- À paraître
Airplanes electrification began during the First World War with engine ignition systems and wireless telegraphy in military aircraft. At that time, generators were of a DC type and rated at less than 500W. The voltage system was 6V, like in the automotive industry, or 12V when more power was required. But the number of consumers grew quickly with the installation of lighting, signaling and heating systems so that the distributed voltage became 28VDC before the Second World War.
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Rubrique :
Électricité – Électro. – Hydraulique
ISBN :
9782383953098
Référence :
2309
À paraître
Airplanes electrification began during the First World War with engine ignition systems and wireless telegraphy in military aircraft. At that time, generators were of a DC type and rated at less than 500W. The voltage system was 6V, like in the automotive industry, or 12V when more power was required. But the number of consumers grew quickly with the installation of lighting, signaling and heating systems so that the distributed voltage became 28VDC before the Second World War.
After the Second World War, aircraft size and speed increase required more power to supply all the loads. Because of its better reliability and power density, AC generation established itself as a supplement to the DC one, and constant speed 115VAC / 400Hz generators became the standard voltage system for commercial aircraft in the early 1960s.
To adapt to engine speed and because of the growing systems demand, AC power is nowadays provided by 230VAC Variable Frequency Generators, like in the AIRBUS A350 or the BOEING B787, rated at 100kVA for the A350 and 250kVA for the B787.
Tomorrow, with the planned deletion of pneumatic and hydraulic networks, the embedded power is likely to exceed 1MW and even more in case of hybrid or full electric propulsion. To reduce cabling weight, the order of magnitude of the foreseen supply voltage is 1kV.
Electrification is therefore a deep and long-lasting trend in the aircraft industry due to the high flexibility and superior performance of this source of energy. At the center of electrical architectures, the distribution system occupies a prominent place. In addition to connecting the sources to the loads, it ensures crucial functions for the aircraft like devices protection against electrical hazards or network reconfiguration in case of sources failure.
Little literature is available to describe what an aircraft electrical distribution system is. That is why the authors have undertaken to capitalize all their knowledge about it in this work. The topics addressed are centered around the functions performed by the distribution system: supply loads, reconfigure the network as per sources availability, monitor and guarantee the network integrity, communicate with other aircraft controllers, inform about its status. These functions are detailed in different chapters with elements of the technologies used to implement them. The distribution system itself is presented afterwards in a dedicated section. This book ends with design considerations about Power Distribution Units: electrical installation, lightning strike protection, bonding / grounding, corrosion, mechanical and thermal design.
It was written for “self-starter” electrical engineers but also for those who want to upgrade their knowledge in that matter. It does not provide a level of detail that one can find in design notes or maintenance manuals but rather provides information helping the reader understand the current and upcoming stakes of electrical distribution in civil aviation. It will also be of help to electrical engineering or aeronautics students who would like to specialize in this field.
| Référence : | 2309 |
| Nombre de pages : | 574 |
| Format : | 16x24 cm |
| Reliure : | Broché |
| Rôle | |
|---|---|
| Collectif | Auteur |
| Bareille Michel | Coordonnateur |
1. Introduction
2. EPDS loads supply function
2.1. Power commutation: switches, relays, contactors
2.1.1. Switches
2.1.2. Relays
2.1.3. Contactors
2.2. Power routing
2.2.1. Wires and cables
2.2.2. Busbars
2.3. Interfacing sources and loads
2.3.1. Connectors
2.3.2. Solderless terminations
3. EPDS protection function
3.1. Electrical network or systems failure cases
3.1.1. Systems inrush current
3.1.2. Overcurrent – Short-circuit
3.1.3. Ground Fault Protection
3.1.4. Differential protection
3.1.5. Partial Discharges
3.1.6. Arc Fault Detection
3.1.7. Leakage between different power supply systems
3.2. Electrical Protection types
3.2.1. Generalities on electrical protection devices
3.2.2. Thermal Circuit Breakers
3.2.3. Electro-mechanical Circuit Breakers
3.2.4. Silicon and Silicon Carbide (SiC) MOS transistor
3.2.5. Insulated Gate Bipolar Transistor (IGBT)
3.2.6. Fuses
3.2.7. Pyroswitches – Pyrofuses
3.2.8. IMD “Insulation Monitoring Device”
4. EPDS network supervision function
4.1. Sensors
4.1.1. Current sensors
4.1.2. Voltage sensors
4.1.3. Temperature sensors
4.2. Network supervision principles
4.2.1. Introduction
4.2.2. General network management principles
4.2.3. Electrical sources connection
4.2.4. Electrical loads management
5. EPDS communication function
5.1. Generalities - Constraints on aircraft electrical signals
5.2. Signals
5.2.1. Analog signals
5.2.2. Discrete signals
5.3. Bus communication
5.3.1. Bus communication networks basics
5.3.2. ARINC 429
5.3.3. CAN
5.3.4. AFDX/μAFDX
5.3.5. RS485
6. EPDS presentation and status
6.1. The Electrical Power Distribution System (EPDS)
6.1.1. Aircraft electrical architecture
6.1.2. Centralized and Decentralized Electrical Power Distribution System 374
6.1.3. Elements of certification requirements and PRA (Particular Risk Analysis) applicable to the EPDS
6.2. Electrical Primary Power Distribution Center
6.2.1. Primary Power Center architecture
6.2.2. EPDC state machine
6.3. Decentralized architecture: Solid State Power Controllers (SSPCs) and Secondary Power Distribution Box (SPDB)
6.3.1. SSPCs
6.3.2. Secondary Power Distribution Box (SPDB)
6.4. EPDC configuration
6.4.1. Dataloading
6.4.2. Equipment software configuration by switch
6.4.3. Piece of equipment software configuration by pin programming
6.5. EPDS pieces of equipment BITE
6.5.1. Definition
6.5.2. Monitoring
6.5.3. Test types
6.5.4. Reporting
6.5.5. Maintenance Message
7. Power Distribution Units electrical design
7.1. Wiring installation
7.1.1. Introduction – Wiring degradation.
7.1.2. Current FAA Guidance
7.2. Lightning Indirect Effects (LIE)
7.2.1. Introduction – The lightning phenomenon
7.2.2. Lightning Direct Effects (LDE)
7.2.3. Lightning Indirect Effects
7.2.4. Electrical equipment protection
7.2.5. LIE waveforms
7.3. Bonding and Grounding
7.3.1. Electrical installation requirements
7.3.2. Electrical installation for current return, people and equipment protection
7.3.3. EPDS bonding and grounding design principles
7.4. Corrosion
7.4.1. Electrochemical corrosion mechanisms
7.4.2. Types of corrosion
7.4.3. Corrosion mitigation
8. Power Distribution Units mechanical and thermal design
8.1. Mechanical design
8.1.1. Mechanical constraints
8.1.2. Manufacturing
8.1.3. Mechanical simulations
8.2. Thermal design
8.2.1. Thermal environment
8.2.2. Thermal Management System
8.2.3. Thermal Simulations
Index
Livres de l'auteur Collectif
