Non-biased momentum single-flywheel magnetizing control method

A single flywheel, non-biased technology, applied in the field of satellite flywheel attitude control, can solve the problems of momentum wheel weight, volume and power consumption, momentum wheel large angular momentum, etc.

Active Publication Date: 2014-01-22
SHANGHAI XINYUE METER FACTORY
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Problems solved by technology

[0002] The existing long-term steady-state control of satellites in orbit mainly has two methods: zero momentum and bias momentum. These two wheel control methods have certain disadvantages: zero momentum control r

Method used

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  • Non-biased momentum single-flywheel magnetizing control method
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  • Non-biased momentum single-flywheel magnetizing control method

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Embodiment Construction

[0097] The following is a detailed description of the embodiments of the present invention: this embodiment is implemented on the premise of the technical solution of the present invention, and provides detailed implementation methods and specific operation processes. It should be noted that those skilled in the art can make several modifications and improvements without departing from the concept of the present invention, and these all belong to the protection scope of the present invention.

[0098] Please also see Figure 1 to Figure 3 .

[0099] The present invention is achieved through the following technical solutions.

[0100] A non-bias momentum single flywheel magnetization control method, comprising the following steps:

[0101] Step 1, the flywheel is installed along the rolling axis (X axis), and the wheel control mode of the rolling axis and the magnetic field strength used for magnetic control are determined:

[0102] - When the absolute value of the rolling m...

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Abstract

The invention discloses a non-biased momentum single-flywheel magnetizing control method which includes the following steps that a flywheel is installed along a rolling axis, and the wheel control mode of the rolling axis and the magnetic field intensity used for magnetic control are determined; the flywheel is installed along a yaw axis, the wheel control mode of the yaw axis and the magnetic field intensity used for magnetic control are determined; the flywheel is installed in an inclined mode, a wheel control mode and the magnetic field intensity used for magnetic control are determined; non-biased momentum satellite three-axis stable control is achieved through three-axis magnetic-control current output and flywheel magnetic dumping fusion control of a pitch axis. The non-biased momentum single-flywheel magnetizing control method is simple in system configuration, only one flywheel and magnetic control can achieve the non-biased momentum satellite three-axis stable control, system reliability is improved, the method can be applied to flywheel fault control modes of micro-satellites and medium-and-large-sized satellites, switching of angular momentum exchange control and gyroscopic torque control can be achieved according to rolling intensity and yaw magnetic field intensity, algorithm and calculation are simple and the method is easy in engineering application.

Description

technical field [0001] The invention relates to the technical field of satellite flywheel attitude control, in particular to a non-bias momentum single flywheel magnetization control method, which is used for long-term stable operation control of satellites in orbit. Background technique [0002] The existing long-term steady-state control of satellites in orbit mainly has two methods: zero momentum and bias momentum. These two wheel control methods have certain disadvantages: zero momentum control requires at least three flywheels available; The momentum wheel installed on the pitch axis must have a large angular momentum, and the weight, volume and power consumption of the momentum wheel are generally large. Microsatellites have relatively large restrictions on the number, weight, volume, and power consumption of flywheels. The non-bias momentum single flywheel + magnetic control algorithm is suitable for microsatellite control, and is also suitable for medium and large sa...

Claims

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Application Information

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IPC IPC(8): B64G1/32
Inventor 王献忠张肖张国柱
Owner SHANGHAI XINYUE METER FACTORY
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