Research Establishments Activities within SFWA-ITD Innovation takes off E. COUSTOLS (ONERA) , U. HERRMANN (DLR), C. NAE (INCAS) and J. KOS (NLR) SFWA-ITD Consortium Confidential • DLR, INCAS, NLR and ONERA were selected by the SFWA- ITD leaders in a 1 st Phase after the “Associate Partners Worskhop” held by AIRBUS @ Toulouse (October 11 th , 2006): – DLR – INCAS Cluster: INCAS, ROMAERO, STRAERO & AVIOANE CRAIOVA – NL Cluster: Fokker Aerostructures, NLR, Fokker Elmo, TU Delft, Univ. Twente and 4 SME's. – ONERA – QinetiQ – RUAG • In a 2 nd Phase (late 2008/beg. 2009): – AERNNOVA CS Closing Event 22/03/17, Brussels 2 SFWA-ITD Partnership DLR/INCAS/NLR/ONERA Associate Partners (1/3)
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Research Establishments
Activities within SFWA-ITD
Innovation takes off
E. COUSTOLS (ONERA) , U. HERRMANN (DLR),
C. NAE (INCAS) and J. KOS (NLR)
SFWA-ITD Consortium Confidential
• DLR, INCAS, NLR and ONERA were selected by the SFWA-
ITD leaders in a 1st Phase after the “Associate Partners
Worskhop” held by AIRBUS @ Toulouse (October 11th, 2006):– DLR
SFWA-ITD PartnershipIllustration of DLR/INCAS/NLR/ONERA Cooperation
CS Closing Event 22/03/17, Brussels 5
• Numerical Assessment of CROR configurations– Performance & noise predictions + analysis of installation effects
ONERA
ONERA S1MA WT
DNW-LLF WT
SFWA-ITD Consortium Confidential
SFWA-ITD PartnershipIllustration of DLR Achievement: Infra-Red
CS Closing Event 22/03/17, Brussels 6
Year Description
2014 Camera moved from fusel. to FIN:
- Small view angle (< 20o) AND
- Distance to target area (> 36m)
Ground tests in Toulouse & Berlin
Wind Tunnel testing (Fin vibr.)
pre flight testing on A340
2015 Soft- & hardware development
2016 Surface coating influence on IR-
measurements
In-flight camera calibration procedure
Soft- & hardware delivered for BLADE
Flight Test
BLADE Flight Test
SFWA-ITD Consortium Confidential
SFWA-ITD PartnershipIllustration of DLR Achievement: Hot-Films
CS Closing Event 22/03/17, Brussels 7
BLADE Flight TestMeasuring Transition via hot-film sensor at the wing leading edgeSensors installed in a curved surface, no stepsFast response, remote sensor (75kHz, 50m)Tested, delivered & installed for Flight Test
SFWA-ITD Consortium Confidential
SFWA-ITD PartnershipIllustration of INCAS Achievement
CS Closing Event 22/03/17, Brussels 8
Flow ControlLOSPA, Hardware Manufacturing
BizJet-U-Tail HTP
interaction
SHIELD,
Ground Based
Demonstrator
SFWA-ITD Consortium Confidential
SFWA-ITD PartnershipIllustration of NLR Achievement in ‟Smart flap”
Description of Work DLR INCAS NLR ONERA1.1.1 Passive Tech. for Laminar Flow X X1.1.2 Active Tech. for Lam. Flow & Buffet Control X X X X1.1.3 Surface Tech: New Painted Riblet X X1.1.4 Flow Control for Low Speed / High Lift X X X X1.3.1 Adv. Control Sys. Options for A/C Appl. & Int. X X1.3.2 Adv. Communication Network & field buses X1.3.3 Power Network and Management X1.3.5 Ground Demonstration X X1.3.6 Loads & Inertial Sensing Technologies X1.3.7 Aerodynamic Sensing Technologies X X X1.3.8 Fluidic Actuators X X X1.3.9 Mechanical Actuators X X2.1.1 Application of SFWA Technologies X2.1.2 Struct. & Syst.: Concepts, Capab. & Int. X X2.1.3 Numerical Simulations & Ground Testing X X X X
Description of Work DLR INCAS NLR ONERA1.2.1 Innovative Devices for Load Control X X1.2.2 Adaptive Wing X1.2.3 Advanced Load Control Technologies X X X1.2.4 A/C Load Evaluation & Optimisation X X X1.3.1 Adv. Control Sys. Options for A/C Appl. & Int. X X1.3.2 Adv. Communication Network & field buses X1.3.3 Power Network and Management X1.3.5 Ground Demonstration X X1.3.6 Loads & Inertial Sensing Technologies X1.3.7 Aerodynamic Sensing Technologies X X X1.3.8 Fluidic Actuators X X X1.3.9 Mechanical Actuators X X2.2.1 Investigate Innovative After Body X2.2.2 CROR Innovative Power Plant Integration X X X X2.2.3 Innovative After Bodies Detailed Design X X2.2.4 Detailed Simulation and Ground Testing X X X X3.2.2 Novel Flap System X3.2.4 Load & vibration control - Fatigue testing X
3.5.2Manu. of realistic aft bodyshape for Bizjets to
support testing X
3.5.5Demonstration of design of new afterbodies wrt
thermal & vibration loads from engine jet X
3.5.7Demonstration of aeroelastic stability of new