Post on 27-Feb-2021
OutlineOutline
The InstallationThe InstallationProblemProblem
ArchitectureArchitectureSelectionSelection
MethodologyMethodology
h fh fThe ProofThe Proofof Conceptof Concept
ConcludingConcluding
2Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
ggRemarksRemarks
OutlineOutline
The InstallationThe InstallationProblemProblem
ArchitectureArchitectureSelectionSelection
MethodologyMethodology
h fh fThe ProofThe Proofof Conceptof Concept
ConcludingConcluding
3Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
ggRemarksRemarks
MotivationMotivationOld ComponentsOld Components More Electric ComponentsMore Electric ComponentsCurrent efforts emphasize developing
more electric technologiesmore electric technologiesComponents optimized individually by vendors
Majority of issues arise during system j y g yintegration
New technologies often physically swapped inOrganization of Aircraft Equipment Organization of Aircraft Equipment Systems (AES) affects overall subsystem efficiency
Interactions and constraints between components must be captured
Information should be leveraged to develop strategic AES installationNo environment exists to evaluate
4Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
these types of tradeoffs during conceptual design
The Focused Problem: InstallationThe Focused Problem: InstallationFull potential of new components may not be
Minimizing Weight
More Electric Component
achieved in future aircraft
Current configurations may benefit from holistic
re integration/e al ation
Minimizing Exergy Loss
re-integration/evaluation
Potential gains:Minimizing system weight - Adding/removing cabling or Managing Energy Flow
Current Component
hydraulic lines
Minimizing exergy loss - Maximum amount of available
work
Current AircraftEnergy Optimized Aircraft
Managing energy flows - Efficiency fluctuation due to
thermal effects
5Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
Investigation of new installation architectures is necessary
What is an Installation Architecture?What is an Installation Architecture?Architecture 1 Architecture 2
A Same components
Different placement
A
C
B
A
C
B
D
D
6Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
2008-2009 EOASys Effort
Previous Grand Challenge teams have studied aspects of the functional
2008 2009 EOASys Effort
architecture design process
I
Power Generation Power Generation –– TurboTurbo--FanFan
Provide Non-Prop
Power
Produce Thrust
Mech. PowerMech. Power
Weight
Fuel
Requirement
Starting Power
Requirement
ThrustThrust
Pneu. PowerPneu. Power
Jet fuelJet fuelTurbo-Fan
AGB
Pneu. Starter
EBAS
Power Generation Power Generation –– TurboTurbo--CellCell
Provide Non-Prop
Power
Produce Thrust
HydrogenHydrogen
Weight
Fuel
Requirement
Starting Power
Requirement
ThrustThrust
Pneu. PowerPneu. Power
Jet fuelJet fuelTurbo-Fan
FuelCell
Elec. Starter
II
Conditioning Air High Pressure Bleed Concept yes Low Pressure
Bleed Concept ND Bleed Less Concept 1
Protect From Icing Pneumatic Concept ND Electro-Thermal Concept ND Electro-Impulse Concept
Control Flight Electro-Mech. Actuator Concept ND Electro-Hydrostatic
Actuator Concept ND Hydraulic Actuator Concept
Fly Wing Design Concept 1 ND Wing Design Concept 2 ND Wing Design Concept 3
Protect Passengers and Payload Fuselage Concept 1 ND Fuselage Concept 2 ND Fuselage Concept 3
Proppel PW6000 ND T1000 ND CFM56
To Hydraulic Engine Driven Pump Concept ND Electric Motor
Pump Concept ND Engine/Electric Motor Hybrid
To Electric IDG ND VFG ND
To Pneumatic Engine Bleep IP ND Engine Bleed IP/HP ND Electric Compressors
Electric Power x Vac fixed frequency ND xVdc ND xVacVF
Pneumatic Power 1.2 psi ND 2.4 psi ND no distribution at AC level
Hydraulic Power 3H ND 2H1He ND 3He
Tran
sfor
m P
ower
Dis
trib
ute
Pow
er
PDe PDh PDp PTe PTh PTp PG
AC
FC
PR
PDe
PDh
PDp
PTe
III
IV0
I
Power Generation Power Generation –– TurboTurbo--FanFan
Provide Non-Prop
Power
Produce Thrust
Mech. PowerMech. Power
Weight
Fuel
Requirement
Starting Power
Requirement
ThrustThrust
Pneu. PowerPneu. Power
Jet fuelJet fuelTurbo-Fan
AGB
Pneu. Starter
EBAS
Power Generation Power Generation –– TurboTurbo--CellCell
Provide Non-Prop
Power
Produce Thrust
HydrogenHydrogen
Weight
Fuel
Requirement
Starting Power
Requirement
ThrustThrust
Pneu. PowerPneu. Power
Jet fuelJet fuelTurbo-Fan
FuelCell
Elec. Starter
II
Conditioning Air High Pressure Bleed Concept yes Low Pressure
Bleed Concept ND Bleed Less Concept 1
Protect From Icing Pneumatic Concept ND Electro-Thermal Concept ND Electro-Impulse Concept
Control Flight Electro-Mech. Actuator Concept ND Electro-Hydrostatic
Actuator Concept ND Hydraulic Actuator Concept
Fly Wing Design Concept 1 ND Wing Design Concept 2 ND Wing Design Concept 3
Protect Passengers and Payload Fuselage Concept 1 ND Fuselage Concept 2 ND Fuselage Concept 3
Proppel PW6000 ND T1000 ND CFM56
To Hydraulic Engine Driven Pump Concept ND Electric Motor
Pump Concept ND Engine/Electric Motor Hybrid
To Electric IDG ND VFG ND
To Pneumatic Engine Bleep IP ND Engine Bleed IP/HP ND Electric Compressors
Electric Power x Vac fixed frequency ND xVdc ND xVacVF
Pneumatic Power 1.2 psi ND 2.4 psi ND no distribution at AC level
Hydraulic Power 3H ND 2H1He ND 3He
Tran
sfor
m P
ower
Dis
trib
ute
Pow
er
PDe PDh PDp PTe PTh PTp PG
AC
FC
PR
PDe
PDh
PDp
PTe
III
IV0
Forcereq
Forcereq
Electric Power needed
Concept 1: Std Hydraulic
HAControl Surface
s
Landing Gear Actuations
…Weight
Engine Reverse
Drag
Volume needed
Hydraulic Power needed
Concept 2: More Electric
Landing Gear Actuati ons
Control Surface
…
Engine Reverse
Control
Hydrauliclines
Weight
DragVolume needed
EHA
Cooling needed
Forcereq
Forcereq
Electric Power needed
Concept 1: Std Hydraulic
HAControl Surface
s
Landing Gear Actuations
…Weight
Engine Reverse
Drag
Volume needed
Hydraulic Power needed
Concept 2: More Electric
Landing Gear Actuati ons
Control Surface
…
Engine Reverse
Control
Hydrauliclines
Weight
DragVolume needed
EHA
Cooling needed
Concept 1: Std Pneumatic
Piccolo
…
Heatreq Weight
Volume needed
Pneumatic Power needed
Concept 2: More Electr ic 1
Protect From Icing
Val ves
Weight
Volume needed
Heatreq
Ic ing detec ti on sys tem
Electric Mats
…Val ves
Icing detection sys tem
Concept 2: More Electr ic 2
Weight
Volume needed
Powerreq Impulse System
…Val ves
Icing detection sys tem
Electric Power needed
Electric Power needed
Frequencyreq
Concept 1: Std Pneumatic
Piccolo
……
Heatreq Weight
Volume needed
Pneumatic Power needed
Concept 2: More Electr ic 1
Protect From Icing
Val ves
Weight
Volume needed
Heatreq
Ic ing detec ti on sys tem
Electric Mats
……Val ves
Icing detection sys tem
Concept 2: More Electr ic 2
Weight
Volume needed
Powerreq Impulse System
……Val ves
Icing detection sys tem
Electric Power needed
Electric Power needed
Frequencyreq
Concept 1Liftreq Icing Protection needed
Drag generated
control needed
Concept 2
Fly
Missionreq
Wing
Wing
Liftreq
Missionreq
Icing Protection needed
Drag generated
control needed
Concept 1Liftreq Icing Protection needed
Drag generated
control needed
Concept 2
Fly
Missionreq
Wing
Wing
Liftreq
Missionreq
Icing Protection needed
Drag generated
control needed
Concept 1: Std Pneumatic
Air Cycle
Machine
Mixing Chamber
Ozone Converter
Distribution System
Pressure Valve
…
mreq
Preq
.
Treq
Weight
RAM air scoop
Drag
Volume Needed
Pneumatic Power Needed
Concept 2: More Electric
Air Cycle
Machine
Mixing Chambe
r
Ozone ConverterDistribution
System
Pressure Valve
…
RAM air Com presso
r
Conditioning of Air
mreq
Preq
.
Treq
Electric Power Needed
Volume Needed
Weight
Drag
Concept 1: Std Pneumatic
Air Cycle
Machine
Mixing Chamber
Ozone Converter
Distribution System
Pressure Valve
…
mreq
Preq
.
Treq
Weight
RAM air scoop
Drag
Volume Needed
Pneumatic Power Needed
Concept 2: More Electric
Air Cycle
Machine
Mixing Chambe
r
Ozone ConverterDistribution
System
Pressure Valve
…
RAM air Com presso
r
Conditioning of Air
mreq
Preq
.
Treq
Electric Power Needed
Volume Needed
Weight
Drag
VVI
Forcereq
Forcereq
Electric Power needed
Concept 1: Std Hydraulic
HAControl Surface
s
Landing Gear Actuations
…Weight
Engine Reverse
Drag
Volume needed
Hydraulic Power needed
Concept 2: More Electric
Landing Gear Actuati ons
Control Surface
…
Engine Reverse
Control
Hydrauliclines
Weight
DragVolume needed
EHA
Cooling needed
Forcereq
Forcereq
Electric Power needed
Concept 1: Std Hydraulic
HAControl Surface
s
Landing Gear Actuations
…Weight
Engine Reverse
Drag
Volume needed
Hydraulic Power needed
Concept 2: More Electric
Landing Gear Actuati ons
Control Surface
…
Engine Reverse
Control
Hydrauliclines
Weight
DragVolume needed
EHA
Cooling needed
Concept 1: Std Pneumatic
Piccolo
…
Heatreq Weight
Volume needed
Pneumatic Power needed
Concept 2: More Electr ic 1
Protect From Icing
Val ves
Weight
Volume needed
Heatreq
Ic ing detec ti on sys tem
Electric Mats
…Val ves
Icing detection sys tem
Concept 2: More Electr ic 2
Weight
Volume needed
Powerreq Impulse System
…Val ves
Icing detection sys tem
Electric Power needed
Electric Power needed
Frequencyreq
Concept 1: Std Pneumatic
Piccolo
……
Heatreq Weight
Volume needed
Pneumatic Power needed
Concept 2: More Electr ic 1
Protect From Icing
Val ves
Weight
Volume needed
Heatreq
Ic ing detec ti on sys tem
Electric Mats
……Val ves
Icing detection sys tem
Concept 2: More Electr ic 2
Weight
Volume needed
Powerreq Impulse System
……Val ves
Icing detection sys tem
Electric Power needed
Electric Power needed
Frequencyreq
Concept 1Liftreq Icing Protection needed
Drag generated
control needed
Concept 2
Fly
Missionreq
Wing
Wing
Liftreq
Missionreq
Icing Protection needed
Drag generated
control needed
Concept 1Liftreq Icing Protection needed
Drag generated
control needed
Concept 2
Fly
Missionreq
Wing
Wing
Liftreq
Missionreq
Icing Protection needed
Drag generated
control needed
Concept 1: Std Pneumatic
Air Cycle
Machine
Mixing Chamber
Ozone Converter
Distribution System
Pressure Valve
…
mreq
Preq
.
Treq
Weight
RAM air scoop
Drag
Volume Needed
Pneumatic Power Needed
Concept 2: More Electric
Air Cycle
Machine
Mixing Chambe
r
Ozone ConverterDistribution
System
Pressure Valve
…
RAM air Com presso
r
Conditioning of Air
mreq
Preq
.
Treq
Electric Power Needed
Volume Needed
Weight
Drag
Concept 1: Std Pneumatic
Air Cycle
Machine
Mixing Chamber
Ozone Converter
Distribution System
Pressure Valve
…
mreq
Preq
.
Treq
Weight
RAM air scoop
Drag
Volume Needed
Pneumatic Power Needed
Concept 2: More Electric
Air Cycle
Machine
Mixing Chambe
r
Ozone ConverterDistribution
System
Pressure Valve
…
RAM air Com presso
r
Conditioning of Air
mreq
Preq
.
Treq
Electric Power Needed
Volume Needed
Weight
Drag
VVI
Lack of a modeling environment has caused a discontinuity in the design
7Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
process which is needed to select an optimal architecture
Program ObjectivesProgram Objectives
1. Formulate a generic methodology that allows designers to optimally install Aircraft Equipment Systems o u ate a ge e c et odo ogy t at a o s des g e s to opt a y sta c a t qu p e t Syste sinto an aircraft
Methodology facilitates installation of any subsystem or component2. Demonstrate methodology through a Proof Of Concept (POC)
POC makes enabling assumptions to facilitate project scopePOC makes enabling assumptions to facilitate project scopePOC shows how the methodology can be used to improve component placement and realize aircraft level gains
MethodologMethodolog Proof of ConceptProof of Concept Program ResultsProgram Results
Enabling Architecture
MethodologyMethodology Proof of ConceptProof of Concept Program ResultsProgram Results
Assumptions Selection
8Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
Modeling & Simulation EnvironmentModeling & Simulation Environment
M&S environment was created in Pacelab Aircraft
Preliminary Design (Pacelab APD)
Displays a 3D representation of the model
Unique software platform focused on Knowledge
Based Engineering
Allows mathematical definition of an aircraft and
its internal structure
Acquisition of Pacelab APD was a key
breakthrough for our design environment
9Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
OutlineOutline
The InstallationThe InstallationProblemProblem
ArchitectureArchitectureSelectionSelection
MethodologyMethodology
h fh fThe ProofThe Proofof Conceptof Concept
ConcludingConcluding
10Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
ggRemarksRemarks
The Architecture Selection Methodologygy
St StepStep 6Step 1
Component Library Component Library CreationCreation
Investigate Investigate Competing Competing
ArchitecturesArchitectures
Component Library Component Library CreationCreation
Investigate Investigate Competing Competing
ArchitecturesArchitectures
Step 1
Step 6 Investigate Investigate
Competing Competing ArchitecturesArchitectures
Step 6
Component Library Component Library CreationCreation
Step 1
Sizing/Synthesis & Sizing/Synthesis & Ai f Z iAi f Z i
Measures of Merit Measures of Merit Id ifi iId ifi i
Sizing/Synthesis & Sizing/Synthesis & Ai f Z iAi f Z i
Measures of Merit Measures of Merit Id ifi iId ifi i
Step 2
Step 5
Sizing/Synthesis & Sizing/Synthesis & Ai f Z iAi f Z i
Step 2
Sizing/Synthesis & Sizing/Synthesis & Ai f Z iAi f Z i
Step 2
Measures of Merit Measures of Merit Id ifi iId ifi i
Step 5Measures of Merit Measures of Merit
Id ifi iId ifi i
Step 5
Aircraft ZoningAircraft Zoning IdentificationIdentificationAircraft ZoningAircraft Zoning IdentificationIdentification
Step Step
Aircraft ZoningAircraft ZoningAircraft ZoningAircraft Zoning
Step Step 3 Step Step 4
IdentificationIdentificationIdentificationIdentification
Component Component Placement Placement
Requirements Requirements FlowFlow--downdown
Initial Architecture Initial Architecture GenerationGeneration
Initial Architecture Initial Architecture GenerationGeneration
Component Component Placement Placement
Requirements Requirements FlowFlow--downdown
p3
p4Component Component
Placement Placement Requirements Requirements
FlowFlow--downdown
p3 Component Component
Placement Placement Requirements Requirements
FlowFlow--downdown
p
Initial Architecture Initial Architecture GenerationGeneration
p4
Initial Architecture Initial Architecture GenerationGeneration
p
11Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
Step 1 – Component Library Creationp p yMethodology Proof-of-Concept
Method of library creation leveraged from previous Grand Challenge Teams
1.1 Select a primary function
Primary FunctionGenerate light
Component List
Only one primary function was demonstrated to limit the scope
Deliver electrical power to loads in the avionics bay
Function further limits the scope by Other
Electric Components
IDG
1.1 Select a primary function 1.2 Identify induced functions1.3 Create matrix of
alternatives of componentsInduced Functions
p yreducing the number of components modeledThe component list was created from the Maintenance Facility Planning (MFP) d t d i f ti f
AC Essential Bus
AC Bus 1
1.4 Define basic connections between components
1.5 Verify specific functions
Induced FunctionsProvide electricity or
ignite light source
Component List
(MFP) document and information from Airbus component suppliersSchematics in the MFP were used to define basic connections
are met
Output of Step 1Output of Step 1
A fixed list of components and basic
AvionicsLoads
12Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
A fixed list of components and basic connections to be installed
Step 2 – Sizing/Synthesis & Aircraft Zoningp g y g
l f
Methodology Proof-of-Concept2.1 Select an aircraft
geometry
2.2 Acquire sizing and
A320 chosen as the aircraft geometry for POCFlight deck, passenger cabin, & cargo holds modeled in simulation environmentFeasible aircraft areas divided into five zonesq g
synthesis information
2.3 Zone the aircraft
Assists with capturing
Feasible aircraft areas divided into five zonesZones based on possible locations for components in libraryIncludes knowledge gained from Delta 737 overhaul
– Assists with capturing component placement constraints
2 4 S if ibl
Feasible wiring route pathways generated for potential component connections
2.4 Specify possible connection routes
Output of Step 2Output of Step 2
13Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
A fully defined and zoned aircraft geometry
Step 3 – Placement Requirements Flow-down
3 1 Fi d li bl t l l
p qMethodology Proof-of-Concept
3.1 Find applicable system level constraints– FAA Federal Aviation Regulations (FAR)
– Stability Limits
V l Li it
OperatingOperatingTemperatureTemperature
Center of Center of GravityGravity
Required Required PowerPower
– Volume Limits
– Ease of maintenance
3.2 Define applicable component level requirements
l l– Temperature ranges, Electrical power
and ratings, EMI control, System
grounding, etc.2
3.3 Formulate zonal placement requirements
VolumeVolume Wire RoutesWire RoutesZonesZones
Firerequirements
Output of Step 3Output of Step 3
Constraints and requirements on
Fire Zone
General General
14Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
component placement Cabin/Cargo Compartments
Wire Wire PathsPaths
Step 4 – Initial Architecture GenerationStep 4 Initial Architecture GenerationMethodology Proof-of-Concept
4.1 Select location of components within feasible zones
U hi t i l d t h
pInitial configuration used for comparison to all other architectures
Aircraft Documents
– Use historical data when
available
4.2 Verify all requirements are
Initial placements and connections determined from
Excel Database
Documentsy qmet– Change component location
when needed
Airbus documentation
Initial architecture input into
Initial Configuration
Output of Step 4Output of Step 4
Baseline aircraft with componentsplaced to meet requirements
into Pacelab APD using Excel file
15Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
placed to meet requirements
Step 5 – Measures of Merit Identificationp
Related5 1 Id tif l t t l l
Methodology Proof-of-ConceptPOC
Evaluator
Related System
Level Metric
Method of Calculation
B CC
5.1 Identify relevant system level
metrics
– Metrics should be related to costs
and benefits
$/RPMPayload CapacityWire Weight
B
A
B
A5.2 Relate system level metrics to
applicable installation metrics
– Metrics have to be quantifiableq
5.3 Benchmark the initial
architecture
Fuel Weight Fuel Cost
B C
Power Extraction from enginesOutput of Step 5Output of Step 5
Metrics for comparison of different architectures
16Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
StabilityC.G.Locations of Components
A
different architectures
Step 6 – Investigating Competing ArchitecturesStep 6 Investigating Competing Architectures
Methodology Proof-of-Concept6.1 Choose method to explore
design space
Many methods to identify competing architectures
Optimization methodsDesign Space Exploration
Run 1: Component 1: X1, Y1, Z1Component 2: X2, Y2, Z2Component 3: X3, Y3, Z3...
Run 2: Component 1: X1, Y1, Z1Component 2: X2, Y2, Z2Component 3: X3 Y3 Z3
Pre-processing:Pre-processing:
Run 1: Component 1: X1, Y1, Z1Component 2: X2, Y2, Z2Component 3: X3, Y3, Z3...
Run 2: Component 1: X1, Y1, Z1Component 2: X2, Y2, Z2Component 3: X3 Y3 Z3
Pre-processing:Pre-processing:Pre-processing:
6.2 Implement exploration method
– Requires development of modeling
and simulation environment
Design Space Exploration methods
Selected a Monte Carlo simulation combined with data post-processing
Component 3: X3, Y3, Z3...
…
Component 3: X3, Y3, Z3...
…
Processing:Processing:Processing:Processing:Processing:
6.3 Perform architecture trades
– Based on weighting preferences on
meas es of me it
post processingInvestigation consists of three phases:
Pre-processing: Generating architectures
Post-processing:Post-processing:Run 1: Results 1
Results 2
Post-processing:Post-processing:Run 1: Results 1
Results 2
Post-processing:
measures of merit
Output of Step 6Output of Step 6
d h b d
architecturesProcessing: Running the modeling and simulation environment Post-Processing: Analysis of th d f it
Results 2...
Run 2: Results 1Results 2...
…
Results 2...
Run 2: Results 1Results 2...
…
17Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
An optimized architecture based on customer preferences
the saved measures of merits
Pacelab APD Front-EndPacelab APD Front End
18Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
Pacelab APD Avionics Bay Pacelab APD Avionics Bay
19Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
Pacelab APD ResultsPacelab APD Results
20Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
Pacelab APD ResultsPacelab APD Results
21Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
OutlineOutline
The InstallationThe InstallationProblemProblem
ArchitectureArchitectureSelectionSelection
MethodologyMethodology
h fh fThe ProofThe Proofof Conceptof Concept
ConcludingConcluding
22Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
ggRemarksRemarks
ConclusionsConclusionsPOC tool applies generic methodology to focused
blproblemProvides capability to dynamically and visually trade architectures ‘Best’ design demonstrates fuel savings and increase in payload capacity for small fraction of the AES
POC enables not only study of fixed aircraft and components:
New New TechnologiesTechnologies
Ability to create architectures with entirely new and varying component listsNew technologies can be input and explored early in design With appropriate information and knowledge base, entire AES can be studied
New Installation New Installation ArchitecturesArchitectures
can be studiedHolistic Holistic
Integration Integration of AESof AES
This study serves as a stepping stone for future integration of Energy Optimized Aircraft
23Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
integration of Energy Optimized Aircraft
Future WorkFuture WorkModeling of more components and systems to realize a more complete perspective of the installation design spacecomplete perspective of the installation design space
Replacing hydraulic and pneumatic systems
Incorporate Pacelab APD’s sizing and synthesisIf i ft ld b l d t i ll i i i d th i b fit If aircraft could be scaled geometrically as in sizing and synthesis, benefits would be magnified
Requirements added to include different flight modes and failure modes
Expand knowledge base with more accurate industry informationRequirements and experience utilized for installation must be captured as q p prules and inputMore comprehensive set of evaluators can be considered
24Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
AcknowledgementsAcknowledgementsASDL Delta Airlines2008-2009 EOASys Grand
Dr. Dimitri MavrisDr. Elena GarciaDr. Neil Weston
Livia CarneiroBrian Duff Charles Harkey
2008 2009 EOASys GrandChallenge Team
N l P l Michael ArmstrongLatessa BortnerBjorn ColeC il d T i
PACEMathias EmenethGlenn Reis
Neal PatelTurab Zaidi
José Bernardo Cyril de TenorioAndrew DunbeckKelly GriendlingEric Hendricks
Glenn ReisAlexander Schneegans
José BernardoPeng Chen
David JacksonHernando JimenezLeon Phan
Sehwan OhEdward Tsai
25Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009
Questions?
26Not to be copied or reproduced without permission from the author. 3rd TEOS forum, Barcelona, 10 September 2009