brief overview of the department of aerospace · pdf filebrief overview of the department of...

22 October 2008

BRIEF OVERVIEW OF THE

DEPARTMENT OF AEROSPACE ENGINEERING

Università degli Studi Università degli Studi di Napoli Federico IIdi Napoli Federico II

DEPARTMENT OF AEROSPACE ENGINEERING

Meeting Alenia Aeronautica – Polo delle Scienze e delle Tecnologie

Pomigliano d’Arco (NA)

OctoberOctober 2008 2008 –– DepartmentDepartment ofof AerospaceAerospace EngineeringEngineeringFacolta’Facolta’ di Ingegneriadi Ingegneria

Polo delle Scienze e delle TecnologiePolo delle Scienze e delle TecnologieUniversita’Universita’ degli Studi di Napoli “Federico II”degli Studi di Napoli “Federico II”

General InformationGeneral Information

The University of Naples “Federico II”, the oldest and biggest of the five Universities in Naples, was founded in 1215.

One of the oldest “lay” University in the world.

The third biggest University in Italy (90 000 students).

The Engineering Faculty has about 13 000 students with almost all

222 Sep 2008 – Brief Overview of the Department of Aerospace Engineering – Alenia, Pomigliano d’Arco (NA)

The Engineering Faculty has about 13 000 students with almost all engineering branches and graduated about 1000 engineers each year.

Bologna convention

Laurea, after 3 years

Laurea Magistrale after 2 more years

Ph.D. Course (generally 3 years)

R O R O OO T ST S

Gabinetto di Costruzioni Aeronautiche

Founded in 1926 by

Gen. Prof. Umberto NOBILE,

polar explorer

Aerodynamics Institute Aircraft Design Institute

Gasdynamics Institute


Science and Space

Engineering Department

“Luigi G. Napolitano”

Aicraft Design Department

Department of

Aerospace Engineering

(01 January 2007)

Teaching and ResearchTeaching and Research

12

Full Professors

14

Associate Professors

10

Assistant Professors

Ph.D. Students

Research Assistants

11

Technicians

8

Administration

All Aerospace Disciplines Are Covered


FluidodynamicsNavigation &

ControlStructures

Acoustics &Vibrations

FlightDynamics

Statistics MicrogravityExperimentalAerodynamics

AerospacePropulsion

AerospaceSystems

AdvancedMaterials

RemoteSensing

Research and DevelopmentResearch and Development

AeronauticsAeronautics

VibrationVibration and and

AcousticsAcoustics

MaterialsMaterials and and

TechnologyTechnologyFlight Flight

MechanicsMechanics ThermoThermo

FluidynamicsFluidynamicsFinite ElementsFinite Elements

HypersonicHypersonic

ParticleParticle ImageImage

VelocimetryVelocimetry

Impact and Impact and

Crash Crash MechanicsMechanics

StatisticalStatistical

Energy AnalysisEnergy Analysis

Flow Flow

VisualizationVisualization


StatisticsStatistics SpaceSpace

HypersonicHypersonic

AerodynamicsAerodynamics

MicrogravityMicrogravity

Aperture Aperture

SyntheticSynthetic RadarRadarAttitudeAttitude SensorsSensors

and and NavigationNavigationRocketsRockets, , NozzlesNozzles forfor

AerospaceAerospace PropulsionPropulsion

IntelligentIntelligent StructuresStructures

and Smart and Smart MaterialsMaterials

Alternative and Alternative and

RenewableRenewable EnergyEnergy

RobustRobust DesignDesign

RAMS AnalysisRAMS Analysis

ProbabilityProbability and and BayesianBayesian

ReliabilityReliability AnalysisAnalysis

Design Design ofof

ExperimentsExperiments

Aircraft Design and DevelopmentAircraft Design and Development

High High WingWing AirplaneAirplane


High High WingWing AirplaneAirplane

Low Low WingWing AirplaneAirplane

VeryVery Light Twin Light Twin EngineEngine AirplaneAirplane

Ground TestingGround Testing

Static testingStatic testing

Ground Vibration TestingGround Vibration Testing101 103 105

102 104 106

115 113

116 114 112

111

90

88

87

89

Frequency =

Damping =

Mode S-19.29 [Hz]

2.22%

Aeroelastic CalculationsAeroelastic Calculations

Wind Tunnel TestingWind Tunnel Testing


11

12

13

14

15

16

17

18

19

20

21

22 24

23

22

21

14

13

16

15

18

17

20

19

Fus Y+

Fus Z

+61 62 63 64 65 66 67 68 69 70

121 122

123 124

125 126

127 1288

28

18

38

48

58

68

7 Wind Tunnel TestingWind Tunnel Testing

Laboratory QualificationLaboratory Qualification

DampingDamping and and AcousticAcoustic Material Material CharacterisationCharacterisation


XY

Z

1.

0.938

0.875

0.813

0.75

0.688

0.625

0.563

0.5

0.438

0.375

0.313

0.25

0.188

0.125

0.0625

2.554E-15

V1

Output Set: Mode 6, 394.271 Hz

Contour: Total Translation

Active Noise and Vibration ControlActive Noise and Vibration Control

FuselageFuselage mockmock--upup –– Alenia ATR 42 Alenia ATR 42 turbopropturboprop aircraftaircraft


Active Noise and Vibration ControlActive Noise and Vibration Control

High speed gt car – Ferrari F-50 (in collaboration with Alenia)


Morphing Structural ControlMorphing Structural Control

Morphing design requirements Morphing design requirements

Preliminary aerodynamic analysisPreliminary aerodynamic analysis

Morphing solutionsMorphing solutions

LoadsLoads


Skin morphingSkin morphing Rib morphingRib morphing

ATR42 Morphing flap designATR42 Morphing flap design

Shape Memory Alloys actuatorsShape Memory Alloys actuators


11

22

44

55

Optimization of Optimization of

Experimental Experimental

tests tests


33 66

Best performances !Best performances !

Optimization of Optimization of

the configuration the configuration

by means of GAby means of GA


OnOn

OffOff

SMA SMA actuatorsactuators

Morphing Rib SolutionsMorphing Rib Solutions

Smart flap Smart flap prototypeprototype realizationrealization

StaticStatic and and functionalityfunctionality teststests

1st 1st smartsmart flapflap forfor a a CSCS--2525 airplaneairplane

Mid Term TargetMid Term Target

Next Research GoalsNext Research Goals


Morphing Rib SolutionsMorphing Rib Solutions

MorphingMorphing LeadingLeading and and TrailingTrailing EdgeEdge

Next Research GoalsNext Research Goals

ImprovedImproved AerodynamicAerodynamic EfficiencyEfficiency

ImprovedImproved ControlControl EffectivenessEffectiveness

LoadLoad AlleviationAlleviation & & NoiseNoise ReductionReduction

Research and DevelopmentResearch and Development

StatisticalStatistical Energy AnalysisEnergy Analysis CFD (RANS) CFD (RANS) SimulationSimulation


Multi Multi AxialAxial TestingTesting EquipmentEquipment

Flight TestingFlight Testing


HardwareHardware SoftwareSoftware Results Results –– Stall TestingStall Testing

Aircraft Noise CertificationAircraft Noise Certification

FAR 36 and ICAO FAR 36 and ICAO AnnexAnnex 1616


Speed and RPM Time History

-5

15

35

55

75

95

115

13:44:52.0 13:50:42.0 13:56:32.0 14:02:22.0 14:08:12.0 14:14:02.0 14:19:52.0 14:25:42.0

Time

Speed [KCas]

-1000

0

1000

2000

3000

4000

5000

6000

Engine RPM

Flt #01

Flt #02

Flt #03

Flt #04

Flt #05

Flt #06

Flt #07

Flt #08

Flt #09

69

59

5500

Passenger Passive SafetyPassenger Passive Safety

Geven 16g DynaLab - Simulation Chart

8

9

10

11

12

13

14

15

16

17

18

Accelerazione (G)

25

30

35

40

45

50

Spostamento (in) & Velocità (f/s)

FAA/EASA Requirements

TSO/JTSO C127a & ACTSO/JTSO C127a & AC

SAE AS 8049SAE AS 8049

FAR 25.562FAR 25.562

Dynamic Lab

DynamicDynamic QualificationQualification TestsTests

Test Test SetupSetup


0

1

2

3

4

5

6

7

8

Tempo (secondi)

Accelerazione (G)

0

5

10

15

20

Spostamento (in) & Velocità (f/s)

SAE AS8049a required

2g reducted

Simulation A

Acquired A

Simulation X

Simulation V

Aircraft Seat Sled Test with Geven

Bird StrikeBird Strike

NumericalNumerical ExperimentalExperimental ComparisonComparison on on LeadingLeading EdgeEdge

Dynamic Testing Dynamic Testing

for Material for Material

CharacterizationCharacterization


Experimental Setup and Numerical Model for simulationExperimental Setup and Numerical Model for simulation

Num Exp Error

Max deflection skin [mm] 320 305 5%

Max load impact [daN] 1915 2050 4%

Duration [ms] 33 34 3%

Truss deflection [mm] 225 235 4%

Rib distance after impact [mm] 220 230 4%

RAMS AnalysisRAMS Analysis

GuidelinesGuidelines DefinitionDefinition and and AvailabilityAvailability AssessmentAssessment forfor anan AirportAirport


E N A VE N A V

Gino Lisa Gino Lisa AirportAirport

FoggiaFoggia

Wind Tunnel TestingWind Tunnel Testing

22--D and 3D and 3--D D ModelModel TestingTesting Flow Flow VisualizationVisualization


α=17°

AutomaticAutomatic Data Data AcquisitionAcquisition SystemSystem

Alternative EnergyAlternative Energy

Vertical Vertical AxisAxis TurbineTurbineHorizontalHorizontal AxisAxis TurbineTurbine RealReal InstallationInstallation


DesignDesign AerodynamicAerodynamic TestingTesting Performance Performance TestingTesting

Experimental Experimental FluidynamicsFluidynamics

12

34

1

2

3

4

y/D

-1

AdaptativeAdaptative WallWall Wind Tunnel Wind Tunnel –– HeatHeat Transfer Transfer –– ParticleParticle ImageImage VelocimetryVelocimetry


-10

12

x/D0

-1

0

1

z/D

Infrared Infrared ThermographyThermography

– Infrared thermography is a powerful non intrusive technique that enables to measure wall temperature maps;

– From these measurements it is possible to evaluate the convective heat transfer coefficient map in complex flow conditions;

– The expertise of the DIAS in this field is


– The expertise of the DIAS in this field is testified by more than two decades of experiment and publications in the field;

– As an example in the top figure is shown a reconstruction of the vortices on a rotating disk in still air and in the bottom one the surface distribution of the normalized Nusselt number on a 180deg turn ribbed channel.

Visualization of the vortex pattern in a rotating Visualization of the vortex pattern in a rotating

disk in still air.disk in still air.

0.0 1.0 2.0 3.0 4.0 5.00.0

1.0

2.0

Quantitative measurement of the normalized Quantitative measurement of the normalized

NusseltNusselt number in a ribbed channel.number in a ribbed channel.

Particle Image Particle Image VelocimetryVelocimetry -- PIVPIV

– PIV and stereo PIV are experimental techniques that enables to measure instantaneously 2 or 3 components of the velocity vector on a plane;

– The experimental group present at DIAS is well known world wide for their expertise in both techniques;

– From PIV and Stereo PIV data it is


– From PIV and Stereo PIV data it is possible to evaluate mean flow fields, vorticity fields, turbulent statistics etc;

– By combining measurement in different planes it is possible to obtain a full 3D representation of the flow phenomenon. As an example the vorticity field in the second half of the turn of a rotating channel is shown in the Figure.

3D3D--reconstruction of the reconstruction of the vorticity’svorticity’s distribution distribution

in the second half of the turn: in the second half of the turn: ReRe=20000 and =20000 and

RoRo=0.3.=0.3.

ThermoFluidynamicsThermoFluidynamics

AdvancedAdvanced methodsmethods ofof nonnon--modalmodal instabilityinstability ofof linearlinear mechanicalmechanical systemssystems

drivendriven byby nonnon--normalnormal differantialdifferantial operatorsoperators. . ApplicationApplication toto fluidynamicsfluidynamics

((viscousviscous flow flow controlcontrol, , vortexvortex instabilityinstability) and ) and toto fluidfluid--structurestructure interactioninteraction

((panelpanel flutterflutter instabilityinstability).).


NumericalNumerical modellingmodelling ofof syntheticsynthetic jet jet micromicro--devicesdevices (MEMS) (MEMS) forfor: flow : flow

controlcontrol ((separationseparation and/or and/or transitiontransition); ); coolingcooling ofof smallsmall areasareas; ; micromicro--thrustthrust

generation generation forfor MAV (MAV (micromicro--aerialaerial--vehiclesvehicles).).

V.O.F.V.O.F. ((volumevolume--ofof--fluidfluid) ) methodsmethods forfor the the numericalnumerical simulationsimulation ofof free free

surfacesurface motionmotion includingincluding surfacesurface tensiontension effectseffects..

Technological LaboratoryTechnological Laboratory

LASER Applications

Composites materials (development, production process and testing).

Application of Acoustic Emission technique (AE) for non destructive control evaluation

and process monitoring.

Application of laser in macro and micromanufacturing (cutting, welding, engraving and

marking).


Grove geometry of

micro cutting on SMAMicrp gripper cut by laser Aesthetical application of

laser marking on AISI 304

Hypersonic AerodynamicsHypersonic Aerodynamics

Molecular Aerodynamics and MONTE CARLO Method

Space vehicles fly in a rarefied environmen where the continuum mechanics is notvalid anymore. In such conditions “classical CFD methods cannot be used.

A technique useful for the computation of the aerodynamic coefficient and thethermal flow is based on the gas kinetic theory, based on a statistical approach, forwhich the “Direct Simulation Monte Carlo” (DSMC) method is an example.


Geometry of the FTB-X vehicle

to be developed at CIRA

Cell computational

domain

Polar curves at different altitudes

MicrogravityMicrogravity

Numerical simulation and experimental testing of complex multiphase flows,

Texus launcherMaragoni instability effect (numerical and

experimenal correlation) International Space StationParabolic flights


Numerical simulation and experimental testing of complex multiphase flows,with temperature gradients and different concentrations.

Definition of experiments onboard the International Space Station (ESAcollaboration)

Collaboration with:

Non-coalescence of two drops at different

temperature (CCD and thermographical pictures)

MicrofluidicsMicrofluidics

ThermophisicalThermophisical propertiesproperties

measurementsmeasurements

““SelfSelf--rewettingrewetting”” fluidsfluids andand

nanofluidsnanofluids forfor heatheat exchangerexchanger

KaptonKapton flexibleflexible radiatorsradiators with “self with “self

rewettingrewetting” ” fluidsfluids


HighHigh efficiencyefficiency heatheat pipespipes developmentdevelopment (Joint(Jointpatentpatent -- JapaneseJapanese PatentPatent office,office, nn.. 20070024362007002436))..DevelopmentDevelopment ofof anan experimentexperiment onboardonboard thethe ASIASImicrosatellitemicrosatellite MIOSatMIOSat

rewettingrewetting” ” fluidsfluids

ThermographicalThermographical picturespictures

TestingTesting chamberchamber forfor parabolicparabolic flightsflights

CollaborationCollaboration with:with:

Parabolic FlightsParabolic Flights

PhysicsPhysics ofof FluidsFluids in a in a MicrogravitationalMicrogravitational EnvironmentEnvironment


Marangoni Marangoni instabilityinstability in a in a liquidliquid bridge and bridge and

aroundaround a a bubblebubble (CCD (CCD picturespictures and temperature and temperature

distributiondistribution fromfrom CFD CFD programsprograms))

ParabolicParabolic FlightsFlights and International and International SpaceSpace Station (ISS)Station (ISS)

PotentialPotential developmentdevelopment::

SKYSKY--X X asas PlatformPlatform forfor ExperimentsExperiments in in ParabolicParabolic FlightsFlights

SynthethicSynthethic Aperture RadarAperture Radar

Main objectives: High resolution remote sensing for topographical applications, velocity

measurements, multi-angle observations to improve selectivity and classification.

Mission approved by ASI

Bistatic interferometric space mission of a Synthethic Aperture Radar operating in conjunction

with the Italian Mission COSMO-SkyMed


Mission approved by ASI

Thales Alenia Space prime contractor

Operated under the scientific

supervision and responsibility of

DIAS

BistaticBistatic SAR SAR forfor EarthEarth observationobservation

Guidance, Navigation Guidance, Navigation && ControlControl

Development of GN&C algorythms for

unmanned space vehicles:

Collaborations with CIRA for the USV

(Unmanned Space Vehicle) project


Development of GN&C algorythms for

measurement and control of satellites

flying in formation:

ASI projects, jointly developed with Thales

Alenia Space Italy in the framework of the

bistatic mission SABRINA

Space SensorsSpace Sensors

Stellar sensor MOS

Development of prototypes of solar and stellar sensors


INS-GPS System (Micro Electro-Mechanical

System for the inertial-satellite integrated

navigation)

Stellar sensor MOS

Solar sensor CMOS (Micro

Electro-Mechanical System)

The solar sensor has been selected as demonstation payload onboard the first ASI microsatellite (MIOSAT)

Autonomous Obstacle DetectionAutonomous Obstacle Detection

Real Time

Computer

(deterministic

OS)

Real Time

Computer

(deterministic

OS)

Image

Processing

Computer

(conventional

OS)

Image

Processing

Computer

(conventional

OS)

GNC Computer

(with ACA

decision

making logic)

GNC Computer

(with ACA

decision

making logic) Servos

Servos

AHRS

GPS

AIR

Ethernet

EthernetFirewire

BUS

CAN BUS

Radar

Panchro VIS

Color VIS

IR left

Real Time

Computer

(deterministic

OS)

Real Time

Computer

(deterministic

OS)

Image

Processing

Computer

(conventional

OS)

Image

Processing

Computer

(conventional

OS)

GNC Computer

(with ACA

decision

making logic)

GNC Computer

(with ACA

decision

making logic) Servos

Servos

AHRS

GPS

AIR

Ethernet

EthernetFirewire

BUS

CAN BUS

Radar

Panchro VIS

Color VIS

IR left

System Hardware ArchitectureCIRA Flying Laboratory


OS)OS)

ALTIR right

Navigation Sensors

OS)OS)

ALTIR right

Navigation Sensors

•DIAS supports the TECVOL project of the Italian Aerospace Research Center (CIRA) for

the realization of a prototype system for Autonomous Collision Detect Sense and Avoid

based on an airborne Radar, four Electro-Optical sensors, and two processing units;

•DIAS designed prototype’s hardware architecture and developed the relevant real-time

sensor data fusion software for airborne obstacle detection and tracking;

• The prototype has been installed oboard a VLA manned aircraft with optional automatic

control to be tested in controlled collision scenarios including an intruder aircraft.

11stst

Project 1st : autonomous Flyer for Integration of Remote Sensing Technologies and guidance, navigation, and

control aimed at monitoring environmental riskMini-UAV installation

Light aircraft installation


Acquisition example

Thermal image Single-band hyperspectral

image mosaic

Aerospace PropulsionAerospace Propulsion

Pressure instability measurement and

analysis inside the combustion chamber

Combustion simulation for

Performance measurements of propellants

including aluminum nanoparticles


Hybrid propellant rocket

Max thrust up to 2000 N

Combustion chamber pressure

up to 30 atm

Combustion simulation for

Ram/scram jets

Non-conventional supersonic nozzles

Green Propellants for

OMS and RCS applcations

Space StructuresSpace Structures

Finite Element thermoelastic analysis of a space qualified equipment


Shaker Table for dynamic, random and shock space qualification

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