The Role of the European Research Establishments in AWIATOR on examples from fligth test measurements technologies

Transcription

1 Fifth Community Aeronautical Days 2006 Vienna, Austria 19 th 21 st June 2006 The Role of the European Research Establishments in AWIATOR on examples from fligth test measurements technologies Eric COUSTOLS, Jean-Joël COSTES (ONERA) Anton de BRUIN (NLR) Werner DOBRZYNSKI, Thomas GERZ (DLR)

2 AWIATOR Work breakdown and Partnership 4 Work Packages with 9 linked technical tasks in an integrated approach 23 partners in the project plus several sub-contractors (12) 12 Industry: Airbus SAS, Airbus Deutschland, Airbus-France, Airbus-United Kingdom, ALENIA, EADS Military, IAI, INASCO, GKN, SENER, SONACA, SPASA 7 Research Establishments: DLR, NLR, ONERA, CERFACS, CNRS-IRPHE, EADS-CRC Munich, IST 4 Universities: FLM Munich, NTUA Athens, TUB Berlin, UCL Louvain 7 Contractors: 4 Major Airframe Manufacturers plus 3 Aeronautical Research Establishments 16 Assistant Contractors plus 12 sub-contractors Viewgraph 2 Viewgraph 2

3 AWIATOR Work breakdown and Partnership Beyond leading three Technical Tasks (T1.1, T1.3 & T2.2) the 7 Research Establishments are present in all 9 Tasks Important Involvement of the 3 REC Contractors Viewgraph 3 Viewgraph 3

4 Task 1.1: Vortex Control Devices (led by NLR) Subtask 1.1.1: Design and Manufacture DLR / ONERA: Load distributions and computations of near-wake flow selection of concepts (wing-mounted devices, spoiler, spanwise wing loading, differential flap settings) for Wake Vortex minimisation Subtask 1.1.2: Towing Tank, Wind Tunnel and Catapult Tests DLR / ONERA: Investigations of such concepts in W/T and at Catapult. Development of new PIV traverse system (laser, mirror & cameras). Viewgraph 4 Viewgraph 4

5 Task 1.1: Vortex Control Devices (led by NLR) Subtask 1.1.3: Fligth Tests DLR / ONERA: Ground-based Lidar measurements at Tarbes airfield (closely neighboured CW and remote pulsed Lidars) plus atmospheric measurements Strategy of LIDAR measurements at Tarbes Airbus' A340 with 2 smoke trails L1: pulsed lidar, DLR L2: cw lidar, DLR L3: cw lidar, ONERA L3 L2 L m Strong influence of atmospheric turbulence on vortex decay Planned A340 WV characterisation by airborne Doppler lidar (late 2006) Viewgraph 5 Viewgraph 5

6 Task 1.1: Vortex Control Devices (led by NLR) Subtask 1.1.3: Fligth Tests NLR: Wake flow visualisation with NLR's Cessna Citation a/c Airbus' A340 with 2 smoke trails Reconstructed smoke traces from video Viewgraph 6 Viewgraph 6

7 Task 1.3: Low Noise Assessment and Operations (led by DLR) Subtask 1.3.1: Devices Design and Low Noise Procedures Selection DLR / ONERA: Source noise check-out in DLR s Aeroacoustic Wind Tunnel Subtask 1.3.2: Wind Tunnel and Simulator Studies DLR / NLR / ONERA: Quantification of wing concepts/devices source noise characteristics Tests in DNW-LLF W/T: Source localisation and far-field directivity Farfield microphone traverse (20 Miks) Farfield measurements: ± 5 m Radius 7.3 m Microphone array (140 Miks) DLR: Assessment of low noise procedures feasibility and safety based on data from simulator study (e.g. configuration speed and time, effect of wind speed, parameters affecting passenger comfort, etc.) Viewgraph Viewgraph 7 7

8 Task 1.3: Low Noise Assessment and Operations (led by DLR) Subtask 1.3.3: Flight Tests (Noise tests and Procedures tests) DLR / ONERA: Quantification & ranking of noise characteristics for selected AWIATOR devices by means of microphone array meas. DLR: Evaluation of flight performance data for selected procedures Flyover test set-up at Tarbes airport: Total of 208 ground based microphones ONERA: 32 m cross-array for low frequencies (96 microphones) DLR: 4 m multi-arm spiral array for high frequencies (112 microphones) Frequency: 1250 Hz Viewgraph 8 Viewgraph 8

9 Task 2.1: Large Winglets (led by Airbus) Subtasks 2.1.2, & 2.1.4: Ground & flight tests plus assessment DLR / ONERA: Prediction of the aeroelastic behaviour of the wing equipped with Standard and Large Winglet; Derivation of wing shapes for various flight conditions; Analysis of Large Winglet Performances NLR: Prediction of wing deformation and of load distribution Mesh deformations Comparison: Standard to large winglet Flutter Tip Current Winglet Current Winglet (Ref. (ref. Only) only) Tip Cord 0,75m Tip Chord 0.75m Large Winglet Span 3.73m Large Winglet Span 3,73m Viewgraph 9 Viewgraph 9

10 Task 2.1: Large Winglets (led by Airbus) Subtasks 2.1.2, & 2.1.4: Ground & flight tests plus assessment DLR / ONERA: Prediction of the aeroelastic behaviour of the wing equipped with Standard and Large Winglet; Derivation of wing shapes for various flight conditions; Analysis of Large Winglet Performances NLR: Prediction of wing deformation and of load distribution Mesh deformations inboard Good comparisons between CFD and flight tests median outboard Viewgraph 10 Viewgraph 10

11 Task 2.2: Wing Measurements (led by ONERA) Task 2.2: Specifications, Laboratory & Flight tests, Prediction & Analysis DLR / ONERA: Specification, validation (via Lab tests) & integration onto the flight test aircraft of novel wing measurement techniques. Measurement Requirements Flight shape of the wing Aerodynamic pressure distribution Unsteady Pressures on TEDs Winglet flight shape Gap between the wing and flap Air flow around wing Wing Loads / bending Measurement Techniques Photogrammetry, Inclinometer Pressure belt Kulite Strain Pattern Analysis, Photogrammetry Edge Detection Technique Flow cone Strain Gauge Viewgraph 11 Viewgraph 11

12 Task 2.2: Wing Measurements (led by ONERA) Task 2.2: Specifications, Laboratory & Flight tests, Prediction & Analysis DLR: Inclinometer method applied for 1 st Flight Tests Campaign only Aim: Measurement of the wing shape in flight, including wing twist. 8 cm Sensor Winglet rotation / X axis via inclinometer at Winglet root 13 inclinometers (7 for bending, 6 for torsion) Measurement of the deformation of the chord Reference sensors Viewgraph 12 Viewgraph 12

13 Task 2.2: Wing Measurements (led by ONERA) Task 2.2: Specifications, Laboratory & Flight tests, Prediction & Analysis ONERA: Strain Pattern Analysis "SPA" Method Aim: Winglet Twist measurement based on strain gauge network. 1 2 Strain gauges arrangement (Right large winglet only) Torsion bridge Bending bridge Viewgraph 13 Viewgraph 13

14 Task 2.2: Wing Measurements (led by ONERA) Task 2.2: Specifications, Laboratory & Flight tests, Prediction & Analysis DLR: Edge Detection Technique Method Aim: Optical measurement of the gap between wing and flap. - Mono-camera system (F/T-1) - Relative gap width vs. ground reference - Stereo-camera system (F/T-2) Images of the EDT cameras Camera 4 A 340 Windows Camera 4 Camera 3 Camera 2 Camera Video Cameras Viewgraph Installed in the fuselage Viewgraph

15 Task 3.4: Flow Control Elements (led by Airbus) Task 3.4: Requirement, Design, Laboratory & Flight Tests, Exploitation ONERA: Demonstration that using SBVGs (Sub Boundary-Layer Vortex Generators) will improve the efficiency of standard high lift system. Investigation of Reynolds effect at the ONERA F1 Wind Tunnel with w/o SBVG SBVG ONERA F1 W/T Pi=3bar Re c = SBVGs location Flow Flow SBVGs Viewgraph Viewgraph 15 15

16 Task 3.4: Flow Control Elements (led by Airbus) Task 3.4: Requirement, Design, Laboratory & Flight Tests, Exploitation ONERA: Demonstration that using SBVGs (Sub Boundary-Layer Vortex Generators) will improve the efficiency of standard high lift system. Computation SBVG effect using elsa code (Lab/Flight tests conditions) µ t /µ 4000 µ t /µ w/o SBVGs with SBVGs separation F1 Wind Tunnel Tests CFD Viewgraph 16 Viewgraph 16

17 Conclusions on the role of the European Research Establishments in AWIATOR Existing relationships between REC and Aircraft Industry have been reinforced in the framework of AWIATOR REC offered to the partnership their validated expertise w.r.t. Laboratory tests: wind tunnel and free-flight facilities, microphone array, simulator... Airfield tests: weather forecasting, ground based- plus inboard- Lidar measurements, microphone array... Computation methods: Euler, (U)RANS, LES, Modelling, Vortex-type methods, Wing deformation, aero-elasticity methods... Novel alternative methods (versus standard ones proposed by Airbus Flight Test Department) for specific wing and winglet measurements REC have had a unique integrated opportunity to gain knowledge from Aircraft Industry by preparing and analysing Flight Tests REC are volunteered to reiterate such collaborative partnership in the framework of future EU projects Viewgraph 17 Viewgraph 17

18 Thank you for your attention... Many thanks to my four co-authors plus Jean-Luc Hantrais-Gervois, Joël Reneaux (ONERA) Florent Laporte, Geza Schrauf & Keith Bohannon (Airbus)... and Jens Koenig AWIATOR Manager (Airbus) Viewgraph 18 Viewgraph 18

19 Task 1.1: Vortex Control Devices (leaded by NLR) Subtask 1.1.1: Design and Manufacture DLR / ONERA: Load distributions and computations of near-wake flow selection of concepts (wing-mounted devices, spoiler, spanwise wing loading, differential flap settings) for Wake Vortex minimisation Subtask 1.1.2: Towing Tank, Wind Tunnel and Catapult Tests DLR / ONERA: Investigations of such concepts in W/T and at Catapult. Development of new PIV traverse system (laser, mirror & cameras). Vorticity field Z C Velocity Baseline Baseline Concept DLR device1 Airbus-D device Concept V/U 0 Viewgraph Viewgraph 19 19