Distributed Spacecraft Architecture for Multi-Object Debris Removal
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Solution Overview
Problem
Existing methods and systems for deorbiting satellites and space debris face challenges in safely and economically achieving high delta V, rendezvous with large tumbling objects, and precise atmospheric reentry trajectories, as they require conflicting design characteristics that increase cost and risk.
Innovation Solution
A distributed spacecraft architecture comprising a tug, servicer, and reentry shepherd, each with distinct capabilities, works together to achieve delta V, rendezvous, and targeted reentry, distributing the required functionalities across multiple vehicles.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single spacecraft performs all functions (rendezvous, capture, deorbiting), then device complexity is reduced, but reliability decreases due to conflicting design requirements
Solution Approach 1:
The system divides the debris removal mission into three specialized spacecraft: a servicer for rendezvous and capture, a tug for orbital maneuvers, and a reentry shepherd for controlled atmospheric entry. Each component performs a specific function, allowing optimization for that particular task rather than requiring a single multi-functional spacecraft.
Solution Approach 2:
The servicer spacecraft is designed with universal capabilities to service multiple types of debris objects through standardized capture mechanisms, while working within the larger distributed system that handles different mission phases.
2Speed
If high delta V is achieved for deorbiting, then deorbiting capability is improved, but cost increases due to substantial fuel requirements
Solution Approach 1:
The delta V requirement is segmented across multiple spacecraft. The tug provides substantial delta V for orbital maneuvers, while the reentry shepherd provides the final delta V for atmospheric entry. This distributes the fuel mass requirement across separate vehicles rather than requiring one massive fuel tank.
Solution Approach 2:
The reentry shepherd is designed to be discarded after providing the final deorbiting impulse, as it enters the atmosphere with the debris. This allows the system to carry substantial fuel for the shepherd without permanently increasing the mass of reusable components.
3Reliability
If precise atmospheric reentry trajectory is achieved, then safety is improved, but device complexity increases due to specialized guidance requirements
Solution Approach 1:
The guidance function is segmented and assigned specifically to the reentry shepherd, which carries the specialized guidance and control systems needed for precise atmospheric entry. The servicer and tug focus on their respective functions without requiring complex reentry guidance capabilities.
4Ease of manufacture
If reusable components are implemented, then cost decreases through reusability, but reliability decreases due to reentry risks
Solution Approach 1:
The system segments reusable and disposable components. The servicer and tug are designed for reuse and can return to orbit after servicing missions. The reentry shepherd is designed as a disposable component that enters the atmosphere with the debris, isolating the reentry risks from the reusable parts.
Data Source
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AI summary
According to an aspect of the present invention, there is provided a method for rendezvous with an orbiting object comprising: launching a tug and a servicer into a client orbit; separating the servicer from the tug; and docking the servicer with a client. According to another aspect of the present invention, there is provided system for rendezvous with an orbiting object comprising: a first spacecraft comprising a tug capable of towing a second spacecraft, wherein the second spacecraft is a servicer configured to dock with a tumbling client orbiting object.