Aircraft DC Power Distribution With Redundant Propulsion Switching
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Solution Overview
Problem
Aircraft propulsion systems face challenges with high noise emissions, fossil fuel consumption, pollutant emissions, and operational safety, particularly in electric propulsion systems, which require redundancy and are often tailored to specific aircraft types, limiting flexibility and increasing mass.
Innovation Solution
A DC electrical power distribution device with a main and secondary power supply line, including switching means and control mechanisms, ensures redundancy and flexibility by reconfiguring power supply upon failure, using high-voltage DC sources to power propulsion assemblies.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If turbine engines are used for aircraft propulsion, then thrust is produced effectively, but noise emissions and pollutant emissions increase significantly
Solution Approach 1:
The patent replaces traditional turbine engines (mechanical combustion system) with electric motors powered by high-voltage DC sources. This substitution eliminates combustion processes, thereby eliminating noise and pollutant emissions while maintaining propulsion effectiveness through electromagnetic force generation.
2Reliability
If redundancy is implemented in electric propulsion systems to meet safety requirements, then operational safety is improved, but aircraft mass increases
Solution Approach 1:
The patent merges multiple power supply sources (main DC source and auxiliary DC source) into a unified power distribution system. The switching means enable these separate sources to be combined or isolated dynamically, providing redundancy for safety while sharing common infrastructure to minimize mass increase.
Solution Approach 2:
The patent implements dynamic switching capability that allows the system to adapt its configuration in real-time. The switching means can dynamically connect or disconnect power sources based on operational conditions, enabling the system to maintain safety redundancy only when needed, thereby reducing unnecessary mass.
3Reliability
If electrical network architecture is developed for a specific aircraft type and application, then system performance is optimized, but flexibility and reusability decrease
Solution Approach 1:
The patent designs a universal high-voltage DC power distribution system with standardized components and switching architecture that can be applied across different aircraft types and propulsion configurations. The modular design allows the same basic system to serve multiple functions and be adapted to various applications without complete redesign.
4Power
If high-voltage DC power distribution is implemented for electric propulsion, then propulsion efficiency is improved, but system complexity increases
Solution Approach 1:
The patent segments the power distribution system into distinct functional modules: power sources, switching means, and distribution lines. This segmentation allows each component to be optimized independently for high-voltage DC operation, improving overall propulsion efficiency while making the complex system more manageable and maintainable.
Data Source
AI summary
A DC electrical power distribution device for an aircraft propulsion duct having a main power supply line configured to supply at least one propulsion assembly of the propulsion duct with power from a high-voltage DC electrical power supply source and including main switching means and fast switching means for connecting the source to the propulsion assembly. The device can include a secondary power supply line configured to be connected to another distribution device and configured to supply the propulsion assembly with power from the other device when the main switching means are open.