Method for controlling procession of bias momentum micro-satellite

Abstract

The invention discloses a method for controlling the procession of a bias momentum micro-satellite, which comprises the following steps: performing initialization: the Y-axis output of a magnetometer at the current moment is acquired and recorded, and model geomagnetic field of the satellite in an orbital coordinate system is calculated and recorded referring to a geomagnetic table and according to the current time as well as the orbit parameter; reading out the Y-axis output of the magnetometer recorded at the previous cycle; obtaining A (see details in the specification) by Y-axis outputting the magnetometer at the current moment and subtracting the magnetometer Y-axis output recorded at the previous cycle; obtaining B (see details in the specification) by subtracting the Y-axis model magnetic field value at the previous cycle from that in the orbital coordinate system at the current moment; according to a control law C (see details in the specification), calculating out the output magnetic torque of a Y-axis magnetic torquer, and sending control command to the magnetic torquer; recording the Y-axis output of the magnetometer at the current moment; recording the Y-axis model magnetic field value in the orbital coordinate system at the current moment; and controlling to repeat steps 2) to 9) taking the cycle T as uniform intervals. The invention has the advantages that the measurement to attitude angle is omitted, the operation amount is less, and the dependence on hardware is reduced.

Description

technical field [0001] The invention discloses a method for the precession control of the micro-satellite with bias momentum. The output of the magnetometer is used as the input of the control law, and the prior information of the magnetic field is used to realize real-time compensation. Finally, the output of the magnetic torque device controls the angle of the satellite. The direction of the moment of momentum converges to the normal direction of the orbit. Background technique [0002] The satellite control system configuration of "offset momentum wheel + magnetometer + magnetic torquer" has the advantages of low cost and high reliability, and is a relatively common control system configuration method for micro-satellites, nano-satellites, pico-satellites and even large satellites , this type of configuration needs to control the chapter precession of the satellite, so as to keep the angular momentum moment vector pointing to the normal direction of the satellite orbit fo...

AI Technical Summary

Problems solved by technology

[0010]The advantage is that the design of the control law is very simple, only need differential processing, and the calculation is extremely simple; the disadvantage is that the control precision is low, it is often used in the initial damping to achieve chapter precession control

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