Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Speaker: Antonio Concilio, [email protected]. of Adaptive Structures, Head
CIRA,the Italian Aerospace Research Center
Applications of Active Systems for Noise and Vibration Abatement in Automotive Environments
PSU – CAV Workshop, 2017 – State College (PA-USA), April 25th-26th
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
IndexThe Italian Aerospace Research Center, an OverviewLow Noise: Synthesis and Main Project Attainments
SARISTU – AS02; The Adaptive Trailing Edge Device – ATEDA Short Presentation of the Computational Acoustics Lab.
Applications of Active Systems for Noise and Vibration Abatement in Automotive Environments
PSU – CAV Workshop, 2017 – State College (PA-USA), April 25th-26th
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
An Overview of CIRA,The Italian Aerospace Research Centre
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Overview of CIRACentro Italiano Ricerche Aerospaziali
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
⌐ A non-profit public-private partnership among: ASI (Italian Space Agency) - 47% CNR (National Council for Research) - 5% Campania Region - 16% Italian Aerospace Industries - 32%
⌐ 370 employees and approx. 50 university students and PhD candidates a year
⌐ Partner of the main European research programs in the aerospace field (JTI CLEAN SKY, SESAR, MIDCAS, etc.)
CIRA in Brief
In 1989, the Italian Government entrusted CIRA the
management of the Italian Aerospace Research Program
(PRORA) to support the competitiveness of the Italian
aerospace community by the:
CIRA performs PRORA management under the control of Ministry ofResearch (MIUR).
development of strategic research programs,
development and operation of strategic testing facilities,
enhancement of scientific competences and expertise.
5
ITALIA
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
1 Main gate2 Aeronautics and Space
Division3 Canteen 4 Headquarters,
Supercomputing Centre5 Modeling and Design Methods
Laboratories6 LISA – Crash Test Facility7 Experimental Aerodynamics
and Transonic Wind Tunnel8 HVAC, cooling towers, main
compressed air station9 IWT – Icing Wind Tunnel10 PWT – Plasma Wind Tunnel11 Airport (IT MoD property)
1
2
34
5
6
7 8
9
10
11
CIRA SITE SPANS OVER 160 HECTARES
6
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Organization Chart
7
PRESIDENT
HUMAN RESOURCESVALORIZATION
PROMOTION OF R & TD RESULTS - IPR
PROTECTION
STRATEGICPROGRAMMING &
BUSINESSDEVELOPMENT
SOCIETY AND LEGALAFFAIRS
MANAGEMENT OFSOCIETY
PARTICIPATION
INTERNAL AUDITINGAND TRANSPARENCY
GENERALDIRECTOR
ACCOUNTINGMANAGEMENT
QUALITYASSURANCE
HUMANRESOURCES
ADMINISTRATIONLOGISTICS PURCHASE FINANCE
DOCUMENTATIONCENTER
SCIENTIFICDISCIPLINES
AERONAUTICS SPACEENVIRONMENT& TERRITORY
BIG TESTINGFACILITIES &
IN’STRUCTURES
INFORMATICS& SCIENTIFICCOMPUTATION
ON-BOARDSYSTEMS &
ATM
FLUIDMECHANICS
AERO-THERMO-DYNAMICS
ENVIRONMENTALIMPACT OF AIR
TRANSPORT
MEASUREMENTSMETHODS ANDTECHNOLOGIES
SAFETY & RELIABILITY
STRUCTURES& MATERIALS
ADAPTIVESTRUCTURES
SOFTWAREDEVELOPMENT
& VIRTUALREALITY
PROPULSIONELECTRONICS
& DATATRANSMISSION
DR. CLAUDIO ROVAI
ING. MASSIMO CAVALIERE
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Knowledge
AerodynamicsAeroacoustics
Aerothermodynamics
……….
GN&C and on Board Systems
ATM
IcingPropulsionRAMS
Structures and Materials
Adaptive Structures
Software Technologies
System Integrations
Vibroacoustics
x [cm]
y [c
m]
0 5 10 15 20
-6
-4
-2
0
2
4
6 10
20
30
40
Competences
8
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Facilities
9
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
PWT – PLASMA WIND TUNNelOperational since 2002, is world unique for power andsize. Capable to simulate high speed orbital and super-orbital re-entry to test safety critical thermal protectionsystems of space vehicles.
IWT – ICING WIND TUNNELOperational since 2003, is world unique for size, testenvelope. Capable to simulate clouds within currentand foreseen certification envelopes to improve flightsafety in icing condition.
LISA – CRASH TEST FACILITYOperational since 2003, is world unique for testingenvelope. Capable to simulate landing scenario incase of accidental ground impact to improvepassenger and payload protection.
PT1 – TRANSONIC PILOT TUNNELOperational since 1999, for transonic and supersonicaerodynamic simulation (M<0.4 cont. M<1.4 int.)
Facilities
10
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
LOW NOISE
MAIN REFERENCES• Full Title: NEW TECHNOLOGIES AND MATERIALS FOR NOISE ABATMENT IN CAR VEHICLES• Acronym: LOW NOISE• Call: MIUR 2010• Type of Action: Research• Topics: Advanced Transports and Logistics• Duration: 3 Years
OBJECTIVES• To reduce noise and vibration with sustainable solutions that minimize the impact on weight and other
vehicle features that may have negative consequences on fuel consumption and emissions
GLOBAL VALUE AND EXTENSION• Overall Budget: 10 Millions Euro• Project Duration: 36 months
PARTNERSHIP• Number of Partners: 9• Industry: 2; Universities: 4; Research Centres: 3
Use or disclosure of the information contained herein is subject to specific written approval from CIRA 12
LOW NOISE – HIGHLIGHTS
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
► Digital Active Noise and Vibration Control applications• Active Vibration Control by Piezoceramic actuators of a car rear under‐seat floor panel• Active Vibration Control of a mounting bracket for automotive gearboxes
► Design, Simulation, analysis and testing of Low Noise configurations and Active Control devices:• Optimal Mass/Stiffness distribution during design• ANC to further enhance interior comfort
Adaptive Structures Division – The LOW NOISE Project
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
OR3 - SEALING
OR4 - ACTIVE CONTROL
OR5 - AEROACOUSTICS
OR2 - SOUNDPROOFING
OR6 – ROLLING NOISE
OR2 - SOUNDPROOFING
OR6 – ROLLING NOISE
OR1 - SPECIFICATIONS
OR7 - METHODOLOGIES
INTERIOR NOISE INTERIOR NOISE EXTERIOR NOISE
LOW NOISE - PROJECT LOGIC
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
1. SMA based adaptive seals for sound insulation2. Semi-active tonal vibration reduction of internal
automotive subsystems3. Active tonal vibration reduction of internal components
by piezoceramic stacks4. Active tonal distributed vibration control by piezoceramic
patches5. Reduction of the rolling wheel noise through a distributed
active vibration control of the backseat area by PZT
OBJECTIVES
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Title: SMA based adaptive seals for sound insulation
Objective: Increase of the sound insulation capability of automotive seals, to compensate the leakage effects due to the aerodynamic loads acting on the doors during the cruise phase
Reference persons: S. Ameduri, A. Brindisi, M. Ciminello, A. Concilio
Publications/IPR aspects:Patent pending
SMA Seals
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Concept/strategy adopted: Expansion cells integrated within the seal cavities, actuated by SMA linear elements to press the seal foam against the door and the cabin frames, thus enhancing the adhesion
SMA systemSeal foam
Cell off
Door and cabine frames
Cell switched off during door
closure
Cell switched on during cruse
SMA system
SMA Seals
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
FE cell modeling
Non linear FE analysis aimed at estimating:spostamento assiale
imposto
zona vincolatasealing
SMA Seals
o straino axial cell activation forceo radial displacemento radial force transmitted to the sealing
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
ABS prototypes
Lab setup
Prototype for integration
Cell integration within the seal
Integration
Results & Benefits
SMA Seals – Experimental Results
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Title: Tonal vibration reduction of internal automotive subsystems
Objective: Feasibility study of a «switched shunt resonator» for the vibration reduction of a wiper windshield at resonances in the frequency range of 600-850 Hz.
Reference persons: M. Ciminello, R. di Leo, M. Viscardi (UniNA)
Publications/IPR aspects:Paper Submitted to JTAM 10-jun-2016 Paper ID: 23353276
Wiper Control
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Concept / strategy adopted 1/3: Preliminary vibro-acoustic characterization of the device under test and control system design.
0.00 1500.00Hz
0.00
0.03
Ampl
itude
Pa0.00
1.00
Ampl
itude
691.43
F AutoPow er mic 1 tergicristallo 10 sF AutoPow er driver sx 10 sF AutoPow er driver dx 10 s
Measured parameters:
• Acoustic level outside the vehicle
• Acoustic level inside the vehicle
The windsield wiper produces noiselevels two magnitudes higher than thenoise produced by the car engine.
Tichness 2.2 mmArea 9384.8 mm2E 180 Gparho 7800 Kg/m^3
Wiper Control
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Concept / strategy adopted 2/3: Experimental evaluation of the strain map of the bracket by using the vibro-meter laser.
Vel 1
Vel 2
The measured voltage amplitude is about 200mV
Wiper Control
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
CfL
mech2102
1
The shunt resonatorneeds a supply of 0.5V
At lower frequency the shunt resonator produces some effects when a sine excitation is provided
Wiper Control – Experimental results
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Title: Active Tonal Vibration Reduction of InternalComponents
Objective: Feasibility study of a feedforward control systemfor the vibration reduction of a gearbox bracket in the frequency range of 500-3000 Hz.
Reference persons: M. Ciminello, I. Dimino, D. Magliacano, M. Viscardi (UniNA), A. Concilio
Publications/IPR aspects:International Journal of Mechanical Engineering, 1, 69-74 (2016)
Gearbox Bracket
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Concept/strategy adopted 1/2: Preliminary characterization of the device under test and control system design.
Mode I Mode II872.15 Hz 1599.4 Hz
FEM and Experimental validation of the bracket with• Resonance search test• Sweep excitation 500-2000Hz• 6 triaxial accelerometers
Gearbox Bracket
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Concept/strategy adopted 2/2: Piezo stack selection and layout design.
Gearbox Bracket
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
The blue curve is the baseline response. The red curve is the effect of the control system on the braket vibrationusing a force of 1 N acting in phase opposition, while the yellow curve is the structural response by using a force of1.3 N with an optimized phase of 169 deg.
The feedforward control system provide a vibration reduction of 75% (-12dB).
Tavolo
vibrante
Gearbox Bracket – Experimental Results
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Title: Active Tonal Vibration Control by PiezoceramicActuators of a Car Rear Under-Seat Floor Panel
Objective: Implementation of a FF ASAC control through a PZT network
Reference persons: I. Dimino, A. Concilio, D. Magliacano, M. Viscardi (UniNA)
Publications/IPR aspects: D. Magliacano, I. Dimino, M. Viscardi, A. Concilio, “Active Vibration Control by PiezoceramicActuators of a Car Floor Panel”, Proceedings of the 23rd ICSV 2016 Conference, July 10-14 2016.
Under-seat Panel
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Concept / strategy adopted: • Problem identification through Transfer Path Analyses• FE modeling and prediction of the PZT effectiveness in reducing noise• Active Control System logic development and DSP implementation • Setup preparation • Test validation
Under-seat Panel
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Numerical optimization and performance estimateModal strain plots – experimental data
Under-seat Panel – Experimental Results
Sensors / actuators location
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Under-seat Panel – Experimental Results
Noisysignals
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Title: Reduction of the rolling wheel noise through the active control of the supporting structure of the backseat
Objective: Implementation of a collocated feedback control through a PZT network installed onto the back seat structural support
Reference persons: S. Ameduri, I. Dimino
Publications/IPR aspects: Journal papers preparing
Rolling Wheel Noise
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Concept/strategy adopted:
• Topologic optimization driven by the energy transmission map of the back seat supporting panel
• FE modeling of the panel for predicting the effectiveness of the PZT network in reducing the noise levels
• Setup preparation and backseat panel integration with PZT patches
• Validation tests
Rolling Wheel Noise
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Numerical optimization and performance estimateTransmission energy maps computation and identification of the most effective location of the PZT patches
Rolling Wheel Noise
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Experimental tests
Setup design and preparation
Installation of the PZT network
Achieved results
SPL significant abatement over 1000Hz (2 actuators):• -7,3dB at 1600Hz• -7,0dB at 3150Hz• -6,6dB at 4000Hz
Rolling Wheel Noise – Experimental Results
Estimated power = 100 W
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
SARISTU – AS02The Adaptive Trailing Edge Device – ATED
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Leader: Airbus, 64 Partners from 16 EU Countries, 51M€ budget, duration09.11-08.15. Addressing two full-scale integrated demonstrators: a Multi-functional Fuselage Structure and a Morphing Wing section. Referring to thelatter, the project targeted to WTT advanced technologies to enhance A/Cperformance (fuel consumption, weight, operative costs, noise emissions, …).
The SARISTU Project, www.saristu.euFunded by the EU (7th FW Progr. for research, tech. dev. & demonst. – Grant agreem. N. 284562
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Concept Illustration
Concept fundamentalsMorphing is enabled by a multi-finger architecture driven by load-bearing actuator systems (hidden in the figure). To provide camber variation, devices are designed to work synchronously but can be activated differentially. A control system drives the actuators action after info gained by a strain sensor network. Skin absorbs part of the external loads and insures a smooth profile. The system keeps its structural properties while actuated. Loaded static & dynamic responses are considered.
Technology OverviewGoalCivil AC flight profiles are quite standard but different missions may be flown (fast or slow, at low or high altitude). Lift coefficient can vary between tenth to unit while weight reduces by a quarter as the fuel burns. The best configuration then changes, having to match new conditions.ObjectivesThe project addresses medium-range AC (around 3h cruise flight). Chord-wise camber variations are implemented through TE adaptations to get optimal geometry for different flight conditions. BenefitsUpgrades are herein measured as reduction of fuel consumption or increase of range, estimated about 3% or more. L/D ratio is the parameter that may synthetically express these performance variations, kept to its optimal value while weight and angle of attack variate. Because span-wise adjustments may lead to RBM reduction and then to design weight decrease, this potentiality can be exploited.
The SARISTU Project – The ATED Concept
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
AS02 (2-bay) demo
IS12 (5-bay) demo
The Adaptive Trailing Edge Device (ATED) is one of the three adaptive wing components developed within SARISTU and integrated into the full-scale WT Demonstrator.
WT demo
Polimi computations show a reduced CD respect to the Onera ones (probably due to viscous effect not properly taken into account in the Euler code)Wing adaptation benefits are higher with a morphing flap respect to a plain flap (without gap) in the normal aircraft operating range
SARISTU Project – ATED Expected Performance
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
ATED, the Adaptive Trailing Edge Device ATED Team Leader: CIRA, 14 Partners, around 5 M€ budget, 09.11 – 08.15
Morphing – The SARISTU Project – The ATED
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Definition of Requirements & Specifications
Morphing Structure DesignAerodynamic design
TE box
Skin
Systems Design
Actuation & Control
Sensing(& AS04 Team)
Stress report, Aeroelastic assessment
Executive drawings and manufacturing of prototypes Experimental tests
FHA Assessment, Results Analysis
The ATED Logic
Morphing – The SARISTU Project – The ATED
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
This presentation is aimed at providing the status of the AS02 developments at the date, attained by the joint effort of people from different partners. The following colleagues & friends provided their valuable support:
Saverio CORBO, Valerijan COKONAJI, Yasser ESSA, Federico MARTIN De La Escalera, Victor MUNOZ, Augusto OTERINO (AERNNOVA)
Steffen BAUSS (AIRBUS), Giovanni Marco CAROSSA (ALENIA)Okan GULAÇ, Sermar GÜNTER, Hatice NAROĞLU, Enis OKAN, Cem SAPMAZ, Hakan TEKIN (ATARD)
Monica CIMINELLO, Ignazio DIMINO, Gianluca DIODATI (CIRA)Andrè GRATIAS, Mathias LIPOWSKI, Martin SCHUELLER (FhG-ENAS)
Andreas LUEHRING, Christof NAGEL, Bernd SCHNEIDER, Oliver SCHORSCH, Michael WOLF (FhG-IFAM)Moshe STEINBUCK, Shlomo ROSENTAL, Avner VOLOVICK, Lior ZIVAN (IAI)
Christos KOIMTZOGLOU (INASCO)Haim ABRAMOVICH, Eyal PRESENTE (INNOWATTECH)
Marco BELLUCCI, Alfonso CELANO (MARE)Antoine DUMONT, Jean-Luc GODARD, Fabien HUVELIN, Cedric LIAUZUN (ONERA)
Francesco AMOROSO, Leonardo LECCE, Marco MAGNIFICO, Rosario PECORA (UNINA)
Other people supported in many ways our activity, involved in other parts of SARISTU:Katrin GENZEL, Ben NEWMAN, Piet Christof WOELCKEN (AIRBUS), Alfonso APICELLA, Salvatore RUSSO, Giuliano CATTANEO, Domenico CAVEZZA, Carlo RICCIARDELLI, Lorenzo ROSSI (ALENIA), Kristina DITZEL, Andreas KOETTER, Rebecca WALDLEICH (ALTRAN), Salvatore AMEDURI (CIRA), Sergio RICCI, Alessandro DE GASPARI (POLIMI), Michelangelo GIULIANI (REDAM), Rolf EVENBLIJ, Merlijn KUIN, Iskander DEERENBERG (TECHNOBIS)
To all of them, I would express my sincere thanks.… To Ignazio & Rosario a special acknowledgement for their continuous assistance in carrying out the AS02 scenario … Antonio CONCILIO
The ATED Team (SARISTU AS02)
Morphing – The SARISTU Project – The ATED
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Adaptive Trailing Edge Device, ATED (CIRA)
Adaptive Leading Edge (DLR)
Wing Box – Instrumented for SHM (Alenia)
Location of Fairings 1
Location of Fairings 2
Assembly RigAdaptive Winglet (EADS)
Morphing – The SARISTU Project
The ATED integrated to the Adaptive Wing Demonstrator with other morphing devices
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Info Reserved. For public info please refer to:
http://tsagi.com/pressroom/news/2192/?sphrase_id=13887
Or
http://www.saristu.eu/2015/06/saristu-end-of-project-meeting-conference/
Morphing – The SARISTU Project – WTT Tests @ TsAGI (RUS)
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Division of Environmental Impact of Air Transport
Computational Acoustics Lab.
CIRAItalian Aerospace Research Center
Points of ContactAeroacoustics: Mattia Barbarino ([email protected])
Vibroacoustics: Pasquale Vitiello ([email protected])
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Computational Acoustics Lab. - Mission
► Development of methodologies and numerical tools for Aeroacoustics and Vibroacoustics:• Aerodynamic noise generation and radiation models• Noise shielding and propagation models• Fluid‐structure interaction, transmission loss and radiation efficiency
► Simulation, analysis and design of Low Noise configurations and devices:• Tiltrotor, Rotorcraft, Aircraft, Engines and Automotive components
CAR SIDE MIRRORTurbulent source field (SNGR)
ACOUSTIC HEMISPHERESound Pressure Level
(FWH)
FUSELAGE SHIELDINGReal part of the acoustic pressure
(BEM)
ROTORCRAFT NOISE PROPAGATIONReal part of the acoustic pressure
(FWH+FEM)
NOISE REDUCTION TECHNOLOGYLined Flap
LAUNCHER NOISEHybrid approach
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
CAA approaches for low-noise technologies design
Broadband Noise Prediction by means RANS-based models
Fuselage Scattering on Noise Radiated byAircraft, Rotorcraft and Tiltrotor
Low-Noise Rotor / Propeller Design
Noise Human Response
Interior noise prediction and control
Computational Acoustics Lab. – Applications
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Interior noise prediction and control.Noise generated by TBL pressure field ‐ Convected field effects on acoustic properties of metallic and composite panels.
References:Marino, A., Vitiello, P., et al., Innovative vibration and acoustic methodologies for the design of enhanced composite panel for aircraft applications, 31st AIAA Applied Aerodynamics Conference, 2013;
Vitiello, P., De Rosa, S., Franco, F. , Convected field analysis of flat panels response to turbulent boundary layer induced excitation, Aerospace Science and Technology, Elsevier, 2008
Projects:
ENABLE: Environmental Noise Associated with TBL Excitation - EU funded Program AMACA : TBL noise transmitted by composite panels – Alenia funded Program
Kx/k
Ky/k
Radiation
Efficiency M=0
Scheme of the experimental setup for Vibro‐acoustic Tests in Wind Tunnel
Convected field effect on Radiation Efficiency (left) and Dynamic Properties (right)
10210-3
10-2
10-1
100
101
102
103 Aluminum Panel P1 - TBL Response - Structural Damping 0.003
Frequency (Hz)
Nor
mal
ized
Acc
eler
atio
n P
SD
(m/s
2 /Pa)
2
M=0.4M=0.5M=0.6M=0.7M=0.8
COMPUTATIONAL ACOUSTICSINTERIOR NOISE PREDICTION AND
CONTROL
Computational Acoustics Lab. – Interior Noise Prediction and Control
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
Launcher Aero-Vibro-Acoustic prediction during the lift-off.‐ Hybrid empirical‐CAA approach for external noise generation and radiation.
An improvement of the Eldred standard model has been formulated in order to investigate the sourcescorrelation effects and to propagate them through a wave equation. The noise prediction obtained with therevised Eldred‐based model has then been used for formulating an empirical/BEM hybrid approach that allowsto evaluate the scattering effects. In the framework of the European Space Agency funded program VECEP, thesemodels have been applied for the prediction of the aeroacoustic loads of the VEGA launch vehicle at lift‐off andthe results have been compared with experimental data.
‐ Hybrid FEM/SEA approach for vibration and internal noise prediction.The external acoustic field has been used for the Inter‐Stages structural and interior cavity response in the midfrequency range by employing an Hybrid FEM‐SEA model. Acquisition of Equipment acceleration level to assesstheir qualification status required them to be modelled as concentrated mass rigidly connected to the Inter‐Stage skin. Due to the large Inter‐Stage dimensions and the extension of the frequency range to be investigatean appropriate balance between accurate dynamic response and computational cost containment was achievedby recurring to the Hybrid modelling approach. An acoustic diffuse excitation field was assumed for each Inter‐Stage and the response of the FEMmodelled Equipment acquired at their attachment points.
Project: VECEP Program, funded by AVIO SpAReferences:
Barbarino, M., Adamo, F., P., Bianco, D., Bartoccini, D., “A hybrid approach for launch system scattering of empirical correlated noise sources in rocket noise prediction”, ICSV2016 Conference (Athens, 10-14 July 2016)
Computational Acoustics – Launcher Aero-Vibro-Acoustic Prediction
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
0
(free‐field) (near‐field shielding effects)Real part of the acoustic pressure at kR=5.5. Launcher altitude 0m.
SPLs in third band octave at interstage level. Comparison between Eldred models and
experimental data.
(Lower Section Structural Model) (Upper Section Structural Model) (Interior Cavity Acoustic Model)Hybrid FEM‐SEA model of a VEGA Launcher Inter‐Stage
EXCITATION
RESPONSE
Computational Acoustics Lab. – Launcher Aero-Vibro-Acoustic Prediction
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
BEM‐DbbFMMNumerical solution of convected Helmholtz equation:• Pressure based (Lighthill) and potential based (Pierce) formulation;• Bounday conditions (rigid, vibrating, impendance wall, …);• CHIEF regularization of the sporious frequencies handling complex geometries;• Numerical scheme based on centered cells and isoparametric formulation;
• Interface with FW‐H for scattering problems;• Directional Black‐Box Fast Multipole Method (DbbFMM).
Writing/reading interface:• Compatible with several visualization packages and softwares (tecplot, fieldview, AVS …)
References:Barbarino, M., Bianco, D., BEM-FMM Simulation of Uniform mean flows with a new internal-point Algorithm for the CHIEF Spurious Solutions Removal,ICSV2016 Conference (Athens, 10-14 July 2016)Barbarino, M., “Aeroacoustic methods for low-noise technologies design”, Federico II University of Naples, PhD Thesis, 2013.
Computational Acoustics Lab. – BEM-DbbFMM
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
The work herein presented is the result of the efforts of manyresearchers and colleagues, working at CIRA, University ofNapoli and other companies, who contributed in different waysand in several moments to the development of the «Adaptive(or Smart) Structures» technology…Really, nothing (or very few) could have been done without theenthusiastic concurrency of so many expertises, engineeringand not.
Acknowledgements
Use or disclosure of the information contained herein is subject to specific written approval from CIRA
THANKS FOR YOUR ATTENTION!