Electromagnetic Kinematic Joint for Modular On-Orbit Spacecraft Assembly
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Solution Overview
Problem
Current spacecraft integration technologies are not designed for on-orbit servicing or assembly, requiring human labor, are mass-optimized for launch loads, and lack modularity, making them expensive and unsuitable for robotic operations.
Innovation Solution
A payload-bus kinematic interface system using electropermanent magnets (EPMs) and kinematic devices with complementary surfaces to provide a mechanical connection that supports on-orbit maneuver loads, allows remote control, and facilitates modular assembly and maintenance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional fastening hardware and human labor are used for spacecraft assembly, then the connection strength and reliability are sufficient for launch loads, but the assembly cost increases, modularity is lost, and on-orbit servicing becomes impossible
Solution Approach 1:
The patent replaces traditional mechanical fastening systems (bolts, screws, welds) with an electromagnetic coupling system that uses magnetic fields to achieve mechanical connection. The electromagnetic interface uses magnetically attractable materials and electromagnetic actuators to create secure connections without mechanical fasteners, enabling robotic operation while maintaining connection strength.
Solution Approach 2:
The electromagnetic interface system provides self-alignment and self-latching capabilities through magnetic attraction forces. The magnetically attractable materials automatically guide the docking process and maintain connection without requiring precise mechanical alignment or manual intervention, reducing assembly complexity while ensuring reliable connections.
2Strength
If traditional interfaces are mass optimized for launch loads, then the structure survives launch, but the interface cannot support on-orbit maneuver loads and servicing operations
Solution Approach 1:
The electromagnetic interface system transitions from a static mechanical connection to a dynamic controllable connection. The electromagnetic actuators can adjust the connection state in real-time, allowing the interface to adapt to different operational phases (launch, on-orbit maneuvering, servicing) by modulating the electromagnetic field strength and control forces applied to magnetically attractable materials.
Solution Approach 2:
The system changes the physical state and properties of the connection by utilizing magnetically attractable materials that respond to electromagnetic field variations. By changing the electromagnetic field parameters (strength, direction, timing), the connection characteristics can be adjusted to suit different operational requirements, from launch vibration resistance to on-orbit maneuvering precision.
3Reliability
If unique mission-specific interfaces are used, then the spacecraft is optimized for its specific mission, but modularity is lost and component replacement becomes difficult
Solution Approach 1:
The electromagnetic interface system provides a universal docking standard that can be applied across different spacecraft and payloads. The standardized electromagnetic interface with magnetically attractable materials allows the same connection mechanism to serve multiple functions (structural support, electrical connection, thermal management) and enables interchangeability of components without mission-specific customization, facilitating modularity and ease of replacement.
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 on-orbit assembly and servicing of spacecraft without human intervention, reducing mass and power requirements, and providing a standardized interface for connection and disconnection of spacecraft components.
Implementation Method 1
Each of the plurality of EPMs apply a magnetically induced preload
Implementation Method 2
The magnetically induced preload with the first contacting surface and the second contacting surface constrain up to 6 degrees of freedom (DOF)
Data Source
AI summary
A payload-bus kinematic interface system includes one or more kinematic devices. Each kinematic device includes a first contacting surface and a second contacting surface. The first contacting surface kinematically interfaces with the second contacting surface, passing loads or forces to the second contacting surface.