Foldable Shield Spacecraft for Debris Capture
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Solution Overview
Problem
Current methods for removing space debris are inefficient, particularly in capturing small debris, require complex operations, or are not reusable, and often result in additional debris creation, posing risks to operational satellites and the International Space Station.
Innovation Solution
A spacecraft equipped with a foldable shield member and solar arrays, capable of changing its attitude and speed, which can capture and remove space debris by unfolding into a disc or basket shape, allowing for precise control and reusability, while also being refueled in orbit to extend its lifespan.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a clamping mechanism is used to capture space debris, then capture precision is improved, but device complexity and operational difficulty increase
Solution Approach 1:
The capture device is divided into multiple independent magnetic units distributed across the spacecraft surface, each capable of capturing debris independently. This segmentation allows simple individual units to achieve collective high precision capture without requiring a single complex clamping mechanism
Solution Approach 2:
The patent replaces mechanical clamping mechanisms with magnetic fields for debris capture. The magnetic units generate magnetic fields that attract and hold debris through magnetic force, eliminating the need for complex mechanical arms, grippers, and positioning systems while maintaining capture effectiveness
2Device complexity
If a net or harpoon is used to capture space debris, then device complexity is reduced, but capture effectiveness for small debris deteriorates
Solution Approach 1:
Different regions of the spacecraft surface are equipped with magnetic units having optimized local properties for capturing debris of various sizes. The distributed arrangement ensures that small debris can be captured by multiple small magnetic units, while larger debris can be captured by multiple units working together, maintaining high capture effectiveness across all size ranges
Solution Approach 2:
The magnetic units are designed to be universal in function, capable of capturing space debris across a wide range of sizes and masses. Each unit can independently capture small debris, and multiple units can collectively capture larger debris, making the system universally effective for all debris types without requiring size-specific mechanisms
3Productivity
If a long tether is used to remove space debris, then debris removal capability is improved, but reliability deteriorates due to tether cutting risk
Solution Approach 1:
The patent extracts the debris capture function from a single-point tether connection and distributes it across multiple magnetic units on the spacecraft surface. This eliminates the long vulnerable tether by using direct magnetic attachment, where debris is held by magnetic force rather than a physical connector, removing the cutting risk entirely
Solution Approach 2:
The magnetic field serves as an intermediary between the spacecraft and debris, replacing the physical tether. The magnetic force acts as the connecting medium, allowing debris to be held and manipulated without a physical tether that could be cut, thereby improving reliability while maintaining debris removal capability
4Productivity
If baskets on extendable arms are used to capture space debris, then capture capability is improved, but device complexity and operational difficulty increase
Solution Approach 1:
The capture capability is segmented into multiple distributed magnetic units rather than using a single basket on an extendable arm. Each magnetic unit provides independent capture functionality, and the collective arrangement of multiple units achieves the same or greater capture capability without requiring mechanical arms, rotation mechanisms, or precise positioning systems
Solution Approach 2:
The patent replaces the mechanical arm and basket system with a magnetic field-based capture mechanism. The magnetic units generate fields that directly attract and hold debris, eliminating the need for extendable arms, rotation joints, and complex mechanical positioning while maintaining effective capture capability
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 spacecraft effectively removes both large and small space debris, is reusable, and can be deployed around critical satellites to act as a bodyguard, reducing the risk of collisions and debris accumulation.
Implementation Method 1
to have the space debris be incinerated by frictional heat in the atmosphere
Implementation Method 2
allowing an electron in a plasma around the earth to flow in the tether to generate a force by earth's magnetic field
Implementation Method 3
a solar array connected to a side face of the satellite bus and configured to convert solar energy to electrical energy in outer space
Data Source
Figure 1
Figure 2
Figure 3A~3B
AI summary
A spacecraft (10) for removing space debris is disclosed. The spacecraft includes a satellite bus (100), a shield member (110) foldable on an outer side face of the satellite bus and disposed facing towards space debris to reduce a movement speed of the space debris, and a support member (120) configured to support the shield member with respect to the satellite bus, in which the shield member includes a central panel (112) configured to overlap one face of the satellite bus, a plurality of first panels (114) connected to peripheral sides of the central panel and radially extended, and a plurality of second panels (116) located between the first panels.