Non-biased momentum single flywheel magnetizing control algorithm

Abstract

The invention discloses a non-biased momentum single flywheel magnetizing control algorithm. The non-biased momentum single flywheel magnetizing control algorithm comprises the following steps: step 1, a flywheel is mounted along a rolling axis (X axis); a wheel control mode and a magnetic density used for magnetic control are determined; step 2, the flywheel is mounted along a yaw axis ( Z axis ); a wheel control mode and a magnetic density used for magnetic control are determined; step 3, the flywheel is mounted in an inclined manner; a wheel control mode and a magnetic density used for magnetic control are determined; step 4, an integrated control is conducted on the triaxial (X axis, Y axis and Z axis) electrical current output and magnetic unloading of the flywheel on the Y axis; therefore, triaxial stable control of the non-biased momentum satellite is realized. The non-biased momentum single flywheel and magnetizing control algorithm is simple in the configuration requirements; all that is needed is to adopt a single flywheel and the magnetic control, so as to realize the triaxial stable control of the non-biased momentum satellite; the system reliability is improved; the non-biased momentum single flywheel and magnetizing control algorithm provided by the invention can be applied to flywheel fault control modes of micro satellites and medium and large-scale satellites; angular momentum exchange control and gyroscope torque control switch are conducted according to rolling and the yaw magnetic density; the calculation in the algorithm is simple, thereby being easy for 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 algorithm. 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 satellite flywheel failure control modes. Contents of the invention [00...

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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 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

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