Buckling & Post-buckling Behavior Of Thin Composite Panels
CSIRCSIR-NALBuckling & Post-buckling Behavior ofThin Composite PanelsAshwin Rai, S Nadeem Masood, S R Viswamurthy,Saurabh Chandrakar, Arun Kumar Singh,Kodukula Swapna & Kotresh M GaddikeriAdvanced Composites DivisionNational Aerospace LaboratoriesCouncil of Scientific & Industrial ResearchBangalore, IndiaAerospaceElectronicsand Systems DivisionInternational r15-18, DublinInternationalDigitalImage CorrelationConference &&Workshop,September15-18, DublinCSIR-National Aerospace Laboratories, India
About NAL-CSIRCSIRCSIR-NALEstablished in 1959 CSIR-NAL mandate DevelopAerospace Technologies with Strong ScienceContent Support all National Aerospace Programmes Design and Build Small and Medium–sized Civil Aircrafts HANSA: 2 seat, all-composite, trainer aircraftSARAS: Multi-role, light transport aircraft (14 seat)CNM-5: Five seat general aviation aircraftAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
About Advanced Composites Division (ACD)CSIRCSIR-NALAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
Composites usage in AircraftsCSIRCSIR-NALSource: Teal Group, Boeing, Airbus, Composite Market ReportsAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
Buckling as a Design LimitationCSIRCSIR-NALSkin stiffener construction commonlyfound in aircraft structuresFuture Design ScenarioCurrent Design ScenarioLoadFinal collapseFinal collapseUltimateLoad (UL)Improvement in structuralefficiencyUnused reservedstrength of panelUltimateLoad (UL)First Buckling Load 150% LL and aboveFirst Buckling LoadLimitLoad (LL)LimitLoad (LL)End ShorteningEnd ShorteningAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
Compression Testing of Large Composite PanelsCSIRCSIR-NALTestSimulationsLanzi & Giavotto, 2006Aerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
Compression Testing of Large Composite PanelsCSIRCSIR-NALPevzner et al., 2008Aerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
Composite Test PanelCSIRCSIR-NAL130mm130mm130mmLayup Sequence for skin: [ 45/-45/0/90]s(t 1.52 mm)Layup Sequence for stringers : [ 45/-45/0/0/ 45/-45/0/90]s (t 3.04 mm)800 mmStringer height, h 20mmPrepreg Material :Hexply M21/34%/UD194/IMA-12K/300mmStringers450 mmAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
Post-Buckling Test SetupCSIRCSIR-NALPanel stringer side instrumented withlinear SGs & SG Rosettes 17 locations on skin 18 SGs on stringer web One SG on stringer flangePanel skin side is speckled for DICAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
Post-Buckling Test SetupCSIRCSIR-NALAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
Post-Buckling TestCSIRCSIR-NALAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
DIC Set upCSIRCSIR-NAL3D DIC measurements using Vic-Snap AOI: 680 x 450mm (full exposed panel) Camera: PointGrey 5MP Grasshopper 15 fpsfirewire: 2 nos. Lenses: Schneider 17mm Image acquired every 2 sec Calibration grid: 12x9 grid with 35mm spacing Subset size: 55 by 55 Pixels UTM loading rate: 0.12 mm/min Aerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
Vertical Displacement ContoursComparison Test and SimulationsCSIR-NALEnd Shortening 0.35mmAerospace Electronics and Systems DivisionLoad 41.35kNInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, IndiaCSIR
Vertical Displacement ContoursComparison Test and SimulationsCSIR-NALNear Horizontal BandsImply Uniform LoadingEnd Shortening 0.65mmAerospace Electronics and Systems DivisionLoad 76.98kNInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, IndiaCSIR
Load vs End-shorteningCSIRCSIR-NAL160TestLocal Skin BucklingLoad 94.66kNES 0.82 mm140Load (kN)120100SimulationsLocal Skin BucklingLoad 93.20 kNES 0.84 mm806040Numerical Simulation20Test 17000.511.5End Shortening (mm)Aerospace Electronics and Systems Division2International Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India2.5
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 0 kNLOAD (Test) 0 kNEND SHORTENING 0 mmFE AnalysisTest – DIC Measurements
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 22.22 kNLOAD (Test) 24.42 kNEND SHORTENING 0.2 mmFE AnalysisTest – DIC Measurements
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 49.94 kNLOAD (Test) 53.10 kNEND SHORTENING 0.45 mmFE AnalysisTest – DIC Measurements
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 77.61 kNLOAD (Test) 82.33 kNEND SHORTENING 0.7 mmFE AnalysisTest – DIC Measurements
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 103.77 kNLOAD (Test) 107.25 kNEND SHORTENING 0.95 mmFE AnalysisTest – DIC Measurements
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 124.68 kNLOAD (Test) 128.73 kNEND SHORTENING 1.2 mmFE AnalysisTest – DIC Measurements
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 144.04 kNLOAD (Test) 139.71 kNEND SHORTENING 1.45 mmFE AnalysisTest – DIC Measurements
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 154.33 kNLOAD (Test) 143.56 kNEND SHORTENING 1.7 mmFE AnalysisTest – DIC Measurements
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 152.26 kNLOAD (Test) 144.37 kNEND SHORTENING 1.95 mmFE AnalysisTest – DIC Measurements
OUT OF PLANE DISPLACEMENT ‘W’LOAD (FE) 152.60 kNLOAD (Test) 144.16 kNEND SHORTENING 2.20 mmBuckling Load (FE) 93.20 kNBuckling Load (Test) 94.66 kNFE AnalysisTest – DIC Measurements
Strain MeasurementsCSIRCSIR-NAL20001000Load 2000-3000S4 '0' Deg RSGS4 '0' Deg DIC-4000-50001000Load (kN)0Microstrains020406080-1000-2000-3000-4000S13 RSGS13 DIC-5000Aerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
SummaryCSIRCSIR-NAL DIC is used to capture buckling and post-buckling behavior oflarge composite panel subjected to compressive loads DIC is ideal for capturing buckling modes & resulting out-ofplane displacements Provides very useful insight in the transition regime from localskin buckling to global buckling of panel DIC provides information on the uniformity of load distribution Number of strain gages reduced drastically Next, we plan to use DIC to study stiffener deformation deep inthe post-buckling regimeAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
ReferencesCSIRCSIR-NAL1.Lanzi & Giavotto, Composite Structures, Vol.73, 2006, pp.208-220.2.Zimmermann, Klein & Kling, Composite Structures, Vol.73, 2006, pp.150-161.3.Degenhardt, Kling, Klein, Hillger, Goetting, Zimmermann & Rohwer, InternationalJournal of Structural Stability & Dynamics, Vol.7, No.2, 2007, pp.337-358.4.Pevzner, Abramovich & Weller, Composite Structures, Vol.83, 2008, pp.341-353.5.Ghilai, Feldman & David, International Journal of Structural Stability & Dynamics,Vol.10, No.4, 2010, pp.917-926.Aerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
AcknowledgmentsCSIRCSIR-NALM/s PyrodynamicsM/s Correlated SolutionsDirector, NALHead, Advanced Composites DivisionAeronautics Research & Development Board, IndiaAerospace Electronics and Systems DivisionInternational Digital Image Correlation Conference & Workshop, September 15-18, DublinCSIR-National Aerospace Laboratories, India
DIC is used to capture buckling and post-buckling behavior of large composite panel subjected to compressive loads DIC is ideal for capturing buckling modes & resulting out-of-plane displacements Provides very useful insight in the transition regime from local skin buckling to global buckling of panel
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numerical post-buckling critical load is more conservative than that obtained in physical tests [4,5,6].Typical load-shorting of stiffened structure undergoing buckling and post-buckling response are shown in Figure 3 where corresponding simplifications have been overlaid indicating the k1 pre-buckling, k2 post-buckling, k3 collapse
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post-buckling conditions. The results without considering any kind of imperfection, are closed and in good agreement with the tests in terms of buckling and post-buckling stiffness, as well as of collapse loads. Jiang et al. [13] studied the buckling of panels subjected to compressive stress using the differential quardrature element method.
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The aim of this work is to present and discuss the results of an ongoing numerical investigation on the buckling, post-buckling, collapse and DSM design of two-span lipped channel beams.The numerical results presented were obtained through (i) GBT buckling analyses and (ii) elastic and elastic-plastic shell finite element (SFE) post-
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