Morphing high lift structures: Smart leading edge device and smart single slotted flap Hans Peter Monner, Johannes Riemenschneider Madrid, 30 th
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1 Morphing high lift structures: Smart leading edge device and smart single slotted flap Hans Peter Monner, Johannes Riemenschneider Madrid, 30 th March 2011
2 Outline Background Project overview Selected results WP1 Integration WP2 Smart Leading Edge (SLE) WP3 Smart Single Slotted Flap (SSSF) WP4 Wind Tunnel Test
3 Project data of SADE (Smart High Lift Devices for Next Generation Wings) Call: Partners: FP7-AAT-2007-RTD-1 13 from 8 countries Starting date: Ending date: Duration: Total cost: EU contribution: Website: Coordinator: EC Officer: 48 months , 717 PM , 515 PM Dr. Hans Peter Monner Pablo Perez-Illana
4 Outline Background Project overview Selected results WP1 Integration WP2 Smart Leading Edge (SLE) WP3 Smart Single Slotted Flap (SSSF) WP4 Wind Tunnel Test
5 Smart high lift components in SADE Smart Leading Edge (SLE) Smart Leading Edge (SLE) Slot- and gapless droop nose Enables laminar flow Reduce acoustic emissions Produce as much lift as possible! Smart Single Slotted Flap (SSSF) Smart Single Slotted Flap Variable chamber trailing edge Reduce system complexity and weight Recover as much lift as possible!
6 Main work steps / Roadmap Initialisation of a common data base. Calculating of the aerodynamic target shapes Component development, manufacturing and testing Detailed structural design of both targeted smart high lift devices. Design of a wind tunnel test bed. Multidisciplinary analysis of smart high lift devices. Manufacture and assembly of test bed and smart high lift devices Static and dynamic tests with the wind tunnel functional model. Wind tunnel tests at TsAGI 101.
7 Outline Background Project overview Selected results WP1 Integration WP2 Smart Leading Edge (SLE) WP3 Smart Single Slotted Flap (SSSF) WP4 Wind Tunnel Test
8 Outline Background Project overview Selected results WP1 Integration WP2 Smart Leading Edge (SLE) WP3 Smart Single Slotted Flap (SSSF) WP4 Wind Tunnel Test
9 WP1 Integration - TUDelft Objectives: Database with references and background knowledge such as smart structures concepts from previous projects. Pre design model including systems model for fast technology during design of smart components in WP2 and WP3. Virtual development platform to enable collaborative multidisciplinary design and analysis. Aeroelastic investigations on the smart configurations regarding aeroelastic servo effects as well as aeroelastic stability. Pre design of new aircraft configurations using morphing high lift devices and comparison of performance with conventional configurations for technology evaluation. The main objective of WP1 is the development of a roadmap for morphing wing technologies towards full scale experimental flight.
10 CFD-CSM Coupling: Schematic View (SFR) Preprocessing CSM surface displacements Mesh Coupling On-line viewing B Deformation and Stress Solver Inner loop (Newton) Outer loop Increments Mesh deformation CFD mesh CFD solver (Edge) Preprocessor Solver CFD surface displacements Result Analysis CFD pressures Mesh Coupling CSM forces
11 Outline Background Project overview Selected results WP1 Integration WP2 Smart Leading Edge (SLE) WP3 Smart Single Slotted Flap (SSSF) WP4 Wind Tunnel Test
12 WP2 Smart Leading Edge (SLE) - EADS Objectives: Development and selection morphing concepts for the SLE based on combination and adaptation of elementary concepts. Aerodynamic calculation of target shapes for take-off and landing of both configurations: FNG and HARLS. Detailed design and sizing of the SLE for the FNG wing including structures and drive systems. Adaptation of smart concept to the HARLS wing and resizing. Identification of dominant design parameters for optimization in full configuration (in WP1). Smart Leading Edge (SLE) The main objective of WP2 is the detailed design of the SLE component for FNG and HARLS wings.
13 Droop Nose Parameterization (DLR) Front spar is 19% (analogous to FNG) 3 Leading Edge Parameters for Deformation of Initial Input Geometry (Droop, Nose Factor, Asymmetry Factor) X-displacement is coupled to the remaining Factors
14 FNG + HARLS Target Shapes Droop Nose Shape (DLR) Much lower droop for both take off and landing Separation on the flap for low AoA Smaller resemblance between landing and take off shape compared to the FNG case
15 Process chain for parametric structural design of the SLE concept (DLR) Pre-Design of Skin and Kinematics Detailed Design 3D FE model ux+uy+uz Aerod. Target Shape P D parametric FE, Optimal Support Pos P z in m Initial Skin Design KAP1 KAP2 KAP3 KAP y in m Kinematical Path, Strains, Deformations, Stresses Feedback data for other disciplines Optimization of the Design of Omega- Stringers wrt. stability and strength requirements Optimization of layer stacking sequence/ laminate layup wrt. target shape, stability and strength req.
16 Manufactured Skin (DLR)
17 Kinematics for droop nose (EADS) Principle design: rotational (electric) actuator with excentric kinematic to drive pivoted main lever - minimal loads on actuator shaft - provides high stiffness / accuracy - modular design 0 Position 18 Position 20-20
18 Manufactured kinematics (EADS)
19 Outline Background Project overview Selected results WP1 Integration WP2 Smart Leading Edge (SLE) WP3 Smart Single Slotted Flap (SSSF) WP4 Wind Tunnel Test
20 WP3 Smart Single Slotted Flap (SSSF) - DLR Objectives: Development and selection morphing concepts for the SSSF based on combination and adaptation of elementary concepts. Aerodynamic calculation of target shapes for take-off and landing of both configurations: FNG and HARLS. Detailed design and sizing of the SSSF for the FNG wing including structures and drive systems. Adaptation of smart concept to the HARLS wing and resizing. Identification of dominant design parameters for optimisation in full configuration (in WP1). Smart Single Slotted Flap (SSSF) The main objective of WP3 is the detailed design of the SSSF component for FNG and HARLS wings.
21 Target Shapes for the SSSF (CIRA) Optimization of SSSF shape Genetic Algorithm used in conjunction with an in-house geometry manipulator 8 Generations 12 Individuals 80% crossover bit rate 1.5% mutation rate Parameters Gap and overlap Flap trailing edge deflection Flap angle deflection Angle of attack
22 Study for the SSSF (CU) Design & Simulation Objectives: Modeling of the skin connections to represent a real practical design Ensure that the stress values in the skin are within the allowable limits An FE model of the trailing edge structure in neutral position with the curved beam was created Rod type connections (cross sectional area 28 mm 2 ) were set between the beam and the upper and lower skin to allow load transfer and keep the distance between the skins The structure was subjected only to aerodynamic pressure load
23 Outline Background Project overview Selected results WP1 Integration WP2 Smart Leading Edge (SLE) WP3 Smart Single Slotted Flap (SSSF) WP4 Wind Tunnel Test
24 WP4 Wind Tunnel Test - TsAGI Objectives: Pre design of the wind tunnel experiment and general planning inclusive aerodynamic calculations to obtain best model dimensions and calculate loads for structural design. Hardware tests for complementary studies. Design and manufacturing of the wind tunnel model based on WP2 and WP3 components and pre design results. Perform test programme to evaluate performance of smart component. The main objective of WP4 is the test of a 1:1 smart component in TsAGI s large scale wind tunnel T101.
25 Wind tunnel and model dimensions end plates TE passive LE active Wing box 3m 2m LE active 5m WT-101 characteristics: Flow speed: V=5 50m/sec Nozzle form: Ellipse S=264m 2, 14x24m Length of the working section: L=24m
26 Instrumentation of WT model (TsAGI, Piaggio, DLR, EADS) Pressure distribution tubes Strain gages cables Pressure probes sections 3 sections with 84 holes 3 sections with 13 strain gauges
27 Thank you for your attention!
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