Symmetrical Electromagnetic Structure of Attitude Control Actuator Based on Magnetohydrodynamic Satellite

Abstract

The invention provides a symmetrical electromagnetic structure based on a magnetohydrodynamic satellite attitude control actuator, which includes an annular pipe; a fluid chamber is formed inside the annular pipe; the fluid chamber is filled with conductive fluid; the outer side of the annular pipe is connected along the radial direction There is a first electrode; the inner side of the annular pipe in the radial direction is connected with a second electrode; the first electrode is arranged opposite to the second electrode; one end of the second electrode in the axial direction extends radially outward to lead out the electrode , the lead-out electrode is separated from the first electrode (the second electrode and the lead-out electrode are an integral part); in the radial direction, a first permanent magnet is arranged on the outside of the first electrode, and a second permanent magnet is arranged on the inside of the second electrode. magnet. The invention adopts a reasonable and symmetrical magnetic circuit, which can better realize a uniformly distributed magnetic field; the current flowing through the path avoids the influence of the current on the magnetic field, and is slightly wider than the magnetic field of the electrode, avoiding the edge attenuation of the magnetic field, so that the electromagnetic force is within the main range of action The magnetic field is evenly distributed.

Description

Technical field [0001] The invention relates to the field of magnetohydrodynamics, in particular, to a symmetrical electromagnetic structure based on a magnetohydrodynamic satellite attitude control actuator. Background technique [0002] The current mainstream satellite attitude adjustment actuator is a flywheel mechanism, which uses the principle of conservation of angular momentum to adjust the satellite attitude by controlling the rotation of the flywheel. However, due to the existence of bearings and moving mechanical parts, the reliability of the flywheel structure is low, which restricts the service life of the spacecraft. For example, the Kepler Space Telescope, which recently ended its exploration mission, failed two successively because of the four momentum wheels of attitude control (at least three exist to work properly). Summary of the invention [0003] Aiming at the defects in the prior art, the purpose of the present invention is to provide a symmetrical electroma...

AI Technical Summary

Problems solved by technology

However, due to the existence of bearings and moving mechanical parts, the reliability of the flywheel structure is low, which restricts the service life of the spacecraft

Images