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A320 ATA 24 Electrical Power

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Diego alejandro Vega Rusinque

on 30 October 2015

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Transcript of A320 ATA 24 Electrical Power

A320 ATA 24 Electrical Power
General
Description and operation
Generation

Two Integrated Drive Generators (IDG) normally supply the aircraft
electrical power in flight.
The APU drives a third, auxiliary, generator (APU GEN) which can replace
either main generator (GEN 1 or GEN 2).
The generators supply with alternating current.
Two Transformer Rectifiers (TR) supply with direct current. In failure,
a constant-speed hydraulic motor drives an emergency generator to
supply the systems required for aircraft control.

Main GEN and APU GEN
Each main generator is driven by an
accessory gearbox and an integrated hydromechanical speed
regulator which transforms the engine variable speed into
constant speed for the generator.
The APU directly drives the APU GEN at constant speed.
Main Generator, APU GEN and Generator Control Unit (GCU)
Each generator is controlled, via a GCU, by a GEN pushbutton
switch located on the ELEC panel on the overhead panel.
The leading particulars of the generator are:
- nominal power: 90 KVA
- voltage: 115 V/200 V, three-phase, 400 Hz.
GCU functions GCU
-regulate the generator voltage by the field current
-protect the network and the generator by control of the
associated GLC and the generator field current
-provide BITE information to the Ground Power Control Unit
(GPCU)
-control the warnings associated with the corresponding
channel.
Electrical Generation Interface Unit (EGIU)
The main function of the EGIU is to process the parameters from
the GCU and associated generator. The EGIU then transmits the
information to the cockpit (ECAM) via the System Data Acquisition
Concentrators (SDACs).
Two EGIUs are installed on the aircraft.
One EGIU is associated with the GCU1 and the GPCU.
This EGIU receives parameters in analog and discrete form from:
- GEN1 on channel 1 and,
- external power on channel 2.
CSM/G drive
In emergency conditions, a hydraulic motor speed-controlled by a
servo-valve speed regulator drives the CSM/G. The regulator uses
the oil flow from the Blue Hydraulic system to maintain the CSM/G
at a constant speed.
In normal conditions, an electric pump supplies the Blue
hydraulic system. In emergency conditions, the Ram Air Turbine
(RAT) supplies the Blue system.
The leading particulars of the CSM/G are:
- Nominal Power: 5 KVA at POR
- Voltage: 115/200 VAC, three-phase, 400 Hz.
The main functions of the control unit are:
- to control the servo-valve excitation for speed regulation,
- to regulate the generator voltage by the field current,
- to protect the network and the generator by control of the
associated GLC and the generator field current.
Static inverter
The static inverter, with a 1000 VA nominal power, transforms the
direct current from the battery 1 into a single phase, 115 V 400
Hz, alternating current.
The static inverter is automatically activated if AC BUS 1 and AC
BUS 2 are lost and the CSM/G is unavailable.
For maintenance purposes, the static inverter delivers FAULT
indication to the Centralized Fault Display System (CFDS) through
the two Battery Charge Limiters (BCL).
TR
Each TR transforms the three-phase alternating current into
direct current (28VDC).
TR1 and TR2
Upon energization, the two normal TRs operate and supply the
DC network via a contactor controlled by the internal TR
logic.
In case of failure, the TR sends a FAULT signal to the CFDS
for maintenance purposes.
Batteries
Each of the two batteries has a nominal 23 AH capacity and a 24
VDC voltage. The main functions of the batteries are:
- to start the APU in flight and on the ground,
- to supply the essential network in some configurations.
AC External Power Control Supply
An external power receptacle located in front of the nose landing
gear well enables power supply of the aircraft network. This is
performed by means of the three-phase, 400 Hz, 115/200 V ground power
unit.
Centralized Fault Display System (CFDS)
Line maintenance of the electronic systems is based on the use of the
CFDS.
The purpose of the CFDS is to give to maintenance technicians a central
maintenance aid. The CFDS enables intervention at system or subsystem
level from the Multipurpose Control and Display Units (MCDUs) located in
the cockpit.
From the MCDUs it is possible:
- to read the maintenance information,
- to initiate various tests.
Diego Alejandro Vega Rusinque
TLA 5BM
Sistemas 3
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