GARTEUR LIMITED GARTEUR TP SAAB TECHNICAL EPORT FKH R-4109
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2 GARTEUR LIMITED GARTEUR TP SAAB TECHNICAL EPORT FKH R-4109 GARTEUR - STRUCTURES AND MATEMALS - AG 16 DAMAGE PROPAGATION IN COMPOSITE STRUCTURAL ELEMENTS FINAL REPORT PART 2 - COWONS To Ireman (Saab) R. Olsson (FFA) E. Greenhalgh (DM) Re Sharp (BAe) S. Maison (Aerospatiale) P. Perugini (CIRA) Y. Ousset (ONERA) F. Roudolff (ONERA) M. Gadke (DLR) H. Baudisch (Dornier)
3 GARTEUR LIMITED GARTEUR TP Distribution GARTEUR ExecutiTve Committee IGA J. ChCret Dr. R. Haupt ONERA, DLWD-I B.P. 72, D KBln F Chiitillon CEDEX Germany France Prof.ir. J. W. SloofY NLR P.O. Box BM Amsterdm The Netherlands Mi-. G. Moreno Labata INTA Carretera de Ajalvir Km. 4 E Torrei6n de Ardoz (Madrid1 Spain Mi-. A, Gustafsson FFA Box S Broma Sweden Dr. G.T. Coleman Chief Scientist (Air Systems) DERA Fmborough Fmboroureh. Hwshire GU14 OLX ENGLAND Members of the Group of Responsables - Structures and Materials Dr. G. Bartelds NLR P.O. Box AD Emeloord The Netherlands IGA P. Costa Head of Materials hpt. ONERA BP 72 F ChPtillon CEDEX France Mi-. H. Price Dr. Rohwer Struct. Engineering Dept. DLR NRO International Aerospace Inst. fiir Struktmechanik Woodford Postfach Cheshire SK7 1 QR Braunschweif: England Germany
4 GARTEUR LINITED GARTEUR TP Dr. R. Ohayon ONERA BP 72 F Chiitillon CEDEX France Prof. P. Curtis DRA Farnborough Structural Materials Centre Fmborough. Hants GU14 6TD England Dr. A. Blom WA P.O. Box Broma Sweden Dr. ing. J. Biihlmeier Dairnler Benz Aerospace AG Dornier Luftfahrt GmbH Regio-Prop-FlugzeugeLERV Wessling Gemmy Mr. C. Cornuault Dassault Aviation CEDEX Saint-Cloud CEDEX France Mr. A. Tropis Akrospatiale Aircraft Division A/BTE/EG/ST 3 16 Route de Bayonne Toulouse CEDEX 03 France Dip1.-Ing. H. Schnell Daimler Benz Aerospace Airbus GmbH Bremen Germany Mr. F. Beuskens NIVR Kluyverweg HD Delft The Netherlands Mr. H. Ansell Saab m F m S Link6wing Sweden Mr. E. van Teeseling Fokker Services S PO. Box ZJ Schi~hol-Oost The Netherlands Members of the Action Group DLR-BE: Attn. Mr. R. H. Aoki P.O. Box D Stuttg-art Gemany CIRA Attn. Mr. P. Perugini Via Maiorise Capua (CEl Italy
5 FKH R GARTEUR LMTED GARTEUR TP DLR-SM Attn. Dr. M. Gadke P.O. Box 3267 Gemany Saab AB FKH-TI Attn. Mr. T. Ireman Sweden Eurocopter Deutschland Attn, Mr. R. Biibl P.O. Box D Miinchen Germany WA Attn. Mr. R. Olsson Attn. Dr. L. Asp P.O. Box S Bromma Sweden DB-Ae/Airbus Attn. DR. D. Hachenberg P.0. Box D Hamburg Germany BAe (Mil. Aircraft Div.) Attn. Mr. R. Sahrp Warton Aerodrome Preston, Lancashire PR 1 AX England AerospatialelI>ept. Materials DM (MS3B) Attn. Mr. M. S. Maison Attn. Mr. E. Greenhalgh Attn. Mr. ID. Guedra-Degeorges Fmborouzh. Hants GU14 6TD 12 Rue Pasterur England F Suresnes CEDEX France NLR ONERA (OWCE) Mtn. DR. J.F.M. Wiggenraad Attn. Mr. M.Y. Ousset P.O. Box 153 Attn. Ms. F. Roudolff 8300 AD Emmeloord BP 72 The Netherlands F Chiitillon CEDE)(: France Secretary GARTEUR Mr. K.A. Jonasson WA Box S Bromma Sweden I;his report will be downgraded from 'GARTEU LIMITED' to 'GARTEUR OPEN' simulataneously with GARTEUR TP-091 (but not before July ofthe year 2000).
6 GARTEUR LIMITED GARTEUR TP SUMMARY This report is part 2 of the final report of AG-16 "Damage propagation in composite structural elements". Part 1 forms the executive summary. Part 2 presents the work of the "COUPONS" group: research applying fracture mechanics delamination buckling, delamination growth andl or residual strength of flat plate configurations. Part 3 presents the work of the "STRUCTUES" group: research aimed at obtaining insight into the failure process of larger "structural" components through careful experimentation, leading to the development of test methods, design methods and design guidelines, The work within the "COUPONS" group was concentrated on determination of delamination fracture data and delamination growth criteria. The applicability of the methods and data were demonstrated with delamination growth experiments carried out at the coupon level e.g. delamination buckling tests. Compression tests with laminates containing impact damages and open holes were also performed as well as impact and indentation tests. The delamination fracture tests comprised: DCB, ENF, MMB, CLS and SEN tests. The experiments were analysed using various methods and energy release rate, stress based failure criteria and damage models were evaluated. In this report, the results from the work within the "COUPONS" group are summarized. It includes a large amount of delamination fracture toughness data for various material systems and ply intesfaces for mode I, mode 11 and different mixed mode ratios. Dynamic delamination fracture data and fatigue delamination growth data have also been determined for some materials and ply interfaces. Fractography has been used extensively by DRA to determine the relationship between surface features such as cups angle and mixed mode ratio. Simulations of the delamination growth in laminates with embedded artificial delaminations have be performed by FFA and Saab using both a special purpose platelshell algorithm including successive remeshing, and the explicit dynamic FE-code LS-DYNA3D. These analyses show that it is possible to simulate the delamination growth in the tests considered with both methods. This is, however, only a first step towards an application of fracture mechanics on a structural level and the prediction of failure of impacted structures. Further development is needed and an Exploratory Group EG-24 has already been established to formulate a follow-on Action Group to develop "Design methodology for damage tolerant composite wing panels".
7 FKH R GARTEUR LUVImD GARTEUR TP TABLE OF CONTENTS... 1 INTRODUCTION Objectives FFA objectives 6 DRA objectives... 6 BAe objectives ' Saab objectrves... 6 DLR objectives... 6 Aerospatiale objectives... 7 ONERA objectives... 7 CIRA objectives... 7 Dornier objectives Work elements EXPERIMENTS Basic delmination fracture testing FFA tests DRA tests BAe and Saab tests DLR tests ONERA tests Buckling induced delamination tests FFA tests Saab tests DRA tests Domier tests Impact and indentation tests Impact tests Aerospatiale tests CllU tests Indentation tests Tests with laminates containing open holes and impact damages... 24
8 FKH R GARTEUR LIMITED GARTEUR TP ANALYSES -26 Analyses of the delamination fracture tests Analyses of DCB tests FFA analyses ONERA analyses SEN tests CLS tests...*...* Analyses of BID tests Analyses of BID plate tests FFA analyses Saab analyses DRA analyses Dornier analyses Analyses of BID beam tests Analyses of tests with laminates containing impact damages and open holes30 Global -local FE-analyses Analytical methods Energy equivalence criterion Semi-empirical residual strength criterion for the equivalent hole Analyses of impact and indentation tests EXPERIMENTAL RESULTS Delamination fracture tests FFA tests DCB. ENF and MMB tests Dynamic delamination SEN tests B Ae-Saab tests Quasi static DCB tests Quasi static ENF tests Cyclic DCB tests Cyclic ENF tests DRA tests ONERA CLS tests DLR tests Static ENF and MMB tests S.2 Cyclic ENF tests... 60
9 FKH R GARTEUR LMITED GARTEUR TP Cyclic MMB tests...*..**..*..*...* BID tests BID plate tests FFA-tests Saab tests DM tests Dornier tests BID beam tests (FFA) Impact and indentation tests Aerospatiale tests CIRA tests Tests with laminates containing open holes and impact damages ANALYSIS RESmTS Results from analyses of delamination fracture tets FFA DCB and SEN analysis results ONERA DCB analyses CLS analysis results Results from BID plate analyses FFA Saab analyses Analyses of the WA test (bench mark example)...., Analyses of Saab tests DM analyses Results from BID beam analyses Results from analyses of laminates with holes and impact damages Global analysis of a laminate with an impact damage represented as a single dela~nation Local analysis of laminate with impact damage Results from analyses of indentation tests CONCLUDING EMARKS
10 FKH R GARTEUR LIMITED GARTEUR TP DRA Conclusions...*..*......*.* Delamination fracture tests BID plates FFA conclusions Delamination fracture tests BID beams and plates BAe conclusions ONERA conclusions CIRA conclusions Saab conclusions Delamination fracture tests BID plate tests BID plate analyses Aerospatiale conclusions DLR conclu~ions...,., APPENDIX A: FFA Theory APPENDIX B: ONERA Theory APPENDIX C: CIRA Theory APPENDIX D: Illustrations to FFA results APPENDIX E: Illustrations to DRA results APPENDIX F: Illustrations to SAAB results APPENDIX 6: Illus~ations to CIRA results APPENDIX H: Illustrations to BAe results APPENDIX I: Illustrations to ONERA results APPENDIX J: Ulustrations to DLR results APPENDICES
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