Aircraft Engine Controller Power Distribution System
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Solution Overview
Problem
Conventional aircraft engine power systems require redundant batteries and alternators, increasing aircraft weight and reducing payload capacity, and can lead to engine controller inoperability in case of dual alternator failure, disrupting flight operations.
Innovation Solution
An aircraft engine power distribution system utilizing a magnetic generator driven by the aircraft engine, with a power distributor that provides primary power to the engine controller and switches to airframe power in case of generator failure, minimizing the need for additional batteries and providing a warning for safe landing.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional airframe power systems use two batteries with one as primary and one as backup, then the engine controller can continue operation in case of primary battery failure, but the overall weight of the aircraft increases and payload capacity is reduced
Solution Approach 1:
The patent extracts the power supply function from the conventional airframe power system by implementing a dedicated generator-driven power system for the engine controller. This separate power system includes a generator coupled to the engine, a power distributor, and a battery, eliminating the need for the engine controller to depend on the aircraft's main battery system and reducing overall aircraft weight while maintaining operational reliability
Solution Approach 2:
The patent segments the power supply system into two independent parts: (1) a dedicated engine controller power system with its own generator, power distributor, and battery, and (2) the conventional airframe power system. This segmentation allows the engine controller to operate independently of the aircraft's main power system, ensuring continuity of operation while reducing the need for redundant batteries in the airframe system
2Reliability
If conventional airframe power systems use two separate alternators to charge corresponding batteries, then each battery can be independently charged, but the system complexity increases and more components can fail
Solution Approach 1:
The patent merges the power generation and storage functions into a compact integrated unit consisting of a generator coupled directly to the engine, a power distributor with built-in rectification and voltage regulation capabilities, and a battery. This consolidated architecture provides the same redundancy and reliability as separate alternator-battery systems but with fewer discrete components and reduced system complexity
Solution Approach 2:
The dedicated generator is directly coupled to the engine and automatically generates power for the engine controller without requiring external control or intervention. The power distributor automatically manages power distribution and charging, and the system provides self-monitoring with warnings only when the dedicated generator fails, eliminating the need for complex monitoring systems required in conventional dual alternator configurations
3Power
If field coil machines (alternators) are used to generate power, then electrical power can be produced, but additional batteries are required to charge the field coils during operation, increasing weight
Solution Approach 1:
The patent replaces the conventional field coil alternator system with a permanent magnet generator. The permanent magnets provide the magnetic field necessary for electromagnetic induction without requiring external electrical excitation, eliminating the need for field coil batteries and reducing overall system weight while maintaining full electrical power generation capability
Solution Approach 2:
The patent changes the fundamental operating parameter of the generator from requiring external field excitation (conventional alternator) to using permanent magnets with fixed magnetic fields. This parameter change eliminates the need for additional batteries to charge field coils, as the permanent magnets inherently provide the necessary magnetic flux for power generation
4Reliability
If both alternators in the airframe power system fail, then the aircraft loses its primary power source, but the engine controllers can still draw power from batteries until they drain, eventually becoming inoperable
Solution Approach 1:
The patent implements a dedicated generator that is pre-coupled to the engine and automatically activates to provide power to the engine controller when the conventional airframe power system fails. The power distributor continuously monitors power availability and automatically switches to the dedicated generator in advance of complete battery depletion, ensuring uninterrupted operation of the engine controller
Solution Approach 2:
The power distributor acts as an intermediary device that manages power flow between the conventional airframe power system and the dedicated generator. It continuously monitors the status of both power sources and automatically switches between them, providing seamless power transition and extending the duration of engine controller operation by preventing direct battery drain while maintaining continuous power supply
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 ensures continuous operation of the engine controller regardless of airframe power system status, reduces aircraft weight, and allows for safe transition to backup power, enhancing flight safety and payload capacity.
Implementation Method 1
a generator driven by an aircraft engine and a power distributor in electrical communication with the generator. The generator is configured to produce a generator power output when driven by the aircraft engine
Data Source
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AI summary
An aircraft engine power distribution system (28) for an aircraft engine controller (26), such as a FADEC, is provided where the power source (22) is independent from the conventional airframe power system, without the need for a back-up battery. The aircraft engine power distribution system includes a magnetic generator (26) operated by an aircraft engine. The aircraft engine power distribution system also includes a power distributor (24) that rectifies the generator output and provides the rectified power to the engine controller as its primary source of power. In this configuration, as long as the aircraft engine is able to operate the magnetic generator, the engine controller receives power. Accordingly, the engine controller operates regardless of the operational status of the airframe power system.