Aircraft HVDC Power Supply Parallel Network Control
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Solution Overview
Problem
Aircraft electrical power systems face challenges in maintaining high availability and minimizing noise and failure rates, especially when transitioning from hydraulic or pneumatic systems to electrical energy, requiring a robust and efficient high voltage direct current power supply system.
Innovation Solution
A high voltage direct current power supply system for aircraft comprising multiple electrical power supply networks with alternators, rectifiers, low-pass filters, and switches, connected in parallel through intermediate lines, with a control device that enslaves alternators in current to dynamically distribute power based on operational needs and availability, ensuring stable and noise-reduced power delivery.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If multiple electrical power supply networks are connected in parallel to improve availability, then the reliability of power supply increases, but the complexity of the power distribution system increases
Solution Approach 1:
The power distribution system is segmented into multiple independent electrical power supply networks (first network with first alternator, second network with second alternator), each capable of independently supplying power to secondary lines. This segmentation allows the system to maintain high availability through parallel operation while managing complexity by creating modular, independently controllable units.
Solution Approach 2:
Each power supply network is designed with multi-functionality to perform multiple roles: primary power supply, backup power supply, and dynamic load sharing. The control device enables each network to adapt its function based on operational status and flight parameters, reducing the need for dedicated backup systems and simplifying the overall architecture.
2Adaptability or versatility
If current control is applied to alternators to enable dynamic power distribution, then the adaptability of power supply meets operational needs, but the control system complexity increases
Solution Approach 1:
The control device implements dynamic current control of alternators based on real-time operational status and flight parameters. The current control setpoints are continuously adjusted to optimize power distribution across networks, enabling the system to adapt to changing load conditions and maintain stability throughout flight phases.
Solution Approach 2:
The control device employs feedback mechanisms by continuously monitoring the operational status of power supply networks and adjusting current control setpoints accordingly. This closed-loop control ensures that power distribution adapts to actual system conditions while maintaining stability, with the control device playing on the presence of several networks to ensure adequate power supply.
3Object-affected harmful factors
If power supply outputs are connected between networks before connecting to intermediate lines, then noise is minimized through stable power delivery, but the device complexity increases
Solution Approach 1:
The power supply outputs of multiple networks are merged together before connecting to intermediate lines through a common connection point. This merging stabilizes the power delivery by allowing networks to support each other, minimizing noise and disturbances. The control device coordinates this merged connection to ensure smooth power transitions and reduce electromagnetic interference.
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
The system achieves high availability, low failure rates, and minimized noise by dynamically redistributing power across multiple networks, preventing power jumps and disturbances, and prioritizing main engine networks while adjusting with auxiliary power, ensuring reliable electrical power supply to aircraft systems.
Implementation Method 1
a first electrical power supply network comprising a first alternator, a second electrical power supply network comprising a second alternator
Data Source
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AI summary
The invention concerns a power supply system for an aircraft comprising a first power supply network (1) comprising a first alternator (10), a second power supply network (2) comprising a second alternator (20), secondary lines (40) gathered into at least one first group (41) so as to be connected via switches to a same first intermediate line (51) and into at least one second group (42) so as to be connected via switches to a same second intermediate line (52), the system comprising a control unit (60) for controlling the power supply networks, the control unit being arranged to control the current of each of the alternators, the system being arranged such that power supply outlets of the two power supply networks are connected to each other before being connected to each intermediate line, each intermediate line being supplied in parallel by the two power supply networks.