Control method of satellite momentum wheel on-orbit attitude deviation-free spinning and racemization

Abstract

The invention provides a method for controlling the on-orbit attitude of a satellite momentum wheel for spinning and racemization without deviation, which comprises the following steps: setting the final required target angular momentum of a satellite by remote control injection number; managing the momentum of the reaction flywheel, controlling the satellite to operate within a desired central rotational speed range; calculating the magnetic feedforward moment, wherein the magnetic feedforward moment is shown in the description the output moment calculated by the satellite controller, the output moment is shown in the description, the magnetic feedforward is shown in the description, the conventional decoupling moment is shown in the description, and disturbance compensation torque is shown in the description. The magnetic feedforward, the conventional decoupling moment and the disturbance compensation torque are synthesized to obtain triaxial command torque; the triaxial command torque is shown in the description. The command angular momentum of triaxial satellite is obtained by intergration in the control period, and the command rotation speed of the satellite in use is calculated according to the installation matrix of the satellite. The effect of the magnetic moment on the star body is counteracted in the command rotating speed of the flywheel through the synthesis of thefeedforward moment, so that the effects of no-deviation spinning and racemization of the attitude in the process of increasing and reducing the offset angular momentum are achieved.

Description

technical field [0001] The invention belongs to the technical field of satellite attitude control, in particular to a control method for the on-orbit attitude of a satellite momentum wheel without deviation in spinning and despinning. Background technique [0002] With the development of civil aerospace technology and application requirements, the country has higher and higher requirements for the life of civilian satellites with earth observation functions, and the earth observation satellites in low and medium orbits are gradually developing to an on-orbit life span of more than eight years. [0003] In order to ensure the completion of satellite in-orbit application tasks, it is necessary to precisely control its motion. The satellite attitude control system is an important part of the satellite. With the development of modern satellite technology, higher requirements are put forward for its attitude control system. The attitude control system is simple and reliable. Eas...

AI Technical Summary

Problems solved by technology

There are also methods that use geomagnetic torque to achieve flywheel spin-up, but during the spin-up process, there will still be obvious interference with the satellite attitude, and the load generally cannot work normally during this period.

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