Aircraft Power Network Reconfiguration for Shared Drive and Load Supply
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Solution Overview
Problem
Existing aircraft power supply networks are complex and poorly optimized, requiring a large number of electrical devices and networks to combine electricity distribution and drive functions.
Innovation Solution
A simplified aircraft power supply network architecture that integrates electricity distribution and drive functions in a reversible manner, using a single network with a first and second engine, loads, an auxiliary power source, electrical machines, converters, interconnection buses, and switches to isolate components and configure the network according to user needs.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a traditional aircraft power supply network integrates electricity distribution and drive functions separately, then the system can perform both functions, but the number of components (converters, electrical machines) increases and the architecture becomes complex
Solution Approach 1:
The patent applies multi-functionality by enabling the same power supply network components (electrical machines, converters, buses) to serve dual purposes: distributing electricity to loads and providing drive functions for engines. The network can operate in multiple modes (distribution mode, drive mode, hybrid mode) using the same hardware infrastructure, thereby eliminating the need for separate dedicated systems and reducing overall component count while maintaining full functionality.
2Reliability
If multiple separate networks are used for electricity distribution and drive functions, then each function can be optimized independently, but the total number of electrical devices increases
Solution Approach 1:
The patent merges the electricity distribution network and engine drive network into a single integrated power supply network. The same electrical machines, converters, and interconnection buses are used for both distributing power to aircraft loads and providing mechanical drive torque to engines. This consolidation reduces the total quantity of electrical devices while maintaining reliability through configurable operational modes that can optimize each function when needed.
Solution Approach 2:
Components are designed with universal functionality, where electrical machines can operate as motors for drive functions or as generators for electricity production, and converters can handle both distribution and drive power flows. This multi-functionality allows the system to maintain function-specific optimization through software control and mode configuration without requiring separate dedicated hardware for each function.
3Device complexity
If a simplified network with fewer components is used, then the device complexity is reduced, but the ability to isolate components during faults and reconfigure the network may be limited
Solution Approach 1:
The patent implements dynamic reconfigurability through controllable switches (primary switches and inter-bus switches) that can dynamically alter the network topology based on operational requirements and fault conditions. The system can switch between different operational modes (distribution mode, drive mode, hybrid mode) and isolate specific components or sections of the network as needed. This dynamic adaptability ensures that even with fewer physical components, the network maintains high configuration flexibility and can respond to various operational scenarios and fault conditions.
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 solution allows for efficient electricity distribution to loads and drive functions, such as starting or hybridizing engines, with a reduced number of components, ensuring reliability and flexibility in power supply configurations.
Implementation Method 1
a first electrical machine, mechanically connected to the first engine... The first electrical machine is configured to convert an electrical current into a mechanical force, advantageously into a mechanical torque at the corresponding engine
Data Source
AI summary
An aircraft power supply network and associated aircraft, the power supply network includes a first engine and a second engine, a first and a second set of loads, an auxiliary electrical source and a first electrical machine connected to the first engine. The power supply network also includes a first converter connected to the first electrical machine, a first interconnection bus connected to the first converter by a first primary switch and to the first set of loads and a second electrical machine connected to the second motor. The power supply network further includes a second converter, a second interconnection bus, connected to the second converter by a second primary switch and to the second set of loads, a sharing bus connected to the first interconnection bus by a first inter-bus switch, connected to the second interconnection bus by a second inter-bus switch and connected to the auxiliary electrical source.