ORIGINAL_ARTICLE
Fatigue Life Assessment of Composite Airplane Wing Subjected to Variable Mechanical and Thermal Loads
The purpose of this paper is to estimate the fatigue life of an airplane wing with laminated composite skin, subjected to variable mechanical and thermal loads. To achieve this aim,at first, the three-dimensional model of airplane wing was drawn in CATIA software. Then, by transferring the model to the ABAQUS software, the finite element model of the wing wascreated. Here, the spars and ribs weremade ofaluminum T7075 and skin waslaminated composite with uni-directional and woven roving carbon epoxy layers. The convergence behavior of the structure wasexamined for selecting an appreciate element numbers. Finally, transient dynamic analysis followed by fatigue analysis of the wing structure was carried out. By performing fatigue simulation, the number of loading cycles resulted in failure of the structural components and wing skin panel was predicted. By comparing the simulation results with experimental research carried out by other researchers, the validity of the presented simulation method was demonstrated. The results of this research indicated that the replacement of traditional metallic wing skin with laminated composite skin causes a significant increase in fatigue life of the wing,besides a considerable weight reduction.
https://jast.ias.ir/article_81507_e2e15e71442669db3b5cb9e8c1ecf7f6.pdf
2017-10-01
1
11
Airplane wing
Composite skin
Fatigue life
Mechanical and thermal loads
Finite element method
A.
Ebadi
1
Department of Mechanical Engineering, Marvdasht Branch, Islamic Azad University
AUTHOR
Ehsan
Selahi
selahi@miau.ac.ir
2
Department of Mechanical Engineering, Marvdasht Branch, Islamic Azad University, Marvdasht, Iran
AUTHOR
ORIGINAL_ARTICLE
A Parametric Study for Vibration Analysis of Composite Cylindrical Shell Resting under Elastic Foundation: Analytical and Numerical Methods
The aim of this study is to investigatethe effective parameters on vibrations of circular cylindrical shells with fixed rotary speed andresting elastic foundation by means of analytical and finite element numerical simulation. First, the governing equations are derived using the theory of Donnell, considering the centrifugal forces,Coriolis acceleration, and the initial annular tension. Then, the analytical solution for cylindrical shells isintroduced under simply supported conditions. Further, the effect of parameters such as therotational speed of the shell, its lay-up, fiber angle, and the stiffness of the elastic foundation on the values of natural frequency and the critical velocity of the shells are studied. The analytical solution results are in good compatibility with the results achieved from the finite element method.
https://jast.ias.ir/article_81508_d2d33f98a42186b4d8ece70f3e5094f1.pdf
2017-10-01
13
22
Vibration Analysis
Annular cylindrical shells
Donnel theory
Analytical Solution
Finite Element
M.
Noorabadi
1
Composite Materials & Technology Center, Malek-e-Ashtar University of Technology
AUTHOR
N.
Namdaran
2
Composite Materials & Technology Center, Malek-e-Ashtar University of Technology
AUTHOR
M.
Rahnama
3
Composite Materials & Technology Center, Malek-e-Ashtar University of Technology
AUTHOR
Jafar
Eskandari Jam
4
Composite Materials & Technology Center, Malek-e-Ashtar University of Technology
AUTHOR
[1] Egle, D.M., Sewall, J.L., “An Analysis of the Free Vibration of Orthogonally sti. Enedcylindrical Shells with sti. Eners Treated as Discrete Elements”, AIAA Journal, Vol. 3, 1968, pp. 518- 26.
1
[2] Rinehart, S.A. and Wang, J.T.S., “Vibration of Simply Supported Cylindrical Shells with Longitudinal Stiffeners,” Journal of Sound and Vibration, Vol. 24, No. 2, 1972, pp.151-163
2
[3] Amabili, M., “Nonlinear Vibrations of Circular Cylindrical Shells with Different Boundary Conditions,” AIAA Journal, Vol. 41, No. 6, 2003, pp. 1119-1130
3
[4] Karagiozisa, K.N., Amabili, M., Padoussisa, M.P., and Misra, A.K., “Nonlinear Vibrations of Fluid-Filled Clamped Circular Cylindrical Shells,” Journal of Fluids and Structures, Vol. 21, 2005, pp. 579–595.
4
[5] Pellicano, F., , “Linear and Nonlinear Vibrations of Shells,” 2nd International Conference on Nonlinear Normal Modes and Localization in Vibrating Systems,” Samos, June 19-23, 2006.
5
[6] Shao, Z.S., and Ma, G.W., “Series Expansion Method Free Vibration Analysis of Laminated Cylindrical Shells by Using Fourier, Journal of Thermoplastic Composite Materials, Vol. 20, No. 551, 2007
6
[7] Eipakchi, H.R., Rahimi, G.H., Esmaeilzadeh Khadem, S., ,“Closed form Solution for Displacements of Thick Cylindrs With Varying Thickness Subjected to Non-Uniform Internal Pressure”, J. Struc. Eng. and Mech., Vol. 16, No. 6, 2003, pp. 731-748.
7
[8] Zhao, X., Liew, K.M., Ng, T.Y., “Vibration of Rotating Cross-Ply Laminated Circular Cylindrical Shells with Stringer and Ring Stiffeners”, Int. Journal of Solids and Structures, Vol. 39, 2002, pp. 529-545.
8
[9] Jafari, A.A., and Bagheri, M., “Free Vibration of Rotating Ring Stiffened Cylindrical Shells with Non-Uniform Stiffener Distribution,” J Sound Vib, Vol. 296, 2006, pp. 353-376.
9
[10] M.J. Ebrahimi, M.M., “Najafizadeh, Free Vibration Analysis of Two-Dimensional Functionally Graded Cylindrical Shells”, Applied Mathematical Modelling, Vol. 38, pp. 308–324.
10
ORIGINAL_ARTICLE
Adaptive Quaternion Attitude Control of Aerodynamic Flight Control Vehicles
Conventional quaternion based methods have been extensively employed for spacecraft attitude control where the aerodynamic forces can be neglected. In the presence of aerodynamic forces, the flight attitude control is more complicated due to aerodynamic moments and inertia uncertainties. In this paper, a robust nero-adaptive quaternion controller based on back-stepping technique for vehicle with aerodynamic actuators is proposed. The presented control lawconsists of a neural network based adaptive part and an additional term which ensures the robustness of the system. Actually, the first term is designed to approximate and cancel out the matched uncertainties and the second term is used toensure the robustness of system against approximation error of the neural network.The Lyapunov direct method is applied to derive the learning laws for the neural network weights and adaptive gain. Also,theultimately boundedness of the error signals is guaranteed based on theLyapunov’s stability criterion. The benefit of the presented method is evaluated through simulation of an aerodynamic control vehicle.
https://jast.ias.ir/article_81553_aa24748bae2fc28d31bd2d3a44e42aee.pdf
2017-10-01
23
32
Nero adaptive control
Quaternion attitude control
Aerodynamic control
S.
M. Hoseini
sm_hoseini@iust.ac.ir
1
Department of Electrical Engineering, Malek-e Ashtar University of Technology
AUTHOR
Crouch, P., Spacecraft attitude control and stabilization: Applications of geometric control theory torigid body models, IEEE Transactions on Automatic Control, vol.29, no.4, 1984, pp.321-331.
1
[2] Singh, S.N. and Iyer, A., Nonlinear decoupling sliding mode control and attitude control of spacecraft, IEEE Transactions on Aerospace and Electronic Systems, vol.25, no.5, pp.621-633, 1989.
2
[3]Wei B. and Barba,P. M., Quaternion Feedback for Spacecraft Large Angle Maneuvers, J.Guid. Contr. Dynam.,vol. 8, no. 3, 1985, pp. 360-365.
3
[4]Wallsgrove, R.J. and Akella, M.R., Globally stabilizing saturated attitude control in the presence ofbounded unknown disturbances, Journal of Guidance, Control and Dynamics, vol.28, no.5, 2005, pp.957-963.
4
[5] Cai, W.C., Liao, X.H. and Song, Y.D., Indirect robust adaptive fault-tolerant control for attitudetracking of spacecraft, Journal of Guidance, Control and Dynamics, vol.31, no.5, 2008, pp.1465-1463.
5
[6] Seo, D. and Akella, M.R., Separation property for the rigid-body attitude tracking control problem, Journal of Guidance, Control and Dynamics, vol.30, no.6, 2007, pp.1569-1576.
6
[7] Song, Y.D. and Cai, W.C., Quaternion observer-based model-independent tracking control of spacecraft, Journal of Guidance, Control and Dynamics, vol. 32, no.5, 2009, pp.1476-1482.
7
[8] Park, Y., Inverse optimal and robust nonlinear attitude control of rigidspacecraft, Aerospace Science and Technology, 2012. http://dx.doi.org/ 10.1016/j.ast.2012.11.006.
8
[9] Su, Y. and Zheng, C., Simplenonlinear proportional-derivative control for globalfinite- time stabilization of spacecraft, Journal of Guidance, Control and Dynamics, vol. 38, no.1, 2015
9
[10]Juang, J.C., Jan, Y.W. and Lin, C.T., quaternion feedback attitude control design, A nonlinear H∞ approach, Asian Journal of Control, vol. 5, no. 3, pp. 406-411, 2003.
10
[11]Kristiansen, R., Nicklasson, P.J. and Gravdahl J.T., Satellite attitude control by quaternion-based back stepping, IEEE Trans. Control Systems Technology, vol. 17, no. 1, 2009, pp. 277-283.
11
[12]Zou, A.M., Kumar, K. D. and Hou, Z. G., Quaternion-based adaptive output feedback attitude control of spacecraft using Chebyshev neural networks, IEEE Trans. Neural Networks, vol.21, no. 9, pp.1457-1462, 2010.
12
[13] Alipour, M.R., FaniSaberi, F. and Kabganian, M., Modelling, design andexperimental implementation of non-linear attitude tracking with disturbance compensation using adaptive-sliding control based on quaternion algebra, The Aeronautical Journal, vol. 122, 2018, pp. 148-171,.
13
[14] Ma, Y. Jiang, B., Tao, G. and Cheng, Y., Actuator failure compensation and attitude control for rigid satellite by adaptive control using quaternion feedback, Journal of Francklin Institude, vol. 351, 2014, pp.296-314.
14
[15] Song, C., Kim, S.J. and Kim, S.H., Robust control of the missile attitude based on quaternion feedback, Control Engineering Practice, vol. 14, 2006, pp. 811–818.
15
[16] Xia, Y., Lu, K., Zhu, Z. and Fu, M., Adaptive back-stepping sliding mode attitude control of missile systems Int. J. Robust. Nonlinear Control, 2013.DOI: 10.1002/rnc.2952
16
[17]Hoseini S.M., Farrokhi M., and Koshkouei, A.J., Robust adaptive control of nonlinear non-minimum phase systems with uncertainties, Automatica, vol. 47, 2011, pp. 348–357.
17
[18]Jie, G., Yongzhi, S. and Xiangdong, L., Finite-time sliding mode attitude control for a reentry vehicle with blended aerodynamic surfacesand a reaction control system, Chinese, Journal of Aeronautics, vol. 27, no.4, 2014, pp. 964–976.
18
[19]Song, Y.D. and Cai W.C., New Intermediate quaternion based control of spacecraft: part I-almost global attitude tracking, International Journal of Innovative Computing, Information and Control, vol. 8, no. 10, 2012.
19
[20] Hall, J. S., Analysis and experimentation of control strategies for underactuated spacecraft, Ph.D. dissertation, Dept. Mech. and Astro. Eng., Naval Postgraduate School, Monterey, CA, 2009.
20
[21] Hoseini, S. M., Farrokhi, M., and Koshkouei, A. J. "Adaptive neural network output feedback stabilization of nonlinear non-minimum phase systems", Int. J. Adapt. Control Signal Process, vol. 24, 2010, pp. 65-82.
21
[22] Hoseini, S. M., Havaii, M., Amelian, J. and Shahmirzai, M., Robust adaptive control of flexible manipulators using multilayer percepron, J. Intell. Fuzzy Systems.
22
[23] Farmanbordar, A., and Hoseini, S. M., "Neural network adaptive output feedback control of flexiblelink manipulators," J. Dyn. Sys., Meas., Control, vol. 135, no. 2, 2012.
23
[24] Titterton, D. H. Strapdown Inertial Navigation Technology, American Institute of Aeronautics and Astronautics lnc, 2004.
24
ORIGINAL_ARTICLE
Buckling and Post-buckling Analysis of FG-CNTRC Beams: An Exact Closed Form Solution
The present work derives the exact analytical solutions for buckling and post-buckling analysis of nano-composite beams reinforced by single-walled carbon nanotubes (SWCNTs) based on the Euler-Bernoulli beam theory and principle of virtual work. The reinforcements are considered to be aligned in the polymeric matrix either uniformly distributed (UD) or functionally graded (FG) distributed through the thickness direction of the beam. In FG beams, material properties vary gradually along the thickness direction. The effective material properties of the nano-composite beam are predicted based on the extended rule of mixture. Also, by applying von Kármán assumptions, the geometric nonlinearities are taken into consideration. The developed governing equations are solved by utilizing analytical methods and exact closed form solutions for buckling and post-buckling loads of functionally graded carbon nanotube-reinforced composite (FG-CNTRC) beam with different boundary conditions are obtained. By comparing the present post-buckling load results with the ones reported in the literature, the accuracy and reliability of the current method are demonstrated. Eventually, the numerical results are provided and the effects of CNTs distribution, CNTs volume fraction, slenderness ratio, maximum deflection of the beam and boundary conditions on the post-buckling characteristics of the CNTRC beam are discussed.
https://jast.ias.ir/article_81563_43f017f611e2bf0e3c6efbe165d12ea5.pdf
2017-10-01
33
41
Post-buckling analysis
Nano-composite beams
functionally graded materials
Exact Solution
H.
Shafiei
1
Department of Mechanical and Aerospace Engineering, Shiraz University of Technology
AUTHOR
A.R.
Setoodeh
h.shafiei@sutech.ac.ir
2
Department of Mechanical and Aerospace Engineering, Shiraz University of Technology
AUTHOR
[1] S. Iijima, “Helical microtubules of graphitic carbon”, Nature, vol. 354, no. 6348, pp. 56-58, November 1991.
1
[2] B.G. Demczyk, Y.M. Wang, J. Cumings, M. Hetman, W. Han, A. Zettl and R.O. Ritchie, “Direct mechanical measurement of the tensile strength and elastic modulus of multiwalled carbon nanotubes,” Materials Science and Engineering, vol. 334, no. 1-2, pp. 173-178, September 2002.
2
[3] H. Dai, “Carbon nanotubes: opportunities and challenges,” Surface Science, vol. 500, no. 1-3, pp. 218-241, March 2002.
3
[4] R. Ansari, H. Rouhi and S. Sahmani, “Free vibration analysis of single- and double-walled carbon nanotubes based on nonlocal elastic shell models,” Journal of Vibration and Control, vol. 20, no. 5, pp. 670-678, April 2014.
4
[5] H. Wan, F. Delale and L. Shen, “Effect of CNT length and CNT-matrix interphase in carbon nanotube (CNT) reinforced composites,” Mechanics Research Communications, vol. 32, no. 5, pp. 481-489, September 2005.
5
[6] Y. Han and J. Elliot, “Molecular dynamics simulations of the elastic properties of polymer/carbon nanotube composites: modeling and characterization,” Computational Materials Science, vol. 39, no. 2, pp. 315-323, April 2007.
6
[7] E.T. Thostenson and T.W. Chou, “On the elastic properties of carbon nanotube-based composites: Modeling and characterization”, Journal of Physics D: Applied Physics, vol. 36, no. 5, pp. 573-582, February 2003.
7
[8] V. Mittak, Polymer nanotube nanocomposite: synthesis, properties and applications, John Wiley and Sons, New Jersey, 2010.
8
[9] A.M.K. Esawi and M.M. Farag, “Carbon nanotube reinforced composites: potential and current challenges,” Materials and Design, vol. 28, no. 9, pp. 2394-2401, November 2007.
9
[10] K.M. Liew, Z.X. Lei and L.W. Zhang, “Mechanical analysis of functionally graded carbon nanotube reinforced composites: A review”, Composite Structures, vol. 120, pp. 90-97, February 2015.
10
[11] B.S. Aragh, A.H.N. Barati and H. Hedayati, “Eshelby-Mori-Tanaka approach for vibrational behavior of continuously graded carbon nanotube-reinforced cylindrical panels”, Composites Part B: Engineering, vol. 43, no. 4, pp. 1943-1954, June 2012.
11
[12] R. Ansari, M.F. Shojaei, V. Mohammadi, R. Gholami and F. Sadeghi, “Nonlinear forced vibration analysis of functionally graded carbon nanotube-reinforced composite Timoshenko beams”, Composite Structures, vol. 113, pp. 316-327, July 2014.
12
[13] H. Shafiei and A.R. Setoodeh, “Nonlinear free vibration and post-buckling of FG-CNTRC beams on nonlinear foundation”, Steel and Composite Structures, vol. 24, no. 1, pp. 65-77, May 2017.
13
[14] M. Shojaee, A.R. Setoodeh and P. Malekzadeh, “Vibration of functionally graded CNTs-reinforced skewed cylindrical panels using a transformed differential quadrature method”, Acta Mechanica, vol. 228, no. 7, pp. 2691-2711, July 2017.
14
[15] D.G. Ninh, “Nonlinear thermal torsional post-buckling of carbon nanotube-reinforced composite cylindrical shell with piezoelectric actuator layers surrounded by elastic medium”, Thin-Walled Structures, vol. 123, pp. 528-538, February 2018.
15
[16] L.L. Ke, J. Yang and S. Kitipornchai, “Nonlinear free vibration of functionally graded carbon nanotube-reinforced composite beams,” Composite Structures, vol. 92, no. 3, pp. 676-683, February 2010.
16
[17] L.W. Zhang, Z.X. Lei and K.M. Liew, “Buckling analysis of FG-CNT reinforced composite thick skew plates using an element-free approach,” Composite Part B: Engineering, vol. 75, no. 15, pp. 36-46, June 2015.
17
[18] A.R. Setoodeh and M. Shojaee, “Application of TW-DQ method to nonlinear free vibration analysis of FG carbon nanotube-reinforced composite quadrilateral plates,” Thin-Walled Structures, vol. 108, pp. 1-11, November 2016.
18
[19] H.S. Shen, X.Q. He and D.Q. Yang, “Vibration of thermally postbuckled carbon nanotube-reinforced composite beams resting on elastic foundations”, International Journal of Non-Linear Mechanics, vol. 91, pp. 69-75, May 2017.
19
[20] M.H. Yas and N. Samadi, “Free vibration and buckling analysis of carbon nanotube-reinforced composite Timoshenko beams on elastic foundation,” International Journal of Pressure Vessels and Piping, vol. 98, pp. 119-128, October 2012.
20
[21] H.L. Wu, J. Yang, and S. Kitipornchai, 2016. “Imperfection sensitivity of postbuckling behavior of functionally graded carbon nanotube-reinforced composite beams,” Thin-Walled Structures, vol. 108, pp. 225-233, November 2016.
21
[22] H.L. Wu, S. Kitipornchai and J. Yang, “Thermal buckling and postbuckling analysis of functionally graded carbon nanotube-reinforced composite beams,” Applied Mechanics and Materials, vol. 846, pp. 182-187, July 2016.
22
[23] S. Pouresmaeeli and S.A. Fazelzadeh, “Uncertain buckling and sensitivity analysis of functionally graded carbon nanotube-reinforced composite beam”, International Journal of Applied Mechanics, vol. 9, no. 5, pp. 1750071, July 2017.
23
[24] S.A. Emam and A H. Nayfeh, “Postbuckling and free vibration of composite beams”, Composite Structures, vol. 88, no. 4, pp. 636-642, May 2009.
24
[25] A.R. Setoodeh, M. khosrownejad and P. Malekzadeh, “Exact nonlocal solution for postbuckling of single-walled carbon nanotubes,” Physica E, vol. 43, no. 9, pp. 1730-1737, July 2011.
25
[26] A. Fallah and M.M. Aghdam, “Nonlinear free vibration and post-buckling analysis of functionally graded beams on nonlinear elastic foundation,” European Journal of Mechanics A/Solids, vol. 30, no. 4, pp. 571-583, July-August 2011.
26
[27] R.K. Gupta, J.B. Gunda, G.R. Janardhan and G.V. Rao, “Post-buckling analysis of composite beams: Simple and accurate closed-form expressions,” Composite Structures, vol. 92, no. 8, pp. 1947-1956, July 2010.
27
ORIGINAL_ARTICLE
Optimization of Composite Stiffened Cylindrical Shell using PSO Algorithm
Composite stiffened cylindrical shells are widely used as primary elements in aerospace structures. In the recent years, there has been a growing research interest in optimum design of composite stiffened cylindrical shell structures for stability under buckling load. This paper focuses upon the development of an efficient optimization of ring-stringer stiffened cylindrical shell. The optimization problem used in this study involves weight minimization of ring-stringer stiffened composite cylindrical shell with buckling load and stress, which are considered as design constraints. The proposed methodology is based on Particle Swarm Optimization (PSO) algorithm. The material of shell is composite, but the material of stiffeners is considered to be isotropic. The approach adopted in modeling utilizes the Rayleigh-Ritz energy method and the stiffeners are treated as discrete members. In addition, a 3-D Finite Element (FEM) model of the ring-stringer stiffened cylindrical shell is developed that takes into consideration the exact geometric configuration. The results obtained using the Rayleigh-Ritz energy method are compared with those using 3-D FE model. The proposed methodology is implemented on the ring-stringer stiffened cylindrical shell using the PSO algorithm. The obtained results show a 13% reduction in the weight of the ring-stringer stiffened cylindrical shell whilst all the design constraints are satisfied. In addition, the results show that the proposed methodology provides an effective way of solving composite stiffened cylindrical shell design problems.
https://jast.ias.ir/article_81570_a2774c8efa679a13ecc7a558c1285b68.pdf
2017-10-01
43
51
optimization
PSO algorithm
Cylindrical Shell
Composites
M.
Fakoor
1
Faculty of New Science and Technologies, University of Tehran
AUTHOR
P.
Mohammadzade
2
Faculty of New Science and Technologies, University of Tehran
AUTHOR
E.
Jafari
3
Faculty of New Science and Technologies, University of Tehran
AUTHOR
[1] Simitses, G. J., “Buckling and Postbuckling of Imperfect Cylindrical Shells: A Review“, Applied
1
Mechanics Reviews, Vol. 39, No. 10, pp. 1517-1524, 1986.
2
[2] Akbulut, M. and F. O. Sonmez (2008). "Optimum design of composite laminates for minimum
3
thickness." Comput. Struct. 86(21-22): 1974-1982.
4
[3] Lopez, R., et al. (2009). Optimization of laminated composites considering different failure criteria.
5
[4] Coburn, B. H., et al. (2014). "Buckling analysis of stiffened variable angle tow panels." Composite Structures 111: 259-270.
6
[5] Ye, F., et al. (2017). "Variable stiffness composite material design by using support vector regression
7
assisted efficient global optimization method." Structural and Multidisciplinary Optimization 56(1):203-219.
8
[6] Ganguli, R. (2013). Optimal Design of Composite Structures: A Historical Review.
9
[7] Bahubalendruni, M. V. A. R. and B. B. Biswal, (2014). Study of optimization of composite structures with respect to industrial applications. 2014 IEEE 8th International Conference on Intelligent Systems and Control (ISCO).
10
[8] Henrichsen, S. R. (2015). Optimization of Laminated Composite Structures, Aalborg Universitetsforlag.
11
[9] Koide, R. M. and M. A. Luersen (2013)."Maximization of Fundamental Frequency of Laminated Composite Cylindrical Shells by Ant Colony Algorithm." Journal of Aerospace Technology and Management 5: 75-82.
12
[10] Léné, F., et al. (2009). "An advanced methodology for optimum design of a composite stiffened cylinder." Composite Structures 91(4): 392-397.
13
[11] Muc, A., “Transverse shear effects in discrete optimization of laminated compressed cylindrical
14
shells“, Composite Structures, Vol. 38, No. 1, pp.489-497, 1997/05/01, 1997.
15
[12] Paweł Foryś, Optimization of cylindrical shells stiffened by rings under external pressure including
16
their post-buckling behaviour, Institute of Applied Mechanics, Cracow University of Technology, al. Jana Pawła II 17, 31-864 Kraków, Poland.
17
[13] Khong, P., “Optimal Design of Laminates for Maximum Buckling Resistance and Minimum Weight“, 1999.
18
[14] Walker, M., Smith, R. E., “A technique for the multiobjective optimisation of laminated composite
19
structures using genetic algorithms and finite element analysis“, Composite Structures, Vol. 62,
20
No. 1, pp. 123-128, 10//, 2003.
21
[15] Adams, D. B., Watson, L. T., Gürdal, Z., Anderson-Cook, C. M., “Genetic algorithm optimization and
22
blending of composite laminates by locally reducing laminate thickness“, Advances in Engineering Software, Vol. 35, No. 1, pp. 35-43,1//, 2004.
23
[16] MH Shojaeifard, R Talebitooti, A Yadollahi, Optimization of sound transmission through laminated composite cylindrical shells by using a genetic algorithm, mechanics of composites
24
materials, September 2011, 47:481.
25
[17] Park, J. H., Hwang, J. H., Lee, C. S., Hwang, W.,“Stacking sequence design of composite laminates
26
for maximum strength using genetic algorithms“,Composite Structures, Vol. 52, No. 2, pp. 217-231,5//, 2001
27
[18] A. Gharib, Shakeri M, , Stacking sequence optimization of laminated cylindrical shells for
28
buckling and free vibration using genetic algorithm and neural networks, 2nd International Conference on Engineering Optimization, September 6 - 9,2010, Lisbon, Portugal.
29
Sadeghifar, M., Bagheri, M., Jafari, A. A.,
30
“Multi objective optimization of or thogonally stiffened cylindrical shells for minimum weight and maximum axial buckling load“, Thin-Walled
31
Structures, Vol. 48, No. 12, pp. 979-988, 12//, 2010.
32
[20] R. Talebitooti, MH Shojaeefard, S
33
Yarmohammadisatri, Shape design optimization of
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cylindrical tank using b-spline curve, Computers and
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Fluids, Vol 109, 10 March 2015, Pages 100-112.
36
[21] Kennedy, J., Eberhart, R., “Particle swarm optimization“, in Proceeding of, 1942-1948 vol.4.
37
[22] P. Y. Jiang, Z. M. Lin, J. Xu, and J. Q. Sun, “A Particle Swarm Optimization Algorithm for
38
Minimizing Weight of the Composite Box Structure,” in Advanced Materials Research, 2012, vol. 430, pp. 70–475.
39
[23] I. C. Trelea, “The particle swarm optimization algorithm: convergence analysis and parameter
40
selection,” Inf. Process. Lett., vol. 85, no. 6, pp.317–325, 2003.
41
[24] S. Suresh, P. B. Sujit, and A. K. Rao, “Particle swarm optimization approach for multi-objective composite box-beam design,” Compos. Struct., vol. 81, no. 4, pp. 598–605, 2007.
42
[25] N. Chang, W. Wang, W. Yang, and J. Wang, “Ply stacking sequence optimization of composite laminate by permutation discrete particle swarm optimization,” Struct. Multidiscip. Optim., vol. 41, no. 2, pp. 179–187, 2010.
43
[26] Akl, W., Ruzzene, M., Baz, A., “Optimal design of underwater stiffened shells“, Structural and Multidisciplinary Optimization, Vol. 23, No. 4, pp.297-310, 2002.
44
[27] Tian, J., Wang, C. M., Swaddiwudhipong, S., “Elastic buckling analysis of ring-stiffened cylindrical shells under general pressure loading via the Ritz method“, Thin-Walled Structures, Vol. 35, No. 1, pp. 1-24, 9//, 1999.
45
[28] Rinehart, S. A., Wang, J. T. S., “Vibration of simply supported cylindrical shells with longitudinal stiffeners“, Journal of Sound and Vibration, Vol. 24, No. 2, pp. 151-163, 1972/09/22,1972.
46
[29] Lim, C., Ma, Y., “Computational p-element method on the effects of thickness and length on self weight buckling of thin cylindrical shells via various shell theories“, Computational mechanics,Vol. 31, No. 5, pp. 400-408, 2003.
47
ORIGINAL_ARTICLE
Optimization of Sound Transmission Loss of a Composite Rectangular Plate with Infinite Baffle
In this paper, optimization of the sound transmission loss of finite rectangular anisotropic laminated composite plate with simply supported boundary conditions has been developed to maximize transmission loss. Appropriate constraints were imposed to prevent the occurrence of softening effect due to optimization. For this purpose, optimization process was incorporated into comprehensive finite element software. The transmission loss (TL) obtained from the numerical solution was compared with those of other authors indicated good agreement. The discrete frequencies have been chosen based upon the sound transmission class with A-weighting constant. Several traditional composite materials have been studied and the results have shown that in the mass control region, the optimization of stacking sequence and optimal thickness has not been an effective contribution to improve the transmission loss. The results also show that, the lamina thickness optimization has an important effect on improving the transmission loss, but the advantage of low weight composite material is compromised by optimization.
https://jast.ias.ir/article_81584_aef712abbb6baa436c221f66820e783d.pdf
2017-10-01
53
63
optimization
Transmission Loss
Baffle
Composite Panel
A.
nouri
1
Shahid Sattary University of Science and Technology
LEAD_AUTHOR
S.
Astaraki
2
Shahid Sattary University of Science and Technology
AUTHOR
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[18] R Talebitooti,M. R. Zarastvand, H. D Gohari, “Investigation of power transmission across laminated composite doubly curved shell in the presence of external flow considering shear deformation shallow shell theory”, Journal of Vibration and Control, Vol 24, Issue 19, 2018.
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