Aircraft Power Bus Layout With Switchable Fault Isolation
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Solution Overview
Problem
Existing aircraft electrical power supply networks face safety risks due to the potential failure of a single distribution bus, which can lead to the loss of electrical propulsion motors and compromise flight safety, and current segmentation solutions require a high number of batteries, increasing mass and cost.
Innovation Solution
An electrical energy supply network with multiple generators and stators connected to two distribution buses, using contactors to connect or disconnect buses and rectifiers alternately, along with energy storage means like batteries and DC/DC converters, to isolate faults and distribute power sources and loads, ensuring network resilience and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If all power sources are connected to a single distribution bus, then the network structure is simple, but a failure of the distribution bus causes total network loss and compromises flight safety
Solution Approach 1:
The patent divides the single distribution bus into multiple distribution buses (at least two), connecting power sources and loads to different buses. This segmentation ensures that a failure in one bus does not affect the entire network, as loads can be supplied from other buses, thereby improving reliability while maintaining manageable complexity through systematic organization.
Solution Approach 2:
The patent assigns different functional roles to different parts of the network by connecting specific power sources and loads to specific distribution buses in an alternating pattern. This local differentiation allows for targeted fault isolation and maintains overall network functionality by ensuring that not all components are affected by a single point of failure.
2Reliability
If the network is segmented with multiple distribution buses, then reliability improves, but the number of batteries increases mass and cost
Solution Approach 1:
The patent merges the functions of multiple batteries into a single battery by connecting it to multiple distribution buses through contactors. This single battery can supply power to multiple buses, providing the same reliability benefits as multiple batteries would provide, while significantly reducing the total mass and cost of the energy storage system.
Solution Approach 2:
The single battery is designed to perform multiple functions by being able to supply power to different distribution buses as needed. Through the use of contactors, the battery can be dynamically connected to different buses, making it a universal power source that replaces the need for dedicated batteries for each bus, thereby reducing overall system mass.
3Reliability
If rectifiers are mounted alternately on distribution buses, then fault propagation is prevented, but the network configuration becomes more complex
Solution Approach 1:
The patent segments the rectifier configuration by mounting rectifiers alternately on different distribution buses rather than concentrating them on a single bus. This alternating arrangement creates natural fault isolation zones, where a failure in one rectifier or its associated bus does not propagate to other parts of the network, thereby improving reliability while maintaining a systematic and manageable configuration pattern.
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 configuration enhances the network's tolerance to power source failures, prevents propagation of faults, and maintains electrical load supply, reducing the risk of total network loss while minimizing battery usage and maintaining efficient power distribution.
Implementation Method 1
each comprising two stators, each stator being associated with a rectifier
Data Source
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AI summary
The invention concerns an electrical energy supply network (1) of an aircraft equipped with a plurality of electrical loads (C1, C2) to be supplied, the supply network (1) comprising at least two generators (2, 3) of a turbogenerator of the aircraft, each suitable for providing an electrical energy source, at least one stator associated with a rectifier (20a, 20b, 20c; 30a, 30b, 30c), characterised in that the stators of the generators (2, 3) are mounted in parallel on at least two distribution buses (4, 5) designed to supply the plurality of electrical loads (C1, C2), and in that it comprises contactors (100) suitable for electrically connecting or disconnecting the distribution buses (4, 5) from each other.