Aircraft Power Distribution Circuits for Balanced Failure Isolation
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Solution Overview
Problem
Electrically powered aircraft require improved power distribution systems to ensure redundancy and stability in the event of failure events, such as battery failures, to maintain balanced propulsion and aircraft stability.
Innovation Solution
A power distribution system with multiple isolated power distribution circuits and batteries, each coupling to balanced propulsion systems, including contactors and current meters to manage power distribution and decouple batteries when threshold currents are exceeded, ensuring balanced forces and stable aircraft operation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple batteries are used to power multiple electric propulsion systems, then reliability is improved, but device complexity increases
Solution Approach 1:
The power distribution system is divided into multiple isolated power distribution circuits, where each circuit independently couples a battery to two or more electric propulsion systems. This segmentation allows individual circuit failures to be contained without affecting the entire system, thereby improving reliability while managing complexity through modular architecture.
Solution Approach 2:
The system incorporates contactors that can automatically decouple batteries from electrical busses when threshold currents are exceeded or minimum threshold currents are not satisfied. This preliminary protective action prevents failure propagation before it can affect other parts of the system, enhancing reliability without requiring complex manual intervention systems.
2Reliability
If power distribution circuits are isolated and redundant, then reliability is improved, but device complexity increases
Solution Approach 1:
Each power distribution circuit is designed to be universally configurable, coupling a battery to two or more electric propulsion systems through electrical busses. This multi-functional design allows the same circuit architecture to serve multiple propulsion systems with different power requirements, improving reliability through redundancy while reducing complexity by avoiding custom-designed circuits for each configuration.
3Reliability
If contactors are used to decouple batteries, then reliability is improved, but device complexity increases
Solution Approach 1:
The contactors are configured to automatically decouple batteries from electrical busses when threshold currents are exceeded or minimum threshold currents are not satisfied. This self-service capability allows the system to automatically respond to failure conditions without requiring external control systems or manual intervention, improving reliability through rapid isolation while minimizing the complexity of control architecture.
4Reliability
If current meters are used to monitor battery current, then reliability is improved, but device complexity increases
Solution Approach 1:
Current meters are coupled to each battery to measure current entering or exiting the battery, providing real-time feedback on battery status. This feedback mechanism enables the system to detect when threshold currents are exceeded or minimum threshold currents are not satisfied, triggering automatic decoupling actions that improve reliability while maintaining relatively simple monitoring architecture.
Data Source
AI summary
A power distribution circuit for an electrically powered aircraft includes a plurality of batteries and a plurality of electric propulsion systems. A plurality of power distribution circuits each couple a battery of the plurality of batteries to two or more electric propulsion systems. The plurality of electric propulsion systems are positioned on the aircraft to apply balanced forces to the aircraft such that in the event of a failure, the aircraft remains stable and only experiences a loss in altitude or speed.