Inflatable Capture Veil for Orbital Debris Removal
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Solution Overview
Problem
The accumulation of large and/or mass orbital debris in low Earth orbit poses a significant risk due to potential collisions, leading to an exponential increase in debris, which could render low orbit unusable for centuries if not addressed, with existing technologies lacking effective methods for deorbiting or reorbiting objects without their own deorbiting systems.
Innovation Solution
A space vehicle equipped with a flexible sail for capturing and coupling with orbital debris, utilizing inflatable members for deployment and a traction system to deorbit or reorbit objects by applying a traction force, allowing for the transfer of objects to a higher orbit or atmospheric re-entry.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Stability of the object's composition
If a rigid deployment structure is used for the capture veil, then the veil can maintain its shape and provide stable capture, but the device complexity and mass increase significantly
Solution Approach 1:
The patent employs a flexible capture veil made of thin film material that can be inflated to maintain its shape during capture operations. The veil transitions from a folded stowed configuration to an inflated operational configuration, using the flexibility of the thin film to achieve the required shape stability without rigid structural support.
Solution Approach 2:
The deployment and shape-maintenance of the capture veil is achieved through pneumatic inflation. Inflatable elements are integrated into the veil structure, and when inflated with gas, they provide the necessary rigidity and shape stability for effective debris capture, eliminating the need for complex rigid deployment mechanisms.
2Quantity of substance
If the capture veil is made large in size to capture massive debris, then the capture capability increases, but the difficulty of deployment and control increases
Solution Approach 1:
The large capture veil is divided into multiple segmented panels or sections that can be independently deployed and inflated. This segmentation allows the large structure to be managed in smaller, more controllable units during deployment, reducing the operational difficulty while maintaining the overall large capture area needed for massive debris.
Solution Approach 2:
The capture veil employs dynamic deployment mechanisms where the veil transitions from a compact stowed state to an expanded operational state through controlled inflation. This dynamic approach allows the large veil to be deployed on-demand and adjusted in size or shape as needed, making operation easier despite the large final dimensions.
3Weight of moving object
If inflatable elements are used for veil deployment, then the device mass is reduced compared to rigid structures, but the reliability of deployment may be compromised
Solution Approach 1:
The inflatable deployment elements incorporate redundancy and cushioning mechanisms to ensure reliable deployment. Multiple inflation sources or backup systems are integrated, and the inflatable structure includes features that prevent failure modes such as punctures or improper inflation, thereby maintaining high reliability despite the reduced mass compared to rigid structures.
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 efficient capture and removal of large and/or mass objects from low orbit, preventing collisions and mitigating the debris problem by allowing controlled deorbiting or reorbiting, thereby stabilizing the orbital environment.
Implementation Method 1
at least one inflatable element extending over at least part of a peripheral edge of the veil and intended to cause the deployment of the veil when inflated
Implementation Method 2
means for connecting the vehicle to the veil and/or to the element, these means enabling a traction force to be applied to the captured object when the vehicle moves
Data Source
Figure 1~4
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Figure 8~11
AI summary
The device has a veil (14) that is spreadable in a folded position, and an inflation part (26) placed in a chamber. The veil is made of material that is selected from one of Kevlar (RTM: para-aramid synthetic fiber) and Dyneema (RTM: ultra high molecular weight polyethylene fiber). A fine membrane covers a net of the veil. A connecting part applies tensile force to a captured object when a vehicle (10) is moved by a motor unit e.g. chemical or electric rocket motor. The connecting part connects the vehicle to the veil and/or a component. Independent claims are also included for the following: (1) a system for capturing and coupling with a view to de-orbiting or re-orbiting of an object (2) a method for capturing and coupling with a view to de-orbiting or re-orbiting of an object.