Contra-rotating geomagnetic energy storage for space debris de-orbiting
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Solution Overview
Problem
Current methods for removing low-orbit space debris are inefficient and economically challenging, particularly due to the high cost of chemical/electric thrust methods and the reliability issues with electric tethers, which face difficulties in generating sufficient recoil force and maintaining stable operation in the presence of debris and micrometeors.
Innovation Solution
A transfer type contra-rotating geomagnetic energy storage-release delivery system that utilizes a control system with a three-axis control moment canceller and a strong magnetic moment generating device, along with a contra-rotating transmission mechanism, to adjust the orbital trajectory of space debris without consuming working medium, by leveraging the geomagnetic field for energy storage and release.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If chemical/electric thrust methods are used for active drag de-orbit, then de-orbit capability is achieved, but cost becomes extremely expensive
Solution Approach 1:
The patent replaces chemical/electric thrust systems with a magnetic coupling system that uses magnetic fields to transfer angular momentum. The magnetic coupling device generates magnetic moments that interact with the geomagnetic field to produce torque, eliminating the need for expensive propellant-based thrust systems while achieving orbital decay.
Solution Approach 2:
The patent introduces the geomagnetic field as an intermediary medium to transfer energy and momentum. By coupling the magnetic moment of the device with the Earth's magnetic field, the system achieves de-orbit functionality without direct mechanical or chemical propulsion, using the planet's own magnetic field as the working medium.
2Loss of substance
If electric tether is used for non-working medium consumption de-orbit, then working medium consumption is eliminated, but reliability deteriorates due to debris and micrometeors
Solution Approach 1:
The patent extracts the magnetic coupling device from the tether structure, separating the magnetic momentum transfer function from the physical tether. This eliminates the tether's vulnerability to debris and micrometeors while retaining the ability to transfer angular momentum through magnetic fields, thus improving reliability without sacrificing the non-consumptive advantage.
Solution Approach 2:
The patent replaces the mechanical tether system with a magnetic coupling system. Instead of using a physical rope that is susceptible to damage from space debris, the system uses magnetic fields to couple the de-orbit device with the spacecraft, eliminating mechanical contact points that could fail due to micrometeoroid impacts.
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 method enables efficient, low-cost de-orbiting of space debris without working medium consumption, improving the economics and reliability of low-orbit space debris removal by decoupling the magnetic and rotational momentum adjustments, thus reducing the complexity and uncertainty associated with dual coupling.
Implementation Method 1
utilizing a control system with a three-axis control moment canceller and a strong magnetic moment generating device, along with a contra-rotating transmission mechanism, to adjust the orbital trajectory of space debris without consuming working medium, by leveraging the geomagnetic field for energy storage and release
Data Source
AI summary
A transfer type contra-rotating geomagnetic energy storage-release delivery system is disclosed. The system includes a control system, a three-axis control moment canceller and an energy system, which are arranged on a delivery mother spacecraft, and the delivery mother spacecraft is connected, through support rod structures, with a strong magnetic moment generating device, a contra-rotating transmission mechanism and two delivery connection rod structures arranged at the two ends of the contra-rotating transmission mechanism, the strong magnetic moment generating device is arranged between the contra-rotating transmission mechanism and the delivery mother spacecraft, the two delivery connection rod structures are provided with slidable mass blocks respectively, and the strong magnetic moment generating device and the contra-rotating transmission mechanism provide energy through the energy system. The strong magnetic moment generating device is free of accelerated rotation of an attitude, thereby decoupling the dual coupling.


