FATIGUE OF THICK‐SECTION COLD‐EXPANDED HOLES WITH AND WITHOUT CRACKS
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C. F.Tiffany(1977)Durability and damage tolerance assessments of United States Air Force aircraft.Fatigue Life of Structures Under Operational Loads(Edited byO.BuxbaumandD.Schuetz).Darmstadt Lab. Betriebsfestigkeit Rep. No. TR‐136 4.4/1–4.4/31.
Fairhead L. F., 1987, Current capabilities of NDT—a service operators view, Aerospace, 14, 17
E. R.Speakman(1970)Fatigue life improvement through stress coining methods.Achievement of High Fatigue Resistance in Metals and Alloys.ASTM STP No. 467 209–227.
Schrader P., 1978, Investigation into the effect of residual stresses on fatigue strength and measurement of residual stress, with special reference to aircraft construction, G. B. R. Aircr. Establ. Lib. Transl.
J.Schijve F. A.JacobsandA. E.Meulman(1978)Flight simulation fatigue tests on lugs with holes expanded according to the split‐sleeve cold work method.Netherlands Natl Lucht‐Ruimtevaartlab. Rep.No. TR 78131U.
R. G.Hocker(1982)Split sleeve cold worked holes in 7050‐T73651 aluminium plate for improved fatigue life.Northrop Corp. Aircraft Div. Rep.No. NOR 82–80.
Mann J. Y., 1984, Techniques for increasing the fatigue life of thick‐section aluminium‐alloy bolted joints, Aluminium, 60, 515
Beaver P. W., 1986, Fatigue Prevention and Design, 123
A.Brot(1984)Fatigue life evaluation program for the Kfir aircraft.Proc. 26th Israel Annual Conf. on Aviat. Astronaut. pp.36–42.
J. M.Pearson‐SmithandJ. M.Potter(1984)Effects of variations in coldworking repair procedures on flaw growth and structural life.Air Force Wright Aeronaut. Labs Flight Dyn. Lab. Tech. Rep.No. AFWAL‐TR‐82–3030.
I. J.HorsleyandC. B.Wylie(1973)Fatigue testing of pre‐cracked cold‐worked fastener holes in 7178‐T6 aluminium alloy load transfer joints.Boeing Co. Wichita Doc.No. D3–9208.
H.‐G.Koebler H.HuthandD.Schuetz(1982)Fatigue life improvement of riveted joints by cold working of precracked fastener holes.Fraunhofer‐inst. fuer Betriebsfestigkeit. Extract from unpublished LBF‐Rep. No. 3913(1979).
J. Y.Mann G. W.RevillandW. F.Lupson(1983)Improving the fatigue performance of thick aluminium alloy bolted joints by hole cold‐expansion and the use of interference‐fit steel bushes.Aeronaut. Res. Labs. Note Struct.No. 486.
M. W.OzeltonandT. G.Coyle(1986)Fatigue life improvement by cold working fastener holes in 7050 aluminium.Fatigue in Mechanically Fastened Composite and Metallic Joints(Edited byJ. M.Potter). ASTM STP No. 927 53–71.
J. Y.Mann P. W.BeaverandJ. G.Sparrow(1988)Fatigue life improvement of thick sections by hole cold expansion.Proc. 18th Congr. Aero Sci. Israel .
Mann J. Y., 1985, A case study in fatigue life extension—the main spar of RAAF Mirage III0 wings, Mech. Engng Trans. I. E. Aust., 90
Beaver P. W., 1986, Measurement and Fatigue, 491
No author. [undated] Report on part of the tests—influence of cold working on the fatigue performance under the Mirage 2000 spectrum of holes with fatigue cracks cold worked and re‐worked leaving remnant cracks or crack tips.Avions Marcel Dassault—Breguet Aviation Doc.No. 24.142.
H.Lowak(1981)Zum Einfluss von Bauteilgroesse Lastfolge und Lasthorizont auf die Schwingfestigkeitssteigerung durch mechanisch erzeugte Druckeigenspannungen. Fraunhofer‐inst. fuer Betriebsfestigkeit Ber. No. FB–157.
Mann J. Y., 1983, Stress fields associated with interference fitted and cold‐expanded holes, Metals Forum, 6, 43
Amalbert C., 1987, New Materials and Fatigue Resistant Aircraft Design, 445
P. J.Noronha S. P.Henslee D. E.Gordon Z. R.WolanskiandB. G. W.Yee(1978)Fastener hole quality.U.S. Air Force Systm. Command Air Force Flight Dyn. Lab. Tech. Rep.No. AFFDL‐TR‐78–206‐vol. 1.
J.SchijveandF. A.Jacobs(1964)Programme‐fatigue test on aluminium alloy lug specimens with slotted holes and expanded holes.Netherlands Natl Lucht‐Ruimtevaartlab. Rep.No. TN‐M.2139.
Cook R., 1985, Durability and Damage Tolerance in Aircraft Design, 631