References
1. Shanyavskiy A.A. Tolerance fatigue failures of aircraft components.
Synergetics in engineering applications. Monografy, Ufa, 2003.
2. Shanyavskiy A.A., Orlov E.F., Koronov M.Z. Fractographic analyses of
fatigue crack growth in D16T alloy subjected to biaxial cyclic loads at
various R-ratios // Fatigue & Fracture of Engineering Materials &
Structures, 1995, Vol. 18, No. 11, pp. 1263-1276 DOI:
10.1111/j.1460-2695.1995.tb00853.x
3. Shanyavskiy A.A. Development of semi-elliptical fatigue cracks in AK6
aluminum alloy under biaxial loading // Fatigue & Fracture of
Engineering Materials & Structures, 1996, Vol. 19, No. 12, pp.
1445-1458 DOI: 10.1111/j.1460-2695.1996.tb00180.x
4. Sonsino C.M. Fatigue testing under variable amplitude loading // Int.
J. Fatigue, 2007, Vol. 23, No. 6, pp. 1080-1089.
5. Sonsino C.M. Effects on lifetime under spectrum loading / Proceedings
of the International Conference on “Material and Component Performance
under Variable Amplitude Loading – VAL2”, March, 23-26, 2009, Germany,
Vol. I, (Eds C.M. Sonsino and P.C. McKeighan), 2009, pp. 93-118.
6. Stark P., Walther F., Eifler D. Fatigue life estimation of metallic
materials under constant amplitude and standardised service loading /
Proceedings of the International Conference on “Material and Component
Performance under Variable Amplitude Loading – VAL2”, March, 23-26,
2009, Germany, Vol. II, (Eds C.M. Sonsino and P.C. McKeighan), 2009, pp.
903-912.
7. Aldroe H., Tougui A., Poirier. F., Lacroix F., Venugopal B., Mani
J.A., Ranghantan N. Marker-bands techniques in fatigue / Proceedings of
the International Conference on “Material and Component Performance
under Variable Amplitude Loading – VAL2”, March, 23-26, 2009, Germany,
Vol. II, (Eds C.M. Sonsino and P.C. McKeighan), 2009, pp. 967-976.
8. Winter G., Kobert H., Tan W., Eichiseder W. Research of variable
loading cases during thermomechanical fatigue (TMF) investigations and
consideration in the lifetime calculation / Proceedings of the
International Conference on “Material and Component Performance under
Variable Amplitude Loading – VAL2”, March, 23-26, 2009, Germany, Vol.
I, (Eds C.M. Sonsino and P.C. McKeighan), 2009, pp. 517-526.
9. Sonsino, C.M., Heim, R., Melz, T. Lightweight-structural durability
design by consideration of variable amplitude loading // International
Journal of Fatigue, 2016, 91, pp. 328-336.
10. Shanyavskiy A., Banov M. Acoustic emission methods for lifetime
estimations in aircraft structures // Theoretical and Applied Fracture
Mechanics, 2020, 102719. doi:10.1016/j.tafmec.2020.102719
11. Gallagher J.P., Giessler F.J., Berens A.P., Engle R.M., Jr. USAF
Damage Tolerant Design Handbook: Guidelines for the Analysis and Design
of Damage Tolerant Aircraft Structures, AFWAL-TR-82-3073, USAF Flight
Dynamics Laboratory. Wright-Patterson AFB, Ohio, 1984.
12. Krasnowski B.R., Reddy D.J., Franada B.G., Reid L., Restis J.
Fatigue Strength and Damage Tolerance of Thin-Walled Riveted Structures
with Cold-Worked Holes. American Helicopter Society 56th Forum, Virginia
Beach, Florida, May 2000.
13. Goodlin D.L. Airframe inspection reliability and capability
assessment program. Final Project Report 17-3836 for SA-ALC/LDN (1994)
14. Roach, D.: Recent Damage Tolerance and Inspection Tests to
Demonstrate the Robust Performance of Composite Doubler Aircraft
Repairs. NASA/DOD/FAA Conference on Aging Aircraft, September 2001.
15. Mitchell M.R. Fundamental of Modern Fatigue Analysis for Design. ASM
Handbook, Fatigue & Fracture, 19 (1996), pp. 227-249.
16. Metals Handbook. Vol. 9. Fractography and Atlas of Fractographs.
ASM, Metals Park, Ohio, 1982.
17. Newman J.C., Jr. Plasticity effects on fatigue-crack growth under
variable amplitude and spectrum loading / Proceedings of the
International Conference on “Material and Component Performance under
Variable Amplitude Loading – VAL2”, March, 23-26, 2009, Germany, Vol.
II, (Eds C.M. Sonsino and P.C. McKeighan), 2009, pp. 19-33.
Figure Captions
Fig. 1. The fractured bracket (inside the circle) on the RRJ-95 aircraft
(No. 89051) (a) and fracture surfaces by the four lug sections (b).
Fig. 2. Microstructure of investigated aluminum alloys: 1933T3 (a) and
1163 (b).
Fig. 3. The crack (inside the circle) propagated to the face plane of
the stiffened panel from under the middle bracket of the engine pylon
mount in the RRJ-95 aircraft (No. 95075) and the scheme of the airframe
with the area of bracket position (view A).
Fig. 4. Initial fracture zones in bracket lug sections No. 1 (a), 2 (b),
3 (c), and 4 (d) of the engine pylon mount in the RRJ-95 aircraft (No.
95075) with origins indicated by the arrows.
Fig. 5. The blocks of MBM (a) and fatigue striations (b) on the fracture
surfaces No. 1 and No. 4 of the RRJ-95 aircraft (No. 89051) lug,
respectively.
Fig. 6. The plot of the MBM spacing “h ” (lug section No. 1) and
the fatigue striation spacing “δ” (lug sections No. 2-4) versus the
crack length “a ” of the RRJ-95 aircraft (No. 89051).
Fig. 7. The plot of crack growth duration in terms of the number of
blocks “n f” (lug section No. 1) and the number
of unit cycles “N f” (lug sections No. 2-4)
versus the crack length “a ” of the RRJ-95 aircraft (No. 89051).
Fig. 8. The fracture surfaces No. 1-4 in the RRJ-95 aircraft (No. 95075)
wing panel.
Fig. 9. The fatigue MBM blocks on the fracture surfaces No. 2 (a) and
No. 3 (b) at different crack length for the RRJ-95 aircraft (No. 95075).
Fig. 10. The plot of the MBM spacing “h ” and the number of
blocks “n f” versus the crack length
“a ” for fracture surfaces No. 2 (a) and No. 4(b) of the RRJ-95
aircraft (No. 95075).
Fig. 11. The program of bench-test loading along the OY (a) and OZ (b)
axes for the lower panel of the RRJ-95 aircraft (No. 4862) wing
reproducing single schematized flight loading cycle.
Fig. 12. Fracture surfaces in the lower panel of the RRJ-95 aircraft
(No. 4862) wing.
Fig. 13. The MBM reflecting the block loading of the lower panel of the
RRJ-95 aircraft (No. 4862) wing in accordance with the schematized
flight cycle (a), and the plot of the MBM spacing “h ” and the
number of blocks “n f” versus the crack length
“a ” in the panel (b).
Corresponding author : 106otdel@mail.ru