Georgia Tech EOASys Grand Challenge Team Study Turab …...To Hydraulic Engine Driven Pump Concept...

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







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


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


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


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



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



AGB

Pneu. Starter

EBAS

Power Generation Power Generation –– TurboTurbo--CellCell

Provide Non-Prop

Power

Produce Thrust

HydrogenHydrogen

Weight

Fuel

Requirement

Starting Power

Requirement

ThrustThrust



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



HAControl Surface

s


…Weight

Engine Reverse

Drag

Volume needed




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


Weight

Volume needed

Powerreq Impulse System

…Val ves




Frequencyreq


Piccolo

……

Heatreq Weight

Volume needed



Protect From Icing

Val ves

Weight

Volume needed

Heatreq


Electric Mats

……Val ves



Weight

Volume needed


……Val ves




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


Drag generated

control needed

Concept 2

Fly

Missionreq

Wing

Wing

Liftreq

Missionreq


Drag generated

control needed


Air Cycle

Machine

Mixing Chamber

Ozone Converter

Distribution System

Pressure Valve

…

mreq

Preq

.

Treq

Weight

RAM air scoop

Drag

Volume Needed

Pneumatic Power Needed


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


Air Cycle

Machine

Mixing Chamber

Ozone Converter

Distribution System

Pressure Valve

…

mreq

Preq

.

Treq

Weight

RAM air scoop

Drag

Volume Needed



Air Cycle

Machine

Mixing Chambe

r


System

Pressure Valve

…

RAM air Com presso

r

Conditioning of Air

mreq

Preq

.

Treq


Volume Needed

Weight

Drag

VVI

Forcereq

Forcereq



HAControl Surface

s


…Weight

Engine Reverse

Drag

Volume needed




Control Surface

…

Engine Reverse

Control

Hydrauliclines

Weight

DragVolume needed

EHA

Cooling needed

Forcereq

Forcereq



HAControl Surface

s


…Weight

Engine Reverse

Drag

Volume needed




Control Surface

…

Engine Reverse

Control

Hydrauliclines

Weight

DragVolume needed

EHA

Cooling needed


Piccolo

…

Heatreq Weight

Volume needed



Protect From Icing

Val ves

Weight

Volume needed

Heatreq


Electric Mats

…Val ves



Weight

Volume needed


…Val ves




Frequencyreq


Piccolo

……

Heatreq Weight

Volume needed



Protect From Icing

Val ves

Weight

Volume needed

Heatreq


Electric Mats

……Val ves



Weight

Volume needed


……Val ves




Frequencyreq


Drag generated

control needed

Concept 2

Fly

Missionreq

Wing

Wing

Liftreq

Missionreq


Drag generated

control needed


Drag generated

control needed

Concept 2

Fly

Missionreq

Wing

Wing

Liftreq

Missionreq


Drag generated

control needed


Air Cycle

Machine

Mixing Chamber

Ozone Converter

Distribution System

Pressure Valve

…

mreq

Preq

.

Treq

Weight

RAM air scoop

Drag

Volume Needed



Air Cycle

Machine

Mixing Chambe

r


System

Pressure Valve

…

RAM air Com presso

r

Conditioning of Air

mreq

Preq

.

Treq


Volume Needed

Weight

Drag


Air Cycle

Machine

Mixing Chamber

Ozone Converter

Distribution System

Pressure Valve

…

mreq

Preq

.

Treq

Weight

RAM air scoop

Drag

Volume Needed



Air Cycle

Machine

Mixing Chambe

r


System

Pressure Valve

…

RAM air Com presso

r

Conditioning of Air

mreq

Preq

.

Treq


Volume Needed

Weight

Drag

VVI

Lack of a modeling environment has caused a discontinuity in the design


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


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


OutlineOutline







ggRemarksRemarks

The Architecture Selection Methodologygy

St StepStep 6Step 1

Component Library Component Library CreationCreation

Investigate Investigate Competing Competing

ArchitecturesArchitectures


Investigate Investigate Competing Competing

ArchitecturesArchitectures

Step 1

Step 6 Investigate Investigate

Competing Competing ArchitecturesArchitectures

Step 6


Step 1

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


Step 2


Step 2


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


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


p4


p


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


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



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


Constraints and requirements on

Fire Zone

General General


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


Baseline aircraft with componentsplaced to meet requirements

into Pacelab APD using Excel file


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


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


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...

…


An optimized architecture based on customer preferences

the saved measures of merits

Pacelab APD Front-EndPacelab APD Front End


Pacelab APD Avionics Bay Pacelab APD Avionics Bay


Pacelab APD ResultsPacelab APD Results


OutlineOutline







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


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


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


Questions?


Georgia Tech EOASys Grand Challenge Team Study Turab …...To Hydraulic Engine Driven Pump Concept...

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