Electropermanent Magnet Modular Service Interface for Spacecraft
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Solution Overview
Problem
Current spacecraft and satellite servicing technologies lack simple, robust, and lightweight modular interfaces that enable efficient and cost-effective servicing and upgradability of space assets, particularly in scenarios where direct human intervention is not feasible due to distance and communication delays.
Innovation Solution
A modular service interface utilizing electropermanent magnets for bi-stable latching with no moving parts, providing a standard compact interface for various client objects, including spacecraft and satellites, allowing for easy attachment and detachment of payloads and components, and enabling scalable configurations for different functions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If mechanical grippers are used to capture spacecraft, then reliable capture can be achieved, but the system becomes heavy and complex with mechanical actuators
Solution Approach 1:
The patent replaces mechanical grippers and actuators with electropermanent magnets that use electromagnetic fields to capture and hold spacecraft. The magnets can be activated or deactivated electrically to control attachment and detachment, eliminating complex mechanical moving parts while maintaining reliable capture capability
Solution Approach 2:
The patent changes the operational parameter from mechanical force application to electromagnetic field activation. By controlling the magnetic field state (on/off), the system achieves capture and release functions without mechanical actuators, reducing complexity while maintaining reliability
2Strength
If heavy mechanical connections are used for spacecraft servicing, then strong attachment can be achieved, but the system mass increases significantly
Solution Approach 1:
The patent substitutes heavy mechanical connection structures with lightweight electropermanent magnet assemblies. The magnets provide sufficient attachment strength through electromagnetic attraction while being significantly lighter than equivalent mechanical fastening systems
Solution Approach 2:
The patent uses ferromagnetic materials in the interface design to enable magnetic attachment. These materials allow the structure to be both lightweight and provide strong magnetic coupling, achieving high attachment strength without increasing mass
3Ease of operation
If mechanical grippers with moving parts are used, then capture function can be achieved, but the risk of mechanical failure increases
Solution Approach 1:
The patent eliminates mechanical moving parts in the capture mechanism by using electropermanent magnets. The magnets have no moving components that can wear or fail, yet still provide the necessary capture function through electromagnetic attraction that can be controlled electrically
Solution Approach 2:
The electropermanent magnets maintain their magnetic state without requiring continuous energy input or mechanical adjustment. Once activated, they self-maintain the capture function without mechanical intervention, reducing failure risk from mechanical wear and actuator malfunction
4Reliability
If traditional docking mechanisms are used, then secure connection can be achieved, but the system becomes less adaptable to different spacecraft configurations
Solution Approach 1:
The patent designs the electropermanent magnet interface to be universally applicable to different spacecraft configurations. The magnetic attachment mechanism can accommodate various spacecraft shapes and sizes without requiring specialized mechanical docking structures for each configuration
Solution Approach 2:
The patent uses controllable magnetic field parameters to adapt to different spacecraft. By adjusting magnetic field strength and distribution, the same interface can securely connect to various spacecraft configurations, providing both reliability and versatility
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 modular service interface offers a lightweight, low-energy, and low-mass solution with reduced risk of mechanical failure, enabling efficient servicing and upgradability of space assets, including satellites and spacecraft, while minimizing the need for heavy mechanical connections and reducing strain from thermal conditions.
Implementation Method 1
one or more electropermanent magnet modules configured to mate the first and second halves when activated
Implementation Method 2
allow the first and second halves to be separated when inactivated
Data Source
AI summary
A modular service interface is provided. The modular service interface includes separable first and second halves, one or more alignment features, a connector interface and one or more electropermanent magnet modules, connector interface configured to mate the first and second halves when activated and allow the first and second halves to be separated when inactivated. The modular service interface includes no mechanical actuators to retain the first half to the second half.