ADYN ADVANCED EUROPEAN TILTROTOR DYNAMICS AND NOISE NUMERICAL - - PowerPoint PPT Presentation

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ADYN ADVANCED EUROPEAN TILTROTOR DYNAMICS AND NOISE NUMERICAL - - PowerPoint PPT Presentation

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ADYN ADVANCED EUROPEAN TILTROTOR DYNAMICS AND NOISE NUMERICAL WHIRL-FLUTTER INVESTIGATION OF THE EUROPEAN TILTROTOR CONCEPT: CURRENT STATUS AND FUTURE PROSPECTS Dr. Pierangelo MASARATI Dipartimento di Ingnegneria Aerospaziale Politecnico di

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ADYN

ADVANCED EUROPEAN TILTROTOR DYNAMICS AND NOISE

  • Dr. Pierangelo MASARATI

Dipartimento di Ingnegneria Aerospaziale Politecnico di Milano 30th European Rotorcraft Forum Marseille, France September 14-16, 2004

NUMERICAL WHIRL-FLUTTER INVESTIGATION OF THE EUROPEAN TILTROTOR CONCEPT: CURRENT STATUS AND FUTURE PROSPECTS

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Emanuele Bianchi Agusta (I) Anselmo Russo CIRA (I) Fritz Kießling DLR (D) Rogelio Ferrer Eurocopter (F) Oliver Dieterich Eurocopter (D)

Consortium & Acknowledgments

Mauro Frosoni IDS (I) Richard Bakker NLR (NL) Vasilis Riziotis NTUA (GR) Didier Petot ONERA (F) Massimiliano Lanz POLIMI (I)

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EUROPEAN TILTROTOR CONCEPT

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EUROPEAN TILTROTOR CONCEPT

  • Nacelle tilting interconnected
  • Outer portions of wing independently tiltable
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ADYN description

WP1 Whirl-Flutter: Requirements and Preliminary Calculations

Numerical simulation of tiltrotor whirl flutter behaviour Investigation on major design parameters Wind tunnel model requirements

WP2 Whirl-Flutter: Model Preparation and Test

Design and manufacture of a Dynamically-scaled half-span WT model Test campaign in a high speed WT Validation of computational tools with experimental database

WP3 Aeroacoustic Assessment and Optimisation

WT tests of TILTAERO’ s rotor to explore its noise characteristics Design and manufacture of a new blade with improved noise characteristics WT tests of the new blades Validation of computational tools with experimental database

WP4 High-Speed Performance Assessment

WT tests of rotors to measure and validate the performances

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ADYN description

  • Enhance the EU knowledge on tiltrotor technologies by deeply

analyzing whirl-flutter

  • Comparison of analytical and experimental results
  • Tests of a half-span scaled model in high speed wind tunnel

facilities

  • The wind tunnel model will help optimize rotor blade design for

low external noise

  • The project will provide final recommendations for the design
  • f a full-scale tiltrotor flight demonstrator (European Tiltrotor

Concept)

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WP1 Whirl Flutter Task Objectives & Organization

WP 1: Whirl Flutter: Requirements & Preliminary Calculations

T 1.1: Mathematical models ST 1.1.1: Preliminary WF and dynamic behavior prediction (C) ST 1.1.2: WT model stability and WF prediction (C) ST 1.1.3: Analysis of special aspects regarding WF (A) ST 1.1.4: WT model update and prediction of WF boundary (F) T 1.2: Establishment of model requirements & variants to TILTAERO

WP 2: Whirl Flutter Model Preparation & Test

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Software Tools

Partner Software Developed by Type CIRA CIRANO CIRA MB DLR NASTRAN + ZAERO* Commercial FEM EC HOST EUROCOPTER Comp. ECD CAMRAD II Commercial Comp./MB IDS CAMRAD JA + NASTRAN Commercial

  • Comp. + FEM

NLR Flightlab Commercial Comp./MB NTUA GAST NTUA MB ONERA HOST EUROCOPTER Comp. POLIMI DYMORE GaTech/POLIMI MB MBDyn ( + NASTRAN) POLIMI MB ( + FEM)

* Fixed wing only

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Wing Design

movable wing actuators tube supports tube/nacelle actuator nacelle tube (outboard) movable wing fixed wing tube (inboard) wing-fuselage connection

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Wind Tunnel Model: Overview

Reflection Plane DNW Closed Section Floor Model Support Structure Fairing Windmilling Rotor Dynamically Scaled Wing

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Wind Tunnel Model: Nacelle Details

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Wind Tunnel Model Support

WT closed section floor turn table wind direction

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Numerical Model of the Rotor Hub

Multiple load path Single load path beam rigid

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Excitation System

Unbalanced mass Motor 1 Motor 2 Unbalanced mass F 1 F 2 Cres

2 counterrotating motors with masses at 0 deg: beamwise excitation Mass Summary: Motor: 1.3 Kg/motor Frames (aluminum): 8.6 Kg Attachments: 1.8 Kg

  • Max. rotating

masses: 1.6 Kg/motor Total mass (max including frames): 16.6 Kg Excitation forces: Max Flap excitation @ 6 Hz 150 N/motor 300 N Max Torsion excitation @ 12 Hz 600 N/motor 360 Nm 2 motors rotating in phase with masses at 180 deg: torsion excitation

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Excitation System (Cont.)

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Analyzed Configurations

Wing Blades Hub Nacelle 1 Full-scale European Tiltrotor Concept (ETRC) 2 Mach-scale ETRC 3 Mach-scale ETRC TILTAERO 4 Mach-scale ETRC TILTAERO ADYN 5 ADYN TILTAERO ADYN ADYN (overweight)

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Whirl-Flutter Stability Results

Flight Speed - KTAS Frequency - Hz

100 200 300 400 500 10 20 30 40 50

Flight Speed - KTAS Damping

100 200 300 400 500

  • 0.2

0.2 0.4 0.6 0.8 1

Figure 1: Whirl flutter Mach scaled nacelle: critical mode: wing vertical bending (green)

Flight Speed - KTAS Frequency - Hz

100 200 300 400 500 10 20 30 40 50

Flight Speed - KTAS Damping

100 200 300 400 500

  • 0.2

0.2 0.4 0.6 0.8 1

Figure 2: Whirl flutter overweight nacelle: critical mode: wing torsion (grey)

Mach-scale: critical mode is wing beam Overweight nacelle: critical mode becomes wing torsion

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Model Design Issues

  • Nacelle/hub mass is larger than Mach-scale
  • Tailoring of the whirl-flutter mode to be wing beam
  • Tailoring of the wing beam mode damping
  • Wing will be stiffer than Mach-scale
  • Kinematic/constitutive couplings are being investigated
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Future Work

  • There are delays partially related to sibling projects
  • Whirl-flutter tests in late 2005 in DNW (Marknesse)
  • High-speed tests in early 2006 at ONERA (Modane)
  • WP1/2 (and ADYN as a whole) is expected to proceed without

further delays