Electrodynamic Tether Orbit Descent for Space Debris
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Solution Overview
Problem
Current methods for removing large-sized space debris are costly due to complex construction and high weight requirements, and lack effective collision avoidance and re-entry control mechanisms, particularly when using electrodynamic tethers.
Innovation Solution
An orbit descent system utilizing an artificial satellite with an extendable electroconductive tether that leverages electromagnetic effects from a heavenly body's magnetic field to control the descent of space debris, incorporating a propulsion system for collision avoidance and re-entry management, allowing for multiple debris removal with smaller, less expensive satellites.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If a conventional propulsion system is used to capture and control space debris, then the debris can be removed from orbit, but the satellite weight increases to several tons and launch cost increases significantly
Solution Approach 1:
The patent replaces the conventional mechanical propulsion system with an electrodynamic tether system that utilizes electromagnetic forces and geomagnetic field interactions to achieve orbit descent, eliminating the need for heavy fuel tanks and rocket engines
Solution Approach 2:
The patent changes the fundamental operating parameters by using electrodynamic forces instead of chemical propulsion, transforming the mass-energy conversion approach to electromagnetic field interaction, thereby reducing satellite mass while maintaining debris removal functionality
2Weight of moving object
If an electroconductive tether is used to tow space debris, then the satellite weight is reduced, but the tether becomes unstable in the direction of travel and may collide with the satellite
Solution Approach 1:
The patent applies dynamic control through the propulsion system to actively manage tether oscillations and orientation, transforming the tether from a static, unstable element to a dynamically controlled component that maintains stable operation during debris towing
Solution Approach 2:
The patent implements a feedback control mechanism where the propulsion system responds to real-time tether and debris position data, continuously adjusting control forces to maintain tether stability and prevent collisions during the towing process
3Speed
If a heavy fuel-based propulsion system is used, then orbit change capability is achieved, but collision avoidance and re-entry control are compromised due to lack of maneuverability
Solution Approach 1:
The patent creates a multi-functional system where the propulsion system serves multiple purposes: it controls tether stability, enables collision avoidance maneuvers, manages re-entry timing, and provides general orbit adjustment capability, replacing multiple specialized systems with a single versatile electrodynamic propulsion mechanism
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
This approach reduces the cost and size of debris removal satellites, enables efficient orbit descent, and prevents collisions by applying controlled braking forces, ensuring reliable re-entry and reducing the risk of debris damage on Earth.
Implementation Method 1
causing a descent of an altitude of the space debris by interference with a geomagnetic field
Implementation Method 2
by action of an electromagnetic effect of a magnetic field around the heavenly body upon the extended electroconductive tether
Implementation Method 3
an electron emitter electrically connected to another end of the electroconductive tether for emitting electrons to ambient plasma in order to form a pseudo closed circuit
Data Source
Figure 1
Figure 2~2a
Figure 3~4
AI summary
Provided are an orbit descent method and system for space debris, capable of collision avoidance operation and re-entry control without a removal satellite of complicated construction and heavy weight, and an orbit changing method and system for an artificial satellite, based on the same principles. Provided are an orbit descent method and its associated system. The method includes the steps of: bringing an artificial satellite extendably holding an electroconductive tether near to space debris orbiting around a heavenly body; attaching one end of the electroconductive tether to the space debris by an electroconductive tether attachment mechanism; extending the electroconductive tether, with the other end thereof held by the artificial satellite, by an electroconductive tether extension mechanism, and causing the orbits of the integrated and orbiting artificial satellite, electroconductive tether and space debris to descend toward the heavenly body, by action of an electromagnetic effect of a magnetic field around the heavenly body upon the electroconductive tether; and changing the orbital motions under control by the artificial satellite. The system is configured to perform the steps. Provided are an orbit changing method and system for an artificial satellite, based on the same principles.