power dissipation optimization process in aircraft power...
TRANSCRIPT
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Power Dissipation Optimization Process in Aircraft Secondary Power Distribution Systems
Neno Novakovic
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November 1, 2014 ◊ Future of Flight Aviation Center ◊ Paine Field Everett, Washington
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• Introduction, Aircraft Electrical Power History and Concepts
• Power Distribution Units, Configurations and Characteristics
• Problems, Challenges and Constrains
• Solution, Tools and Methods
PROPOSED AGENDA
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• During the WWI era, radio communication was introduced and 12 volt lead acid battery and air or engine driven DC generators were used.
• 28 V dc aircraft system voltage was established during WW II era (then sometimes called a 24 volt , or 27 volt or 30 volt system).
• In the early 1940s the decision was made to adopt 400 Hz, 3-phase, 115/200 volt system as future aircraft electrical power system.
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AIRCRAFT ELECTRICAL POWER SYSTEM HISTORY
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0
200
400
600
800
1000
1200
1400
1600
1960 1970 1980 1990 2000 2010 2020
PO
WE
R R
AT
ING
[K
VA
]
AIRCRAFT AC POWER GENERATION
AIRCRAFT ELECTRICAL POWER GENERATION HISTORY
DC-9
B757
B747 A340
A380
B787
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ELECTRIC POWER DISTRIBUTION CONCEPTS
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EPDS EPDS
PDU-1
PDU-2
PDU-3
PDU-N
CENTRALIZED DECENTRALIZED
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SECONDARY POWER DISTRIBUTION WITH COCKPIT CIRCUIT BREAKERS CONCEPT
AC
115 V AC BUS
28 V DC BUS
TRU
AC ELECTRICAL LOADS
DC ELECTRICAL LOADS
COCKPIT CIRCIUT BREAKER PANEL
THERMAL CIRCUIT BREAKER
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SECONDARY POWER DISTRIBUTION CONCEPT WITH INTEGRATED PDUs
AVIONICS AND
INTERFACE CONTROL
PDU PDU PDU
PDU PDU PDU
28 V DC
28 V DC
115 V AC
115 V AC
COCKPIT MULTY FUNCTIONAL DISPLAYS
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PDU HARDWARE CONFIGURATION
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• Each PDU contains up to n AC and/or DC power modules with Solid State Power Controllers (SSPCs) designed to switch power ON and OFF to aircraft electrical loads in response to commands from dedicated system controllers.
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DC POWER MODULE ARCHITECTURE
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SSPC 1
SSPC 2
SSPC 3
SSPC K
INPUTFILTER
INTERFACE
BOARDCONTROLLER
POWER FEED
DATA AND CONFIGURATIONCONTROL BUS
LOAD #1
LOAD #2
LOAD #3
LOAD #K
POWER RETURN
POWER MODULE
+28 V DC
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AC POWER MODULE ARCHITECTURE
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SSPC 1
SSPC 2
SSPC 3
SSPC L
INPUTFILTER
INTERFACE
BOARDCONTROLLER
POWER FEED
DATA AND CONFIGURATIONCONTROL BUS
LOAD #1
LOAD #2
LOAD #3
LOAD #L
POWER RETURN
POWER MODULE
115 V AC PHASE A
INPUTFILTER
INPUTFILTER
115 V AC PHASE B
115 V AC PHASE C
POWER FEED
POWER FEED
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CHALLENGES AND CONSTRAINS
• Total system equipment weight.
• Architecture driven by minimal distance between power source and electrical load.
• Bus power and load segregation.
• Load shed pattern.
• System hardware limitations.
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PHISICS OF HARDWARE AND SYSTEM LIMITATIONS
1. Limit on AC and DC input feed current.
2. Limit on power dissipation on SSPC components .
3. Limit on internal control power dissipation.
1
3
2
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POWER DISSIPATION DEFINITION
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• For each Power Module at position X, total power dissipation can be defined as a sum of all individual SSPC channel power dissipations:
were
I is a continuous load current through SSPC channel, which depends on aircraft configuration ε,
and Ron is SSPC channel ON resistance, as a function of ambient operating temperature Temp,
PD_MX = RON [W]
I=I(ε) [A]
Ron=Ron(Temp) [Ω]
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AIRCRAFT DESIGNATED FLIGHT PHASES
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• Load currents of the electrical and electronic equipment are dependant on aircraft configuration.
• For the purpose of this analysis, the aircraft configuration parameter ε, can be tied to a different aircraft designated flight phases, listed in the following order:
- Ground Loading
- Engine Start
- Taxi
- Takeoff
- Climb ε - Cruise
- Descent
- Landing
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SSPC CHANNELS CONFIGURATION
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• SSPC channel ON resistance Ron includes MOSFET ON drain-source resistance, current sensing resistance, and some other elements relevant to specific hardware configuration.
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PDU TOTAL POWER CONSUMPTION
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• PDU total power consumption can be calculated as a sum of Power Supply power consumption, and all n Power Modules power dissipations:
were
Power Supply power consumption includes:
- Processor power
- Power Supply efficiency, and
- Control Switching power losses.
PDU_TPC = PS_Power_Concumption + [W]
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POWER ANALYSIS NUMERIC ALGORITHM
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DC AC
MODULE 1
MODULE 2
CONFIG
M1 1,
M2 1,
Mn 1,
M1 2,
M2 2,
Mn 2,
:=
MODULE n
SSPC1 SSPC2 SSPCK
MODULE 1
MODULE 2
TDCM ε( )
TDCM_1ε 1,
TDCM_2ε 1,
TDCM_nε 1,
TDCM_1ε 2,
TDCM_2ε 2,
TDCM_nε 2,
TDCM_1ε k,
TDCM_2ε k,
TDCM_nε k,
:=
MODULE n
n
K
ε
PDU CONFIGURATION LOAD DATABASE
THREE DIMENSIONAL CURRENT MATRIX
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POWER ANALYSIS BLOCK DIAGRAM
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PDU POWER ANALYSIS RESULTS
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40− 30− 20− 10− 0 10 20 30 40 50 60 70 8050
70
90
110
130
150
Ambeint Temperature [C]
Tota
l Pow
er C
onsu
mpt
ion
[W]
PDU_TPC Temp ε, ( )
Temp
40− 30− 20− 10− 0 10 20 30 40 50 60 70 800
2
4
6
8
10
12
14
16
18
20
22
Ambeint Temperature [C]
Pow
er D
issi
patio
n [W
] PD_M1 Temp ε, ( )
PD_M2 Temp ε, ( )
PD_M3 Temp ε, ( )
PD_M5 Temp ε, ( )
Dissipation_Limit
Temp
Phase_Of_Flight ε( ) "CLIMB"= Phase_Of_Flight ε( ) "CLIMB"=
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POWER DISTRIBUTION OPTIMIZATION PROCESS
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REFERENCES
• “Overcoming Power Challenges With Power Distribution Units”, Dave Proli, Power Electronics Technology, May 31 2012, www.powerelectronics.com.
• “MOSFET Power Losses Calculation Using the Data-Sheet Parameters” by Dr. Dusan Graovac, Marco Pϋrschel, Andreas Kiep, Application Note, V 1.1 July 2006, INFINEON.
• “Electrical Power Distribution Architecture for All Electric Aircraft” D. Izquierdo, R. Azcona, F. J López del Cerro, C. Fernández, J. Insenser, 27th International Congress of the Aeronautical Science ICAS 2010.
• 787 Program, Electrical System and Batteries, Sinnet-TOS-Deck.pdf
• “Power Dissipation Optimization Process in Aircraft Secondary Power Distribution Systems”, N. Novakovic, M. Manojlovic, SAE Aerospace 2013-01-2275.
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AIRCRAFT ELECTRIC POWER DISTRIBUTION
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