On-Orbit Spacecraft Servicing System with Electromagnetic Capture
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Solution Overview
Problem
Current technologies lack the capability for efficient on-orbit servicing of spacecraft, including repair, de-orbiting, salvaging, and refueling, due to the high costs and complexities associated with existing servicing missions.
Innovation Solution
A modular spacecraft servicing system comprising multiple subsystems, including a host spacecraft with a deployable boom equipped with an electromagnet-based capture mechanism and a docking mechanism, along with a robotic manipulator arm for repairs and refueling.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If traditional servicing missions are used, then spacecraft can be serviced, but the cost and complexity are extremely high
Solution Approach 1:
The servicing system is divided into separate functional modules: a host spacecraft, a deployable boom with capture mechanism, and a robotic manipulator arm. Each module can be independently designed, tested, and assembled, reducing overall system complexity while maintaining servicing capability.
Solution Approach 2:
A deployable boom acts as an intermediary structure between the host spacecraft and the client spacecraft. The boom extends the reach of the host spacecraft, allowing capture and servicing operations without requiring direct docking or complex maneuvering.
2Ease of manufacture
If spacecraft are not designed with on-orbit servicing in mind, then launch costs are reduced, but servicing capability is lost
Solution Approach 1:
The host spacecraft is designed with universal interfaces and standardized capture mechanisms that can accommodate various types of client spacecraft. The robotic manipulator arm can perform multiple servicing functions including repair, replacement, and refueling, making the system adaptable to different mission requirements.
Solution Approach 2:
The deployable boom is designed to be extendable and reconfigurable, allowing the host spacecraft to adapt its reach and positioning capabilities based on the specific servicing task. This dynamic structure provides versatility without requiring multiple specialized spacecraft.
3Reliability
If a robust capture mechanism is used, then capture reliability is improved, but the capture envelope is limited
Solution Approach 1:
The capture mechanism utilizes spherical displacement freedom, allowing the electromagnets to move in multiple dimensions (radial, tangential, and spherical directions) to accommodate misalignments. This multi-dimensional adjustment capability expands the capture envelope while maintaining reliable capture through the electromagnet-striker plate interface.
4Adaptability or versatility
If standardized interfaces are implemented, then compatibility with different spacecraft is improved, but interface design complexity increases
Solution Approach 1:
The standardized interface is designed with localized functional elements: electromagnetic capture pads on the host spacecraft and corresponding striker plates on the client spacecraft. These localized interfaces provide standardized capture functionality without requiring complex overall system integration, as each component only needs to implement its specific local interface requirements.
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 flexible and efficient on-orbit servicing of spacecraft, reducing operational complexity and costs, while expanding the capture and work envelopes to accommodate a variety of repair tasks.
Implementation Method 1
The capture mechanism comprises one or more electromagnets spaced apart and suspended on a frame... The electromagnets on the host spacecraft attract the striker plate to capture the client spacecraft
Implementation Method 2
A compression spring is configured to provide compliance and slightly preload the spherical (or rod-end) bearing that supports the frame in a nominal position
Data Source
AI summary
A servicing system for on-orbit spacecrafts is disclosed. The system comprises a servicing or host spacecraft configured to perform on-orbit servicing of client spacecrafts. The servicing spacecraft comprises a dedicated, deployable, boom having capture and docking mechanisms. The capture mechanism comprises one or more electromagnets spaced apart and suspended on a frame that may include means for compensating for any out of plane misalignments during capture. The client spacecraft includes a striker plate that covers an area, nominally larger than the footprint of the capture mechanism, that is sized to accommodate a capture envelope determined by the rendezvous and proximity sensing systems. The electromagnets attract the striker plate to capture the client spacecraft in order to provide on-orbit servicing. The docking system has multiple degrees of freedom that are independent of the capture system; docking is accomplished by mechanically coupling the two spacecrafts together, post capture. During docking, electrical and fluid transfer connections may also be accomplished. The servicing spacecraft further comprises a manipulator arm that may be configured to position/align the captured client spacecraft for docking, thereby permitting a very flexible, larger, capture envelope, and reducing operational complexity.