[1] Reddy, J. N. An Introduction To the Finite Element Method. Tata McGraw Hill Publishing Company, third ed. , 2005.
[2] Suzuki, Shin-Ichi. Some stress measurements in wing structures using a photoelastic method. International Journal of Mechanical Sciences, 5(6):475 – 485, 1963.
[۳] رشیدی, احسان و فاضل زاده حقیقی, سیداحمد. بررسی اثر مدل بارگذاری آئروالاستیک و زاویه عقبگرد بر سرعت و فرکانس فلاتر بال
هواپیما. در شانزدهمین کنفرانس سالانه مهندسی مکانیک. دانشکده فنی مهندسی دانشگاه شهید باهنر, 1387.
[4] Guo, S., Morishima, R., Zhang, X., and Mills, A. Cutout shape and reinforcement design for composite c-section beams under shear load. Composite Structures, 88(2):179 – 187, 2009.
[5] Gomez, Sanya Maria and Mathai, Alice. Numerical analysis of carbon fibre reinforced aircraft wing. International Journal of Earth Sciences and Engineering, 4(6):648–651, October 2011.
[6] Kennedy, Graeme and Martins, Joaquim. A Comparison of Metallic and Composite Aircraft Wings Using Aerostructural Design Optimization.
[7] Muchchandi, Vinod S. and Pilli, S. C. Design and analysis of a spar beam for the vertical tail of a transport aircraft. International Journal of Innovative Research in Science, Engineering and Technology, 2(7):3341–3347, July 2013.
[8] Mazidi, A., Kalantari, H., and Fazelzadeh, S.A. Aeroelastic response of an aircraft wing with mounted engine subjected to time-dependent thrust. Journal of Fluids and Structures, 39:292 – 305, 2013.
[9] Skorupa, A., Skorupa, M., Machniewicz, T., and Korbel, A. Fatigue crack location and fatigue life for riveted lap joints in aircraft fuselage. International Journal of Fatigue, 58:209 – 217, 2014. Fatigue Crack Paths 2012.
[10] Chitte, Pritish, Jadhav, P. K., and Bansode, S. S. Statistic and dynamic analysis of typical wing structure of aircraft using nastran. International Journal of Application or Innovation in Engineering & Management (IJAIEM), 2(7):321–326, July 2013.
[11] Harakare, Poonam and Heblikar, V. K. Evaluation of static and buckling load carrying capability of the wing box through fem approach. International Journal of Current Engineering and Technology, pp. 6–9, September 2013.
[12] Kumar, A. R., Balakrishnan, S. R., and Balaji, S. Design of an aircraft wing structure for static analysis and fatigue life prediction. International Journal of Engineering Research & Technology, 2:1154–1158, 2013.
[13] Chowdhury, Nabil M., Chiu, Wing Kong, Wang, John, and Chang, Paul. Experimental and finite element studies of bolted, bonded and hybrid step lap joints of thick carbon fibre/epoxy panels used in aircraft structures. Composites Part B: Engineering, 100:68 – 77, 2016.
[14] Ebadi, A. and Selahi, Ehsan. Fatigue life assessment of composite airplane wing subjected to variable mechanical and thermal loads. Journal of Aerospace Science and Technology, 11(2):1–11, 2017.
[15] https://www.makeitfrom.com/material properties/7075- T6-Aluminum.
[16] Stochastic model for estimation of probability-confidence bounded a-n curves (experimental and applied mechanics).
[۱۷] مهدیزاده, امیرحسین, مشایخی, محمد, و کدخدایی, محمود. تخمین عمر خستگی پرچرخه با رهیافت مدل آسیب شابوش- لمتر. روش‌های عددی در مهندسی, 35(1):27--41, 1395.
)
