Magneto-coupler Stabilizes Rotating Space Debris
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Solution Overview
Problem
Current methods for active debris removal face challenges in controlling the angular velocities of large space debris, particularly due to high rotation speeds, which complicates capture and increases the risk of collision during the deorbiting process.
Innovation Solution
A space system utilizing magneto-couplers launched from a hunter spacecraft to generate magnetic fields that couple with the Earth's magnetic field, stabilizing the debris by attaching to its surface and modulating the magnetic coupling to reduce angular velocities, thereby facilitating safe capture and deorbiting.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If a hunter satellite approaches a target satellite with uncontrolled angular variations to capture it, then the capture process can be initiated, but the risk of collision with the debris increases and the control system requirements become more complex
Solution Approach 1:
The patent applies preliminary action by deploying the electromagnetic module with magneto-couplers to the debris surface before the hunter satellite approaches for capture. This preliminary attachment and stabilization phase reduces the debris angular velocity and stabilizes its attitude, creating safer conditions for the subsequent capture operation. The module is launched and attached in advance, allowing the debris to be stabilized before the high-risk close-approach phase.
Solution Approach 2:
The electromagnetic module with magneto-couplers serves as an intermediary between the hunter satellite and the rotating debris. This intermediate device attaches to the debris surface and uses electromagnetic interactions with the Earth's magnetic field to stabilize the debris attitude and reduce rotation, thereby mediating the interaction and reducing collision risk during the capture process.
2Strength
If a robotic arm is used to capture large debris, then a rigid link can be established for capture, but the maximum loads exerted on the arm by the debris become high and make implementation difficult
Solution Approach 1:
The patent applies preliminary action by stabilizing the debris attitude and reducing its angular velocity before the robotic arm capture attempt. By pre-reducing the rotation speed and stabilizing the debris orientation, the mechanical loads on the robotic arm during capture are significantly reduced, making the implementation feasible for large debris that would otherwise exert excessive loads.
Solution Approach 2:
The patent replaces the direct mechanical interaction approach with an electromagnetic stabilization phase first. Instead of immediately engaging the robotic arm with a large rotating debris, the system uses electromagnetic fields to stabilize the debris attitude and reduce rotation, substituting mechanical force requirements with electromagnetic interaction during the preliminary stabilization phase.
3Adaptability or versatility
If second-class techniques using nets or harpoons are used to capture debris, then a larger range of debris can be captured in terms of geometric configuration, but implementation becomes difficult when the rotation speed of the debris is high due to risk of the flexible link winding around the debris
Solution Approach 1:
The patent applies preliminary action by reducing the debris rotation speed and stabilizing its attitude before the flexible link (net or harpoon) capture attempt. This pre-stabilization eliminates the winding risk that would otherwise prevent the use of flexible links, thereby enabling the versatile geometric adaptation benefits of nets and harpoons to be realized without operational difficulties.
Solution Approach 2:
The patent uses electromagnetic stabilization to replace the need for direct mechanical control of flexible links during high-speed rotation. By substituting the mechanical control problem with an electromagnetic field-based attitude stabilization phase, the system enables flexible link deployment without the winding risks that would otherwise constrain operational ease.
4Speed
If third-class techniques such as ion beam guidance or electrostatic interaction are used, then compatibility with high angular debris velocities is achieved, but the deorbit duration becomes very long
Solution Approach 1:
The patent applies preliminary action by using electromagnetic stabilization to rapidly reduce the debris angular velocity and stabilize its attitude before capture and deorbiting. This preliminary stabilization phase addresses the high angular velocity compatibility requirement, while the subsequent capture and controlled deorbiting process eliminates the prolonged duration issue associated with continuous ion beam or electrostatic interaction methods.
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
The system effectively reduces the angular velocities of space debris, enhancing the safety and efficiency of the debris removal process by stabilizing the debris before capture, thus minimizing the risk of collision and enabling controlled deorbiting.
Implementation Method 1
The magneto-coupler is configured to generate on command one or more magnetic fields for coupling to the Earth's magnetic field
Implementation Method 2
generate on command one or more magnetic fields for coupling to the Earth's magnetic field
Implementation Method 3
a device for launching by impulse the magneto-coupler(s) of the spacecraft towards the space debris
Data Source
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AI summary
A space-based system for reducing the angular velocity of space debris (4) comprises a chaser spacecraft (6), one or more magnetorquers (8, 10, 12), and a pulse-launching device (14) for launching the magnetorquer(s) of the chaser spacecraft (6) towards the space debris (4). The launch device (14) includes at least one launch gun barrel (40) for guiding the magnetorquer(s) (8, 10, 12) towards the space debris (4), and each magnetorquer(s) (8, 10, 12) includes an electromagnetic coil (54) and at least one self-docking element (56) to a face of the debris (6) under the action of the momentum(s) of the magnetorquer(s) (8, 10, 12) imparted by the launch device (14).