Non-biased momentum single-flywheel magnetizing control method

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...

AI Technical Summary

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

Images