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EEA 2004 - EYAE - Ref. X24PR0401420 - Issue 1
18th March 2004
EEA 2004From the More Electric Aircraft to the All Electric Aircraft:
State of the Art & Prospective
ELECTRICAL DEPARTMENT
Presented by
Olivier LANGLOISEtienne FOCHXavier ROBOAMHubert PIQUET
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Plan
Introduction
1. Hydraulically Powered Aircraft
2. More Electric Aircraft
3. Towards All Electric Aircraft
4. Example of DC Network
Conclusion
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Introduction
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Current project POWERNET
• Powernet is a RTC about electrical power
• LEEI (Toulouse)
• 3 topics are studied:Power managementMethods of network conceptionHigh voltage DC network
Electricity involve a lot of changes
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Airbus has the most modern aircraft Family
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1. Hydraulically Powered Aircraft
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Users: Engine off-takes needs for aircraft users
Mechanical power- Engine Fuel Pump- Engine Oil Pump
- Engine start200kW (peak)
100kW (local)
Hydraulic power- Flight Controls- Landing gear- Braking- Reverse- Doors
240kW-206bars
Electrical power- Avionics- Commercial- Pumps- De-icing- Lights- …...
115VAC-230kVA
Pneumatic power- Air conditioning- Pressurisation- Ice Protection
- Engine start
From some barsup to 20bars-1200kW
Example: Power used on A330
Power rationalisation should be feasible
4 Power source types3 Power networks on aircraft
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General Overview of an aircraft electrical network
AC/DC Conversion
Batteries
Main Generation AC
DC distribution : 28VDC
AC distribution : 115VAC
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A330: General Architecture (3H)
IDG 1PumpPump
AccuAccu
RATRAT
AccuAccu
CSM/GCSM/G
TR 1TR 1
AC BUS 1 AC BUS 2
AC ESS BUS
ESS TRESS TR
STAT INV
DC ESS BUS
DC BUS 1 DC BUS 2
IDG 2Pump
AccuAccuEXT
Engine 1 Engine 2
TR 2TR 2 APU TRAPU TR
APU START
PumpPump PumpPump
APUGENAPUGENBlue Green Yellow
BAT 1 BAT 2
H2 H3H1
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2. More Electric Aircraft
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A380 Novelties
Generator: VFG (150 kVA) replace IDG (≤ 115 kVA)
Variable frequency (f = 360…800 Hz) replace Fixed frequency (400 Hz)
Electrical actuators (EHA…) replace Some hydraulic actuators
Electrical RAT replace Hydraulic RAT
AC-DC Converter: BCRU (300 A) replace TRU (200 A)
Electronic circuit breakers (up to 15 A) replace Thermal circuit breakers
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A330 “A380”: General Architecture (2H+2E)
VFG 1 PumpPump
AccuAccu
BCRU 1BCRU 1
AC BUS 1 AC BUS 2
AC ESS BUS
BCRU ESSBCRU ESS
STAT INV
DC ESS BUS
DC BUS 1 DC BUS 2
VFG 2Pump
AccuAccuEXT
Engine 1 Engine 2
BCRU 2BCRU 2 APU TRAPU TR
APU START
APUGENAPUGEN
Green Yellow
RATRAT
BAT 1 BAT 2
BAT ESS
E1 E2
H1 H2
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AC Main Generation
IDG
CSD45
00…
9000
tr/m
in
2400
0 tr
/min
PMG Exciter Main
NS
NS
1200
0…24
000
tr/m
in
VFGPMG Exciter Main
4500
…90
00 tr
/min
NS
NS
On A380, IDG has been replaced bya Variable Frequency Generator (VFG) which is conventional wound rotor synchronous alternator
The frequency range is 360-760Hz
Variable Frequency Choice
Mechanically simpler AC source
Butextra-constraints for users
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AC Main Generation
On A380, IDG has been replaced bya Variable Frequency Generator (VFG) which is conventional wound rotor synchronous alternator
The frequency range is 360-760Hz
Variable Frequency Choice
Mechanically simpler AC source
Butextra-constraints for users
IDG A320 90 kVA
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Users : Exemple of electrical flight control
ServovalveAccumulator
Modeselectordevice
Ram
Manifold
Electro-hydraulicservocontrol
Modeselectordevice
Ram
Manifold
Electronics
Motor
PumpAccumulator
Electro Hydrostatic Actuator
EHA are used on A380replacing
one of the 3
hydraulic networksby EHA
supplied by the
electricalnetwork
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Electrically Powered Actuators
EHA supplied by AC power:
EHA Motor
Melec.
EHA Pump
Phyd.
EHA Rectifier EHA Inverter
Bleed Resistor
Hydraulic Jack
Flight Control
115/
200
V A
C
Filter Capacitor
EHA
270 V DC
⇒ Higher local weight but lower global weight
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Electrically Powered Actuators (cont’d)
EHA Bond Graph
• Multi-domain representation• Good visualization of power transfers
Aerodynamic effortDC power supply
Ubus
Ibus
E : « effort » variable
F : « flow » variable
Se : Ubus TF1/α U
I1
E
IGYΦ Cem
Ω
I : L
R : R
1
I : J
R : f
Cch
ΩTFD Pp1-Pp2
Qpi
0Qp
R : 1/ αη
Qfp
Pp1-Pp2 1
Pv1
Qp
0Qv
Qfv
Pv1 TF
R : 1/Cvh1Qfv
Qfv
Pv1-Pv2
Pv1
Pv2
1
2ch
h SBV
2/R1 : C
⋅=
0Qv
Pv2Pv2
Qp
1
2ch
h SBV
2/R1 : C
⋅=
2p
: S bloce
2p
: S bloce
Pp1
Pp2
Qp
Qp
1/S
TF1/S
Fv1
Fv2
Vv
Vv
Fv’
Vv
0
C : 1/Rm
FT=Fv’
VT
1
Se : Fservo h
FG
VG=VT
1
FM
TFMG
ΩG
1/BlSe : MG
Converter Electrical motor Hydraulic pump Pipes Hydraulic jack Control surface
2G
BlJ
M : I =
Fv
Vv
1
Se : Fsec v
Transmission
R : 1/Cvm
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AC – DC Converters
TR
ATRU
28 V
DC
115/
200
V A
C
BCRU
28 V
DC
115/
200
V A
C
270
V D
C
Buck
• BCRU is used to provide 28 V DC and to charge battery• Batteries are permanently connected to the DC network
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3. Towards All Electric Aircraft
Thursday 18th March 2004EEA 2004 - EYAE - Ref. X24PR0401420 - Issue 1 Page 20
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Next step : Main Generation for more needs
Power available versus Aircraft Weight
0100200300400500600700800900
1000
0 200 400 600 800
Max Aircraft Weight MTOW (tons)
Pow
er a
vaila
ble
(kVA
)
Power rationalisation is rather oriented towards more electrical systemsCommercial need is also a factor of power demand increase
A380
7E7
Current aircraft
Next aircraft generation showsa strong break in power demand versus current certified one’s
Thus more electric aircraft needs induced High probability of voltage change either 230 V AC or HVDC⇒ Probability of standard change
A new standard change will impact airlines, industry and technology
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“Bleed” Removal
APU
Engine
Bleed Air
Elec
Air
Engine start
Elec
Air systems
Gen
Gen
Bleed
Electrical loads
Current configuration
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“Bleed” Removal (cont’d)
APU
Engine
Bleed Air
Elec
Air
Elec
Air systems
Gen
Gen
Bleed
Electrical loads
Engine start
Without bleed air configuration
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POA: An Innovative Integrated Generation
Goodrich – 150 kWFan-Shaft GeneratorSwitched reluctance
Power Optimised Aircraft
Energy optimisationVoltage: 350 V DC
HP Starter/GeneratorPermanent magnet
Thales AES150 kW
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Next steps – More versatile users
Electronics converter are largely used even for huge loads
10% motors are fitted with a power electronics on A3456
70% for A380
Other technical loads (eg: light, heating, …) and commercial loads used power electronics as well
Fans/Pumps/Actuators number versus power
0
10
20
30
40
50
2500
5000
7500
1000
012
500
1500
017
500
2000
022
500
2500
027
500
3000
0
Power (VA)
Mot
or(>
1kVA
) nu
mbe
r
A380A3456
The number of power electronic users increases drastically on AirbusPower system specialists take more and more benefits of electronics technologies
for their advanced system architecturesVery huge loads are expected for other programs around 100 kWMore than 100 motors (>1 kVA) for technical loads on A380
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Other Electrical Systems
Great loads use power electronics
• Electrical actuators (for flight controls):EHA, EBHAEMA
• Fan, compressor, pump…
• Example: Electrical Flaps, more electrical architecture
Motor
Motor
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4. Example of DC Network
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Emergency Generation
RATRAT
AIR FLOW
AIR FLOW
An emergency source (called RAT) powered by the air flow
The RAT drives a hydraulic pump which supplies a small electrical generator (less than 10kVA)
On A380, the RAT drives an electrical alternator
In the future, other sources are possible:fuel cells, super-capacitors…
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Emergency Network
RAT Rectifier Inverter
MSMS
Filter NetworkRAT
Batteries,Super-capacitors…
Storage converter
115/200 V400 Hz
Storage element
Accumulationof energy when low needs on network
Restitutionof energy when high needs on network
Use of 2 different sources:• RAT as an energy source• Storage element as a power source
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Energy Recovery
• EHA normally supplied by AC network• Storage element on the DC bus
EHA Rectifier EHA Inverter EHA Motor
Mélec.
EHAPump
Phyd.
EHA
Batteries,Super-capacitors…
Storage converter
Storage elements
Mai
n ne
twor
k11
5/20
0 V
AC
Storage system
Emer
genc
y ne
twor
k27
0 V
DC
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Main Network in DC
• Most of systems own power electronics
• Stability trouble
• New network architectures
Rectifier EHA Inverter
MS
EHA MotorGenerator
270 V DC
Mélec.
EHA Pump
Phyd.
EHA without rectifierPower Generating System
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Conclusion
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Open discussions
•• The more electric aircraft is a general trendThe more electric aircraft is a general trend
•• There is more and more power electronicsThere is more and more power electronics
• Should aircraft manufacturer switch to HVDC?
• What are the best auxiliary sources to replace APU, RAT…?
• Which sizing methods could we use to make the right choice?
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