maneuver control of small satellites. When the average value of the disturbing torque on the satellite is not zero, the angular momentum of the flywheel will accumulate over time, eventually leading to the saturation of the flywheel speed. Therefore, modern small satellites also need to be equipped with a magnetic torque device to realize flywheel unloading. That is, the reaction flywheel is usually used for attitude control, and the magnetic torque device is used to cooperate with the flywheel to complete the unloading of the flywheel. [0003] In the past satellite atti...

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Application Information

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IPC IPC(8): B64G1/32
CPCB64G1/32B64G1/245
Inventor 杜宁尹海宁李芳华孙锦花查理王世耀孟其琛
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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