Electric Aircraft Power Distribution via Electromagnetic Coupling
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Solution Overview
Problem
Conventional electric power distribution systems for electric aircraft face challenges in balancing weight and failure concerns, as additional hardware required for power transfer between battery packs increases weight and adds failure points.
Innovation Solution
A power distribution system that uses electromagnetic coupling between power stages and the rotor of an electric propulsion unit to transfer power between battery packs, eliminating the need for additional hardware and allowing for electrical isolation, thereby balancing power loads and reducing weight and failure points.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If additional hardware is used to transfer power between battery packs, then power transfer capability is improved, but weight increases and failure points increase
Solution Approach 1:
The patent replaces the mechanical/electrical connection system with an electromagnetic coupling system. Power is transferred between battery packs through electromagnetic fields generated by the motor stages, eliminating the need for physical power transfer hardware. This substitution of electromagnetic coupling for mechanical/electrical connections resolves the contradiction by enabling power transfer without adding weight or failure points.
2Power
If battery packs are electrically connected in parallel, then power output is increased, but failure propagation risk increases
Solution Approach 1:
The patent introduces the motor stages as an intermediary medium for power transfer between battery packs. Instead of direct electrical connection, power flows from Battery Pack 1 through the motor stages to Battery Pack 2. This intermediary coupling enables power sharing while maintaining electrical isolation, allowing power output to be increased without risking failure propagation between packs.
3Weight of moving object
If electromagnetic coupling is used for power transfer, then weight is reduced and failure isolation is improved, but system complexity increases
Solution Approach 1:
The patent makes the motor stages multi-functional by having them serve both their primary propulsion function and a secondary power transfer function. The same motor stages that drive the aircraft also mediate electromagnetic coupling between battery packs. This universality resolves the complexity issue by eliminating dedicated power transfer hardware, as the existing motor stages perform dual purposes.
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
This solution enables efficient and safe power distribution across battery packs, reducing weight and failure points, and allowing for operation within a safe and energy-efficient range during flight by transferring power through the electric propulsion unit.
Implementation Method 1
Power from one battery pack can be transferred to another battery pack via electromagnetic coupling between the power stages and the rotor of the electric propulsion unit
Data Source
AI summary
A power distribution system for an electric aircraft includes a first electric propulsion unit comprising at least two power stages; a first battery pack electrically connected to a first power stage of the at least two power stages; a second battery pack electrically connected to a second power stage of the at least two power stages; and a control system configured to control the first battery pack, the second battery pack, the first power stage, and the second power stage to transfer power from the first battery pack to the second battery pack through the first power stage and the second power stage.