Electric Aircraft Ring Bus Reconfiguration for Fault Load Redistribution
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Solution Overview
Problem
Managing electrical power distribution in electric aircraft is challenging, especially when power needs to be redistributed due to system faults, requiring effective and timely solutions to maintain aircraft performance.
Innovation Solution
A ring bus system connected to a controller that can selectively merge bus sections from different energy sources to redistribute electrical load, compensating for faults by actuating switches to form an electrical merger between bus sections and redistribute power.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If the electrical power distribution system operates with multiple energy sources and bus sections, then the power supply reliability is improved, but the system complexity increases
Solution Approach 1:
The electrical power distribution system is divided into multiple independent bus sections (first bus section, second bus section) that can be selectively connected or isolated. Each bus section can be independently managed and controlled, allowing the system to maintain power supply to critical components even when faults occur in specific sections, thereby improving reliability while managing complexity through modular organization
Solution Approach 2:
The system employs dynamic reconfiguration capabilities through controllable switches that can alter the connectivity topology in real-time. When faults are detected, the controller dynamically repositions switches to isolate faulty sections and redistribute power flow, enabling the system to adapt its structure based on operational conditions, thus maintaining reliability without requiring a permanently complex fixed architecture
2Productivity
If the system redistributes electrical load to compensate for faults, then the aircraft performance is maintained, but the control complexity increases
Solution Approach 1:
The electrical power distribution system incorporates automatic fault detection and response capabilities. The controller autonomously monitors the health status of energy sources and bus sections, and when faults are detected, automatically executes load redistribution algorithms without requiring manual intervention. This self-service approach maintains aircraft performance during faults while managing control complexity through automation rather than complex manual procedures
Solution Approach 2:
The system implements continuous monitoring of power distribution status, fault conditions, and load requirements. Based on feedback from these monitoring systems, the controller dynamically adjusts switch positions and power flow distribution to maintain optimal aircraft performance. This feedback-driven control approach enables the system to respond adaptively to changing conditions while managing complexity through closed-loop control rather than overly complex open-loop systems
Data Source
AI summary
A system for redistributing electrical load in an electric aircraft. The system includes a ring bus and a controller communicatively connected to the ring bus. The ring bus includes a plurality of bus sections including a first bus section and a second bus section. The controller is configured to receive a fault datum indicative of a fault associated with one of a first energy source and a second energy source, actuate, as a function of the fault datum, at least a switch to electrically connect the first bus section and the second bus section so as to form an electrical merger of the first bus section and the second bus section, and redistribute the electrical load to compensate for the fault associated with one of the first energy source and the second energy source. A method of redistributing electrical load in an electric aircraft is also provided.