Fatigue Crack Growth in 7050T7451 Aluminium Alloy Thick Section ...

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DSTO-TR-14777. BibliographyAktepe, B. and Dickinson, T., Coupon Tests to Determine the Influence of Buffet Detected at F/A-18 Wing Root. DSTO-TR-0924, Department of Defence, Defence Science and TechnologyOrganisation, 2000.Athiniotis, N., Barter, S. A. and Clark, G., Summary of Fatigue Cracking in RAAF Macchi MB326HWing Spars. ARL-MAT-TR-0747, AR-010-700, Department of Defence, Defence Science andTechnology Organisation. 1999.Athiniotis, N., Barter, S. A., Bohret, D.D., Green, A.J., Houston M.I. and Stimson, M.G., FinalReport for the Component Fatigue Test of a F/A-18 Centre Fuselage FS488 Bulkhead - FT488/2,DSTO-TR-0948, Department of Defence, Defence Science and Technology Organisation. 2003.Barter, S. A., FS488 Bulkhead Fracture Surface Preliminary Fractographic Examination, DefectAssessment and Failure Analysis Report M45/90. Department of Defence, Defence Science andTechnology Organisation. 1990a.Barter, S. A., Athiniotis, N. and Lambianidis L., Examination of the Microstructure of SeveralSamples of 7050 Aluminium Alloy. ARL-MAT-TM-403, AR-006-113, Department of Defence,Defence Science and Technology Organisation. 1990b.Barter, S. A., The use of the Conventional Optical Microscope for Quantitative FractographyMetallography and Mineralogy Conference, Institute of Metals and Materials Australasia Limited.1991.Barter, S. A., Bishop, B. and Clark, G., Defect Assessment on F/A-18 488 Bulkhead Tested at ARL.Aircraft Material Report 125, AR-006-618, Department of Defence, Defence Science andTechnology Organisation. 1991.Barter, S. A., Inspection of Cracking in the Starboard Forward Flange 6 inch Radius of FT488/2.DSTO-DDP-0191, Airframes and Engines Division, Department of Defence, Defence Science andTechnology Organisation. 1996.Barter, S. A., Fractographic Inspection of the Cracking in FT488/2 Removed at Program 79. DSTO-TN-0170. Airframes and Engines Division, Department of Defence, Defence Science andTechnology Organisation. 1998.Barter, S., Molent, L., Sharp, K. and Clark, G., Repair and Life Assessment of Critical FatigueDamaged Aluminium Alloy Structure Using a Peening Rework Method. In the proceedings of theUSAF ASIP Conference, San Antonio USA. 2000.Barter, S. A. and Price, J., Effect of Surface Preparation Treatments on Fatigue Life of 7050-Aluminium Alloy. Proceedings of the Structural Integrity and Fracture 2000 Symposium, pp140-153. 2000.34
DSTO-TR-1477Barter, S. A., Fatigue Crack Growth in 7050T7451 Aluminium Alloy Thick Section Plate with aSurface Condition Simulating Some Regions of F/A-18 Structure. DSTO-TR-1458, Department ofDefence, Defence Science and Technology Organisation. 2003.Clayton, J. Q. and Clark, G., The effect of Steel Shot and Glass Bead Peening Treatments on theFatigue Resistance of 7050-T76351 Aluminium Alloy, Proc. Aust. Ftact. Group, Fracture Mechanicsin Engineering Practice, Melbourne. pp44-51. 1988.Clark, G., Modelling Residual Stresses and Fatigue Crack Growth at Cold-Expanded FastenerHoles. Fatigue Fract. Engng Mater. Struct. Vol. 14, No. 5, pp. 379-589, 1991.Clark, G. and Clayton, J. Q., Effectiveness of Peening Treatments in Improving Fatigue Resistanceof 7050 Aluminium Alloy under Constant Amplitude and Spectrum Loading, Aust. Surface EngngConf., University of Sth. Australia, 1991.Miller, K., The Short Crack problem., Fatigue Fract. Engng Mater. Struct. Vol. 5, No. 3, pp. 223-232.1982.Molent, L., Ogden, R. and Pell, R., F/A-18 FS488 Bulkhead Fatigue Coupon Test Program. DSTO-TR-0941, Airframes and Engines Division, Department of Defence, Defence Science andTechnology Organisation. 2000.Sharp, P. K. and Clark, G., The Effects of Peening on the Fatigue Life of 7050 Aluminium Alloy.DSTO-RR-0208, AR N0. 011-795, Department of Defence, Defence Science and TechnologyOrganisation. 2001.Sharp, P. K, Byrnes, R. and Clark, G., Examination of 7050 Fatigue Crack Growth Data and itsEffect on Life Prediction. DSTO-TR-0729, AR-010-648, Department of Defence, Defence Scienceand Technology Organisation. 1998.Sharp, P. K, Clayton, J. Q. and Clark, G., The Fatigue Resistance of Peened 7050-T7451 AluminiumAlloy – Repair and Re-Treatment of Component Surface, Fatigue Fract. Eng Mater Structure. Vol17, No3, pp243-252. 1994.Simpson, D.L., Molent, L., Landry, N., Roussel, J., Graham, A.D. and Schmidt, N., “The Canadianand Australian F/A-18 International Follow-On Structural Test Project”, Proc. ICAS 2002Congress, Toronto, Canada. 2002.Wang, C. H., Barter, S. A. and Liu, Q., A Closure Model to Crack Growth Under Large-ScaleYielding and Through Residual Stress Fields. Journal of Engineering Material and Technology,Vol. 125. 2003.35
Page 3: Fatigue Crack Growth in 7050T7451 A
Page 8 and 9: DSTO-TR-1477To build the required l
Page 10 and 11: DSTO-TR-1477than internal flaws. An
Page 12 and 13: DSTO-TR-1477127mm Radius (5’)230m
Page 14: DSTO-TR-1477At the surface large gr
Page 18 and 19: DSTO-TR-1477Figure 11 The fracture
Page 20 and 21: DSTO-TR-1477A (KSIF152)B (KSIF107)F
Page 22 and 23: DSTO-TR-1477life axes. The data poi
Page 24 and 25: DSTO-TR-14774. Discussion4.1 Introd
Page 26 and 27: DSTO-TR-14774.2.2 Shape of the crac
Page 28 and 29: DSTO-TR-1477poorly defined areas on
Page 30 and 31: DSTO-TR-1477Simulated flight hours0
Page 33 and 34: DSTO-TR-1477in the appropriate regi
Page 35 and 36: DSTO-TR-1477390MPa(higherslope)420M
Page 37 and 38: DSTO-TR-1477Table 9Specimen No.A co
Page 39: DSTO-TR-1477considerable concern to
Page 43 and 44: DSTO-TR-1477126.5 41102 0.1638 0.25
Page 45 and 46: DSTO-TR-1477248.5 80743 0.1195 0.12
Page 47 and 48: DSTO-TR-147730.5 9910.1 0.0713 0.10
Page 49 and 50: DSTO-TR-1477104.5 33954 0.0733 0.08
Page 51 and 52: DSTO-TR-147743.5 14134 0.042 0.0468
Page 53 and 54: DSTO-TR-147716.5 5523.6 0.0406 0.05
Page 55 and 56: DSTO-TR-147718.5 6011 0.0264 0.0452
Page 57 and 58: DSTO-TR-147723.5 7635.6 0.0481 0.08
Page 59 and 60: DSTO-TR-1477Table A-13. Results of
Page 61 and 62: DSTO-TR-1477Table A-16. Results of
Page 63 and 64: DISTRIBUTION LISTFatigue Crack Grow
Page 65: Page classification: UNCLASSIFIEDDE

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