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

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Intelligence ProgramDGSTA Defence Intelligence Organisation 1Manager, Information Centre, Defence Intelligence Organisation 1CanadaDTA 1NRC – D Simpson 1Bombardier – Y Richard 1SPARES 5Total number of copies: 34
Page classification: UNCLASSIFIEDDEFENCE SCIENCE AND TECHNOLOGY ORGANISATIONDOCUMENT CONTROL DATA1. PRIVACY MARKING/CAVEAT (OF DOCUMENT)2. TITLEFatigue Crack Growth in 7050T7451 Aluminium Alloy Thick SectionPlate with a Glass Bead Peened Surface Simulating Some Regions ofthe F/A-18 Structure4. AUTHOR(S)S. A. Barter3. SECURITY CLASSIFICATION (FOR UNCLASSIFIED REPORTSTHAT ARE LIMITED RELEASE USE (L) NEXT TO DOCUMENTCLASSIFICATION)DocumentTitleAbstract5. CORPORATE AUTHOR(U)(U)(U)Platforms Sciences Laboratory506 Lorimer StFishermans Bend Victoria 3207 Australia6a. DSTO NUMBERDSTO-TR-14776b. AR NUMBERAR-012-8566c. TYPE OF REPORTTechnical Report7. DOCUMENT DATEAugust 20038. FILE NUMBER2003/36886/19. TASK NUMBERAIR0014110. TASK SPONSORASI11. NO. OF PAGES5612. NO. OF REFERENCES2213. URL on the World Wide Web14. RELEASE AUTHORITYhttp://www.dsto.defence.gov.au/corporate/reports/DSTO-TR-1477.pdfChief, Air Vehicles Division15. SECONDARY RELEASE STATEMENT OF THIS DOCUMENTApproved for public releaseOVERSEAS ENQUIRIES OUTSIDE STATED LIMITATIONS SHOULD BE REFERRED THROUGH DOCUMENT EXCHANGE, PO BOX 1500, EDINBURGH, SA 511116. DELIBERATE ANNOUNCEMENTNo Limitations17. CITATION IN OTHER DOCUMENTS Yes18. DEFTEST DESCRIPTORSF/A-18 Aircraft, Aluminium Alloy, Shot Peening, Cracking, Fatigue19. ABSTRACTThis report presents the results of a fatigue coupon test program whose primary purpose was to obtain resultsfrom coupons treated with a glass bead peened surfaces typical of some regions of critical F/A-18 aircraftstructure. A spectrum representative of RAAF’s F/A-18 fleet fatigue usage was used. The coupons wererepresentative of the material and geometry of a structural detail that has been found to be fatigue-critical inthe 7050T7451 high strength aluminium alloy wing carry through bulkheads. Following the tests, quantitativefractography was used to produce crack growth curves for each of the fatigued specimens. This reportdescribes the surface condition being examined, test spectrum, test methods, test results and examines ways ofinterpreting the crack growth curves to establish a measure of the severity of the flaws from which the fatiguecracks initiated.Page classification: UNCLASSIFIED
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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 and 40: DSTO-TR-1477considerable concern to
Page 41 and 42: DSTO-TR-1477Barter, S. A., Fatigue
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: DISTRIBUTION LISTFatigue Crack Grow
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