Aircraft Power Distribution Architecture with Controllable DC Voltage Network
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Solution Overview
Problem
Existing power distribution architectures for aircraft electromechanical and electrohydrostatic actuators do not adequately ensure operator safety during maintenance and suffer from inverter losses, as they directly receive power from high-voltage aircraft buses without adjustable voltage levels, leading to potential hazards and inefficiencies.
Innovation Solution
A power distribution architecture that interposes a controllable DC voltage network between the aircraft's electrical power bus and the actuators, allowing for adjustable voltage levels to reduce risks for maintenance operators and minimize inverter losses, with features like chopper regulation, galvanic isolation, and voltage compensation to account for line impedance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If power distribution members directly receive power from high-voltage aircraft buses, then power delivery capability is sufficient, but maintenance operator safety is compromised due to high voltage exposure risks
Solution Approach 1:
A controllable DC voltage network is introduced as an intermediary between the high-voltage aircraft bus and the power distribution members. This intermediate network enables voltage transformation and control, allowing safe maintenance operations at reduced voltages while maintaining adequate power delivery capability when full voltage is required.
Solution Approach 2:
The DC voltage network is made dynamically controllable, allowing the voltage level to be adjusted in real-time based on operational requirements. During maintenance, voltage is reduced to safe levels; during normal operation, voltage is maintained at full capability levels, thus resolving the contradiction between safety and power delivery.
2Loss of energy
If fixed high-voltage power distribution is used, then power supply capability is adequate, but inverter losses increase due to inability to optimize voltage levels
Solution Approach 1:
The voltage parameter in the power distribution system is made variable through the controllable DC voltage network. By changing the voltage level according to the specific needs of different actuators and operational conditions, the system optimizes inverter efficiency and reduces energy losses while maintaining adequate power supply capability.
3Object-affected harmful factors
If voltage levels are reduced for safety, then operator safety improves, but power delivery to actuators may be insufficient
Solution Approach 1:
The system dynamically adjusts voltage levels based on operational context. During maintenance operations, voltage is reduced to safe levels for operator protection. During normal actuator operation, voltage is restored to adequate levels to ensure sufficient power delivery, thus resolving the contradiction between safety and power adequacy.
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 enhances safety by reducing electromagnetic emissions, minimizing voltage exposure risks for maintenance personnel, and optimizing power delivery to actuators, thereby reducing inverter losses and power demand on the aircraft's power bus, while allowing for flexible voltage adaptation and power recovery.
Implementation Method 1
a controllable DC voltage network which can be varied in a controlled manner is interposed between the electrical power bus of the aircraft and the power distribution member
Implementation Method 2
the power distribution member comprises an inverter
Data Source
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AI summary
The invention relates to an aircraft power distribution architecture for supplying power to electromechanical actuators (105, 106, 108; 205, 206, 208; 109A, 109B, 209A, 209B) of aircraft. The architecture comprises at least one power distribution element (150, 250, 160, 260) for distributing power to a specific electromechanical actuator connected to the architecture. The architecture receives power from at least one aircraft power supply bus (PW1, PW2). According to the invention, a variable DC power supply network (500) is interposed between the aircraft power supply bus and the power distribution elements.