A spacecraft refueling concept built around a Universal Magnetic Docking Interface for passive alignment, secure coupling, and fluid transfer.
The team developed a mechanical-magnetic docking architecture intended to reduce the complexity and precision required by conventional spacecraft refueling interfaces.
The concept combines coarse mechanical alignment, magnetic capture, locking hardware, sealing features, and a fluid-transfer path into a modular spacecraft interface.
Space Systems Design, Validation & Mechanical Subsystem Development
I contributed to both the systems-level development of the spacecraft refueling concept and the detailed development of mechanical interface hardware.
- Developed validation criteria for magnetic coupling strength, leakage, repeatability, and docking stability.
- Established a leakage target of less than 1% of transferred volume and a repeatability target of more than 10 successful coupling cycles.
- Analyzed alignment behavior, magnetic placement, and docking geometry through engineering trade studies.
- Contributed to development of the passive self-aligning magnetic capture approach to improve docking tolerance and reduce dependence on precision-guided mechanisms.
- Designed the spring-loaded release subsystem and developed the spring-retention and locking mechanism for controlled deployment.
- Supported subsystem assembly integration and verified fit between mechanical interface components.
- Contributed to engineering drawings, technical documentation, and project design reviews.
- Supported system architecture, engineering requirements, trade studies, and iterative concept development.
The complete refueling architecture was developed collaboratively by the multidisciplinary team. This section identifies my individual design, validation, and systems-engineering contributions.
The team proposed a mechanical-magnetic hybrid docking interface intended to provide passive alignment and stable engagement during fluid transfer.
The concept included magnetic coupling plates, mechanical alignment features, a locking mechanism, sealing elements, a central fluid-transfer path, and instrumentation for testing.
Coarse alignment transitions into passive magnetic capture and mechanical locking.
The spacecraft interfaces move within the allowable docking capture region.
Mechanical geometry guides the two docking bodies toward the correct orientation.
Permanent magnets provide passive final alignment and pull the interfaces together.
The mechanical interface secures the connection for controlled fluid transfer.
Spring-loaded mechanical release for controlled deployment and separation.
My mechanical-design work included development of the release subsystem used to control engagement and separation of interface components.
Spring loading provides controlled mechanical motion during release.
The retention mechanism maintains the required configuration before commanded release.
Mechanical interfaces were evaluated for assembly fit and subsystem integration.
Measurable success criteria were established so the docking concept could be evaluated objectively.
Maintain sufficient magnetic engagement during the transfer operation.
Limit fluid loss to less than 1% of transferred volume.
Demonstrate more than ten coupling cycles without significant degradation.
Maintain alignment and connection stability during docking and transfer.
- Achieving sufficient magnetic attraction without making separation unnecessarily difficult.
- Providing docking tolerance for translational and rotational misalignment.
- Maintaining a reliable seal during fluid transfer.
- Integrating mechanical locking, magnetic capture, and fluid-transfer hardware within the same interface.
- Designing for repeatability and multiple coupling cycles.
- Balancing system complexity, mass, structural reliability, and spacecraft compatibility.
The project explored how passive magnetic capture and mechanical alignment could simplify spacecraft docking and refueling.
The design required systems-level tradeoffs across mechanical design, magnetics, sealing, fluid transfer, reusability, docking tolerance, and structural reliability.
My work strengthened my experience in aerospace systems design by connecting high-level requirements with detailed mechanical subsystem design and measurable validation criteria.
Final Technical Proposal
The complete proposal includes system architecture, technical requirements, mechanical concepts, performance criteria, drawings, project planning, and supporting engineering analysis.