Aircraft Power Distribution Architecture for Sequential Actuation
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Solution Overview
Problem
The existing electrical power distribution architectures for aircraft are heavy due to the presence of dedicated power electronics for each electromechanical actuator, which is inefficient as many aircraft elements are actuated in sequence, allowing for potential power pooling.
Innovation Solution
A power distribution architecture that uses a common power distribution member with calibration and switching means to direct power to electromechanical actuators as needed, eliminating the need for multiple power electronics by leveraging the sequential actuation of aircraft elements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If dedicated power electronics are provided for each electromechanical actuator, then each actuator can be powered independently and reliably, but the overall mass of the power distribution system increases significantly
Solution Approach 1:
The patent merges multiple dedicated power electronics into a single shared power distribution member that serves multiple actuators. This power distribution member includes a calibration unit and switching means that can dynamically allocate power to different actuators, achieving mass reduction while maintaining the ability to independently control each actuator when needed.
Solution Approach 2:
The shared power distribution member is designed to serve multiple functions and multiple actuators simultaneously. It can calibrate and direct power to any connected actuator, making a single device replace multiple dedicated power electronics, thereby reducing overall system mass while preserving actuator-specific control capabilities.
2Adaptability or versatility
If multiple power electronics are used for each actuator, then power can be supplied to all actuators simultaneously, but the device complexity and mass increase
Solution Approach 1:
The patent introduces a switching means as an intermediary component within the shared power distribution member. This switching means acts as a mediator that can dynamically connect or disconnect different actuators from the power source, enabling flexible power allocation without requiring separate dedicated power electronics for each actuator, thus simplifying the overall architecture.
3Weight of stationary object
If a common power distribution member is used for multiple actuators, then mass is reduced, but the ability to supply power to multiple actuators simultaneously is limited
Solution Approach 1:
The patent implements dynamic switching capability within the shared power distribution member. The switching means can rapidly reconfigure power connections between different actuators, allowing the system to adapt in real-time. This dynamic capability enables the single power distribution member to effectively support both sequential and simultaneous actuation scenarios, maintaining productivity while reducing mass.
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 significantly reduces mass by pooling power distribution for sequentially actuated elements, ensuring efficient power delivery while maintaining redundancy and adaptability to actuator failures, thus enhancing the overall efficiency and reliability of the system.
Implementation Method 1
calibration means for calibrating the electric power coming from the power bus of the aircraft
Implementation Method 2
switching means for selectively directing the calibrated power to one or other of the electromechanical actuators
Data Source
Figure 1~3D
Figure 2
AI summary
The invention relates to an electrical power distribution architecture specifically adapted for sequentially actuating moving parts of an aircraft, such as doors, landing gear, or high-lift devices. These moving parts are actuated by electromechanical actuators sequentially powered by electrical power supplied from at least one of the aircraft's power buses. According to the invention, the architecture comprises at least one power distribution unit (710, 720, ... 760) including: - calibration means (711, 721, ... 761) for calibrating the electrical power from the aircraft's power bus; - and switching means (712, 722, ... 762) for selectively directing the calibrated power to one or another of the electromechanical actuators.