Numerical simulation of maneuvering combat aircraft


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1 Numerical simulation of maneuvering combat aircraft Andreas Schütte DLR  German Aerospace Center Institute of Aerodynamics and Flow Technology Oct. 14 th 2005, Stuttgart Folie 1 > HLRS 2005 > A. Schütte
2 Numerical simulation of maneuvering combat aircraft Gunnar Einarsson, Britta Schöning, Axel Raichle, Wulf Mönnich, Thomas Alrutz, Jens Neumann, Jörg Heinecke DLR  German Aerospace Center Institute of Aerodynamics and Flow Technology Oct. 14 th 2005, Stuttgart Folie 2 > HLRS 2005 > A. Schütte
3 Overview Motivation Objectives Simulation Environment Experimental Simulation Numerical Results HPC Requirements and Resources Summary and Outlook Folie 3 > HLRS 2005 > A. Schütte
4 HPC Requirements Institut of Aerodynamics and Flow Technology Braunschweig /Göttingen Folie 4 > HLRS 2005 > A. Schütte
5 Motivation Source: Cenaero Folie 5 > HLRS 2005 > A. Schütte
6 Objectives of the DLR Project SikMa Prediction of the unsteady behavior of maneuvering aircraft. Development of a numerical simulation environment for calculating maneuvers of a free flying elastic combat aircraft. Realized a by multi disciplinary timeaccurate coupling of CFD, Structure Dynamics and Flight Mechanics within the framework TENT. SikMa is a multidisciplinary project were several DLR Institutes are involved: Institute of Aerodynamics and Flow Technology Institute of Aeroelasticity Institute of Flight Systems DLR Sistec Folie 6 > HLRS 2005 > A. Schütte
7 Simulation Environment TENT Codes are implemented in TENT via wrappers. TENT carries out data transfers and communication between codes. TENT can distribute applications over different platforms SimBrowser: Definition of grid hierarchies for CHIMERA grids definition of all movements of parts and grids relative to each other animation and test of movements creation of motion and hierarchy files for the CFD CodeTAU Folie 7 > HLRS 2005 > A. Schütte
8 DLR TAUCode CFDCode solution of RANS equations for arbitrarily moving bodies on unstructured meshes hybrid meshes (hex., prisms, tetra., pyram.) FV using dual grid approach, MG accelerated unsteady via dual time stepping stateoftheart turbulence models grid adaptation (refinement & derefinement) CHIMERA technique deforming mesh capability designed for massively parallel computers validated for a large number of test cases Folie 8 > HLRS 2005 > A. Schütte
9 DLR TAUCode Chimera approach Chimera boundary of the flap Chimera boundary of the wing Realized soon: Automatic holecutting approach Folie 9 > HLRS 2005 > A. Schütte
10 DLR TAUCode Mesh adaptation (unsteady calc.) Stream lines & Total pressure distribution History of mesh adaptation Folie 10 > HLRS 2005 > A. Schütte
11 SIMULA Flight mechanics library Simulation environment SIMULA delivers the solutions of the flight mechanics equations Trimming calculation Analyze stability Maneuver simulations with 6 DoF and control devices Coupling of Aerodynamics/Flight mechanics Implicit time integration scheme Close coupling within each pseudo timestep Implemented models for SikMa Rolling deltawing with trailingedge flaps Generic 6DoF model (e.g. X31) Folie 11 > HLRS 2005 > A. Schütte
12 CSMCode Structural mechanics simulation Two approaches Discrete approach: Coupling with the overall FEModel Modal approach: Coupling with characteristic Eigenmodes Characteristics Coupling Aerodynamics/Structure: Loose/weak coupling scheme coupling within each physical time step Solving the CSMequations: Implicit Newmark integrationscheme Spatial coupling: Scattered data interpolation methods for force and deformation transfer Coupling in time: Conventional Serial Staggeredalgorithm with predictor /corrector step for the CSM calculation Determination of the system matrices: Reduced system matrices MAA and KAA imported from NASTRAN Folie 12 > HLRS 2005 > A. Schütte
13 Experimental Simulation Wind tunnel experiments Objectives Generating a validation data base for the numerical simulation. Knowledge approach of the aerodynamic behavior of configurations with vortex dominated flow fields Configurations 1. Deltawingconfiguration with movable trailingedge flaps 2. X31 CFRP and RemoteControlModel with remote controlled flaps, rudder and canard for maneuver simulations on the ModelPositioningMechanism (MPM) at NWB Folie 13 > HLRS 2005 > A. Schütte
14 Experimental Simulation Wind tunnel facilities Transonic Wind Tunnel Göttingen (TWG) Test section 1x1m Mach number range: (with perf. walls) Re = (based on 0.1 s) Low Speed Wind Tunnel Braunschweig (NWB) Test section m Mach number range: (for open test section) Re = 1.8 x 106 (based on 0.1 s) Folie 14 > HLRS 2005 > A. Schütte
15 Experimental Simulation Wind tunnel models Deltawingconfiguration with trailingedge flaps Internal 6component piezobalance Piezoresistive pressure sensors at 60% and 80% chord length Control device velocity up to 300 /s X31 configuration with remote controlled control devices CFRP fuselage, steel wing and aluminum made control devices 8 internal servo engines for control device movement Internal 6component strain gauge Pressure sensors for measuring the unsteady pressure distribution at 60% and 70% chord length Internal 64 channel 16 bit telemetric system for data transfer Folie 15 > HLRS 2005 > A. Schütte
16 MPM  Model Positioning Mechanism Maneuver simulation in the wind tunnel Synchronized, dynamic similar movement of model and control devices in comparison to flight tests Parallel kinematics Steward platform connected to electromagnetic linear motors by 6 rods of constant length Folie 16 > HLRS 2005 > A. Schütte
17 Folie 17 > HLRS 2005 > A. Schütte
18 Numerical Results Guided coupled simulation of CFD and CSM Coupled freetoroll maneuver simulation of CFD, CSM and Flight Mechanics Coupled freetoroll maneuver of deltawingconfiguration with movable trailingedge flaps (CFDFMCoupling) X31: first steady calculations Folie 18 > HLRS 2005 > A. Schütte
19 Numerical Results (1) Delta wing guided rolling motion around longitudinal axis CSMTAUCoupling FEModel of deltawing and rear sting support Folie 19 > HLRS 2005 > A. Schütte
20 Numerical Results (1) Delta wing guided rolling motion around longitudinal axis CSMTAUCoupling Folie 20 > HLRS 2005 > A. Schütte
21 Numerical Results (2) Delta wing guided rolling motion around longitudinal axis CSMTAUFMCoupling Folie 21 > HLRS 2005 > A. Schütte
22 Numerical Results (3) Delta wing freetoroll motion around longitudinal axis TAUFMCoupling Ma = 0.5 Re = 3.8Mio Θ = 17 Φ 0 = 0 η = ±5 Folie 22 > HLRS 2005 > A. Schütte
23 Numerical Results (3) Delta wing freetoroll motion around longitudinal axis TAUFMCoupling Folie 23 > HLRS 2005 > A. Schütte
24 Numerical Results (3) Delta wing freetoroll motion around longitudinal axis TAUFMCoupling Flap up Flap down cl OΦ O Folie 24 > HLRS 2005 > A. Schütte
25 Numerical Results (4) Flow simulation around X31 configuration (clean wing) α=14 α=18 α=22 Folie 25 > HLRS 2005 > A. Schütte
26 Numerical Results (4) Flow topology of X31 (clean wing) Oil Flow Picture TauCalculation Ma=0.12 Re=1.0Mio a=18 separation line attachement line Folie 26 > HLRS 2005 > A. Schütte
27 Numerical Results (4) Flow simulation around X31 configuration PSPMeasurement: Re = 2.07Mio α =18 TAUCalculation: Re = 2.07Mio α =18 Folie 27 > HLRS 2005 > A. Schütte
28 HPC Requirements and Resources (1) Calculation times and resources today Folie 28 > HLRS 2005 > A. Schütte
29 HPC Requirements and Resources (2) Requirements on HPC ClusterHardware Maneuver Simulation X31 configuration, movable control devices ~30 Million grid points unsteady simulation with DLRTAUCode CFD / CSD / FM Maneuver simulation of 2 seconds real time Aim: 2 weeks Approximation on target platform HWWCluster Strider (64 Proc, 64 Bit): 30 Mio. grid points 2 s real time, 2000 physical time steps, 600 inner Iterations ~ 950 h wall clock ~ 40 days on HWWCluster Strider (64 Proz) ~ 14 days on Cluster with > 256 Processors Herbstmaneuver: 10 s Folie 29 > HLRS 2005 > A. Schütte
30 Summary Development strategy for the prediction of the behavior of maneuvering aircraft Simulation environment and its elements Experimental simulation for validation data base First results showing the capability of timeaccurate coupling of CFD/FM and CFD/CSD/FMCoupling First CFD results of the complex flow topology over the X31 configuration Need for HPC resources were demanded Folie 30 > HLRS 2005 > A. Schütte
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