Satellite Control Spacecraft Debris Removal via Magnetic Capture
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Solution Overview
Problem
The accumulation of debris in orbit poses a significant risk of collisions with operational satellites, spent rockets, and satellite fragments, which can impede the functionality of active satellites.
Innovation Solution
A system comprising a satellite-control spacecraft with a propulsion subsystem for navigation, a satellite-capture subsystem for capturing and releasing the target satellite, and an energization assembly to apply an electrically conducting and/or magnetic control medium to the target satellite, allowing for controlled manipulation of the satellite's orbit or attitude.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If satellites are decommissioned to a higher orbit and left in orbit, then they remain in orbit as unusable debris, but the accumulation of debris increases collision risks with other satellites and spent rockets
Solution Approach 1:
The patent extracts harmful debris from operational orbit by capturing it with a robotic arm and transferring it to a disposal orbit using a propulsion system. This removes the debris from the harmful environment where it could cause collisions, directly resolving the contradiction between maintaining satellite functionality and reducing collision risks.
Solution Approach 2:
The patent converts the harmful presence of decommissioned satellites into a beneficial service by creating a debris removal system. The same orbital environment that accumulates harmful debris becomes the target for a controlled remediation system that uses capture mechanisms and propulsion to actively manage and remove debris, transforming the problem into a solution.
2Productivity
If active satellites continue to operate in orbit, then they maintain their flight path, but accumulated debris impedes their function
Solution Approach 1:
The patent introduces an intermediary debris removal system that acts between the operational satellites and the debris field. The robotic capture mechanism and propulsion system serve as intermediaries that actively intervene to remove debris, protecting operational satellites from impairment while allowing them to continue their productive function.
3Object-affected harmful factors
If debris is removed from orbit, then collision risks are reduced, but the system requires complex capture and propulsion mechanisms
Solution Approach 1:
The patent applies multi-functionality by designing a spacecraft that combines robotic capture mechanisms, propulsion systems, and navigation capabilities into a single integrated platform. This universal system can perform multiple functions (capture, transfer, disposal) to manage debris, reducing the need for separate specialized systems and managing complexity through functional integration.
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
Enables the controlled servicing, positioning, and removal of debris from orbit, thereby reducing the risk of collisions and maintaining the functionality of operational satellites.
Implementation Method 1
an energization assembly to energize the control medium to release energy for controlling the target satellite
Implementation Method 2
a propulsion subsystem configured to propel and navigate the spacecraft proximate the target satellite
Implementation Method 3
a satellite-capture subsystem configured to capture the target satellite
Data Source
AI summary
An example system for controlling a target satellite includes: a satellite-control spacecraft including: a propulsion subsystem configured to propel and navigate the spacecraft proximate the target satellite; and a satellite-capture subsystem configured to: capture the target satellite; apply a control medium to the target satellite, the control medium including an electrically conducting and/or magnetic material; and release the target satellite; and an energization assembly configured to energize the control medium to release energy for controlling, propelling and navigating the target satellite.