Electromagnetically controlled attitude control system for satellites using movable, segmented mantle belt systems

Abstract

Attitude control system for satellites, comprising at least two orthogonally arranged, ring-shaped magnetic belt systems, consisting of several segmented electromagnets that can selectively generate electromagnetic fields.

Description

1. Description of the invention: The present invention relates to a propellant-free attitude control system for satellites, in particular for spherical spacecraft or miniature satellites. The invention is based on the controlled interaction between electromagnetic fields and a ferromagnetic mass unit within the satellite. The electromagnetic fields are generated by two or more segmented magnetic belt systems that can be moved or tilted around the outer structure of the satellite. The aim of the invention is to enable the satellite to perform three-dimensional attitude control and spatial orientation without using mechanically moving masses such as reaction wheels or lossy propulsion systems. By selectively attracting the ferromagnetic mass within the satellite using activated magnetic segments, a controlled counter-movement of the satellite can be achieved (conservation of momentum). Operation is electrically powered via photovoltaic panels on the satellite's surface. The innovation lies particularly in the combination of segmented magnetic field control, rotating and tilting belts, the spherical structure, and the elimination of propellant or movable mass arms. The system enables durable, low-maintenance attitude control for applications in Earth orbit as well as for deep-space missions. 2. Technical Description: The invention relates to a three-dimensionally controllable attitude control system for satellites, in which at least two orthogonally arranged electromagnetic ring systems ("magnetic belt systems") are provided on a spherical satellite body. Each of these rings consists of several segmented electromagnets that can be individually activated electronically. The rings are designed so that they can either rotate mechanically around their axis or electronically shift their magnetic field in the form of a "wandering" polarization. Furthermore, they can be tilted or inclined along their axes so that the resulting magnetic fields can be freely aligned in space. At the center of the spherical structure is at least one ferromagnetic body (e.g., an iron core) which experiences a directed force due to the action of the active magnetic segments. Because of the conservation of momentum, the entire satellite body undergoes a counter-movement in the same direction or rotation. The magnetic segments are powered by photovoltaic elements mounted externally on the sphere's surface. These are positioned to ensure a continuous power supply, independent of the satellite's rotation. A central control unit monitors the satellite's orientation in real time and selectively activates individual magnetic segments to achieve or stabilize target orientations. The system enables continuous, propellant-free attitude control without moving mass arms, offering high reliability and minimal maintenance. It is scalable for various satellite sizes, particularly for CubeSats and deep-space probes. Explanation of the claims for protection: The patent claims relate to the design, function, and application of the described magnetic belt system. The focus is on the use of segmented electromagnetic rings for propellant-free attitude control, which, through their three-dimensional controllability, enable a new technical functionality. The claims cover all system-relevant components as well as the use in various orbital environments. Innovation: The innovation of the invention lies in the combination of the following features: 1. Use of segmented electromagnetic rings for spatial orientation control 2. Mechanism-free system without moving masses or flywheels 3. Three-dimensional control through orthogonal arrangement of multiple rings 4. Utilization of the reaction force between the internal mass and the magnetic field 5. Fully electric control and power supply via photovoltaics 6. Can also be used outside the Earth's magnetic field (e.g., interplanetary) This solution has not yet been implemented in any known system and offers a new class of attitude control for space-based applications with minimal energy and space requirements.

Claims

Attitude control system for satellites, comprising at least two orthogonally arranged, ring-shaped magnetic belt systems, consisting of several segmented electromagnets that can selectively generate electromagnetic fields. System according to claim 1, characterized in that at least one ferromagnetic mass body is located within the satellite structure, towards which the magnetic fields of the belt systems are directed. System according to one of the preceding claims, wherein the magnetic belt systems are rotatable mechanically or electromagnetically about their respective axis and / or tiltable along an axis. System according to one of the preceding claims, wherein the electromagnets can be controlled independently segment by segment to generate directed magnetic field pulses in different spatial directions. System according to one of the preceding claims, wherein the power supply to the electromagnet segments is provided via photovoltaic surfaces on the outer satellite shell. System according to one of the preceding claims, wherein a control unit automatically regulates the activation of the electromagnetic segments depending on position or target specifications. Use of the system according to one of the preceding claims for propellant-free attitude control of artificial satellites in low Earth orbit (LEO), geostationary orbits (GEO) or interplanetary orbits.

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