Phân tích dao động tấm composite lớp gấp nếp có gân gia cường bằng cách sử dụng phần tử tứ giác đăng tham số tám nút
Bài báo trình bày một số kết quả tính tần số dao động riêng, phân tích đáp ứng tức thời của chuyển vị, phân tích dạng dao động riêng của tấm composite lớp gấp nếp có và không có gân gia cường bằng phương pháp phần tử hữu hạn.
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Tóm tắt nội dung tài liệu: Phân tích dao động tấm composite lớp gấp nếp có gân gia cường bằng cách sử dụng phần tử tứ giác đăng tham số tám nút
TẠP CHÍ KHOA HỌC VÀ CÔNG NGHỆ NĂNG LƯỢNG (ISSN: 1859 – 4557) SỐ 7 - 2014 82 VIBRATION ANALYSIS OF STIFFENED FOLDED COMPOSITE PLATES USING EIGHT NODDED ISOPARAMETRIC QUADRILATERAL ELEMENTS PHÂN TÍCH DAO ĐỘNG TẤM COMPOSITE LỚP GẤP NẾP CÓ GÂN GIA CƯỜNG BẰNG CÁCH SỬ DỤNG PHẦN TỬ TỨ GIÁC ĐĂNG THAM SỐ TÁM NÚT Bui Van Binh Electric Power University Tóm tắt: Bài báo trình bày một số kết quả tính tần số dao động riêng, phân tích đáp ứng tức thời của chuyển vị, phân tích dạng dao động riêng của tấm composite lớp gấp nếp có và không có gân gia cường bằng phương pháp phần tử hữu hạn. Ảnh hưởng của góc gấp nếp, góc sợi, cách sắp xếp gân, số gân của tấm được làm rõ qua các kết quả số. Chương trình tính bằng Matlab được thiết lập dựa trên lý thuyết tấm bậc nhất có kể đến biến dạng cắt ngang của Mindlin. Các kết quả số thu được có tính tương đồng cao khi so sánh với các kết quả của các tác giả khác đã công bố trên các tạp chí có uy tín. Từ khóa: Phân tích dao động, đáp ứng động lực học, tấm composite gấp nếp có gân gia cường, phương pháp phần tử hữu hạn. Abstract: This paper presents several numerical results of natural frequencies, transient displacement responses, and mode shape analysis of unstiffened and stiffened folded laminated composite plates using finite element method. The effects of folding angle, fiber orientations, stiffeners, and position of stiffeners of the plates are illustrated. The program is computed by Matlab using isoparametric rectangular plate elements with five degree of freedom per node based on Mindlin plate theory. The calculated results are correlative in comparison with other authors’ outcomes published in prestigious journals. Keywords: Vibration analysis, dynamic response; stiffeners, stiffened folded laminated composite plates, finite element method. TẠP CHÍ KHOA HỌC VÀ CÔNG NGHỆ NĂNG LƯỢNG (ISSN: 1859 – 4557) SỐ 7 - 2014 83 INTRODUCTION Folded laminate composite plates have been found almost everywhere in various branches of engineering, such as in roofs, ship hulls, sandwich plate cores and cooling towers, etc. Because of their high strength-to-weight ratio, easy to form, economical, and have much higher load carrying capacities than fat plates, which ensures their popularity and has attracted constant research interest since they were introduced. Because the laminated plates with stiffeners become more and more important in the aerospace industry and other modern engineering fields, wide attention has been paid on the experimental, theoretical and numerical analysis for the static and dynamic problems of such structures in recent years. The flat plate with stiffeners based on the finite element model and were presented in [1, 2, 3, 5, 6, 7, 8]. In those studies, the Kirchhoff, Mindlin and higher-order plate theories are used. Those researches used the assumption of eccentricity (or concentricity) between plate and stiffeners: a stiffened plate is divided into plate element and beam element. Behavior of unstiffened isotropic folded plates has been studied previously by a host of investigators using a variety of approaches. Goldberg and Leve [9] developed a method based on elasticity. According to this method, there are four components of displacements at each point along the joints: two components of translation and a rotation, all lying in the plane normal to the joint, and a translation in the direction of the joint. The stiffness matrix is derived from equilibrium equations at the joints, while expanding the displacements and loadings into the Fourier series considering boundary conditions. Bar-Yoseph and Herscovitz [10] formulated an approximate solution for folded plates based on Vlassov’s theory of thin-walled beams. According to this work, the structure is divided into longitudinal beams connected to a monolithic structure. Cheung [11] was the first author developed the finite strip method for analyzing isotropic folded plates. Additional works in the finite strip method have been presented. The difficulties encountered with the intermediate supports in the finite strip method [12] were overcome and subsequently Maleki [13] proposed a new method, known as compound strip method. Irie et al. in [14] used Ritz method for the analysis of free vibration of an isotropic cantilever folded plate. Perry et al. in [15] presented a rectangular hybrid stress element for analyzing a isotropic folded plate structures in bending cases. In this, they used a four-node element, which is based on the classical hybrid stress method, is called the hybrid coupling element and is generated by a combination of a hybrid plane stress element and a hybrid plate bending element. Darılmaz et al. in [16] presented an 8-node quadrilateral assumed-stress hybrid shell element. Their formulation is based on Hellinger TẠP CHÍ KHOA HỌC VÀ CÔNG NGHỆ NĂNG LƯỢNG (ISSN: 1859 – 4557) SỐ 7 - 2014 84 - Reissner variational principle for bending and free vibration analyses of structures, which have isotropic material properties. Haldar and Sheikh [17] presented a free vibration analysis of isotropic and composite folded plate by using a sixteen nodes triangular element. Suresh and Malhotra [18] studied the free vibration of damped composite box beams using four node plate elements with five degrees of freedom per node. Niyogi et al. in [19] reported the analysis of unstiffened and stiffened symmetric cross-ply laminate composite folded plates using first- order transverse shear deformation theory and nine nodes elements. In their works, only in axis symmetric cross-ply laminated plates were considered. So that, there is uncoupling between the normal and shear forces, and also between the bending and twisting moments, then besi ... 1 63.3 63.6 68.7 71.49 66.4 73.5 2 69.7 69.8 75.6 73.18 69.5 73.9 3 150.5 152.7 155.3 157.8 149.9 146.1 4 156.7 158.3 159.5 161.2 156.3 156.1 900 5 203.9 201.9 183.5 183.6 190.8 194.6 TẠP CHÍ KHOA HỌC VÀ CÔNG NGHỆ NĂNG LƯỢNG (ISSN: 1859 – 4557) SỐ 7 - 2014 89 [00/00/00] Present: Angle-ply off axis Present: Cross-ply in axis α ωi Present [19] [450/-450]s [45 0/-450]ns [90 0/00]s [90 0/00]ns 1 59.5 59.3 56.2 57.1 56.8 57.7 2 63.1 63.4 73.3 72.7 66.1 73.1 3 150.3 152.5 154.0 157.1 149.7 146.1 4 153.9 155.0 156.1 158.0 153.1 152.2 1200 5 193.5 190.9 167.4 168.1 175.2 176.0 1 42.3 42.3 40.2 40.7 39.7 38.9 2 60.7 60.8 66.5 66.4 62.3 67.5 3 133.2 131.5 119.0 119.1 122.5 125.1 4 144.9 145.6 143.0 144.2 142.9 138.7 1500 5 149.9 151.8 153.9 157.2 149.3 145.9 Table 3. First three natural frequencies of stiffened two folded composite plate for folding angle α=900,1200,1500, fiber orientation of [900/900/900]. Case 2 Case 3 Case 4 α ωi Present [19] Present [19] Present [19] 1 69.54 69.6 72.73 72.2 95.12 95.6 2 73.98 73.9 81.55 81.1 119.36 122.5 900 3 183.82 181.4 173.19 171.0 195.42 199.1 1 65.36 65.0 74.28 73.8 67.63 67.3 2 69.80 69.9 77.04 76.2 112.11 109.6 1200 3 176.95 174.7 161.28 160.4 180.36 182.5 1 52.86 52.4 66.29 65.3 42.27 42.5 2 68.54 68.5 76.27 75.7 93.15 93.5 1500 3 125.16 123.5 133.12 131.4 148.21 147.9 The first five mode shapes of the unstiffened and three cases of stiffened composite plate are plotted in Fig. 3 for folding angle α=1200, fiber orientation of [450,-450/450]. TẠP CHÍ KHOA HỌC VÀ CÔNG NGHỆ NĂNG LƯỢNG (ISSN: 1859 – 4557) SỐ 7 - 2014 90 Fig.3. First five mode shapes of the unstiffened and three cases of stiffened composite plate, for folding angle α=1200; fiber orientation of [450,-450/450]. a- Folding angle α=900, b- Folding angle α=1500 Fig.4. Effects of fiber orientation θ on the first five natural frequencies for folding angle α=900 and α=1500, [θ0/θ0/θ0], thickness t=0.02L. 0 10 20 30 40 50 60 70 80 90 60 80 100 120 140 160 180 200 220 Fiber Orientaions(deg) N a tu ra l F re q u e n c ie s (H z ) _1Mode _ 2Mode _ 3Mode _ 4Mode _ 5Mode 0 10 20 30 40 50 60 70 80 90 40 60 80 100 120 140 160 Fiber Orientaions(deg) N a tu ra l F re q u e n c ie s (H z ) _1Mode _ 2Mode _ 3Mode _ 4Mode _ 5Mode f1= 60.17(Hz) f2= 117.62(Hz) f4= 186.21(Hz) f5= 201.80(Hz) f3= 163.84(Hz) f1= 66.81(Hz) f2= 74.92(Hz) f4= 170.58(Hz) f5= 263.54(Hz) f3= 162.41(Hz) f1= 58.49(Hz) f2= 76.83(Hz) f4= 179.81(Hz) f5= 203.02(Hz) f3= 153.74(Hz) f1= 55.67(Hz) f2= 73.21(Hz) f4= 154.40(Hz) f5= 156.98(Hz) f3= 151.23(Hz) TẠP CHÍ KHOA HỌC VÀ CÔNG NGHỆ NĂNG LƯỢNG (ISSN: 1859 – 4557) SỐ 7 - 2014 91 Fig.3 shows that the stiffeners do not make any change in getting mode shapes of presented plates (mode shapes make this study interesting, useful in dynamic analysis of the plates, but any generalized recommendation is very difficult without undergoing numerical experiments). * The effects of fiber orientations on natural frequencies: Secondly, the effects of fiber orientations on the first five natural frequencies of two folded composite plate made of [θ0/θ0/θ0] has been carried out for various folding angle α. The results are plotted in Fig. 4a and Fig.4b for folding angle α = 900 and α = 1500, respectively. 3.2 Transient analysis. We consider a cantilever two folded composite plate with the same dimension and material properties of section 3.1 for unstiffened and three cases of stiffened composite plates. The folded plates subjected to a uniformly distributed step loading of intensity q0 = 10kN/m 2 on face (1) for all cases. The location of point A (central point of top face) is shown in Fig.5a, analysis time step of 0.0005t ms, duration time of T = 0.025 (sec). The loading condition scheme is shown in Fig.5b with t1 = 1ms, t2 = 2ms, t3 = 25ms. (b)- Triangular step loading scheme. Time (s) t1 q(t) t2 t3 q0 0 (a)- Two folded composite plate. L L/3 L/3 L/3 α x z y Face (1) q0 Point A Fig.5. Two folded composite plates with folding angle α subjected to uniformly step loading Fig.6a, 6b, 6c and 6d plotted the effect of folding angle α on displacement responses measurement at point A of the plate which having the fiber orientation [450/-450/450/-450] for case 1, case2, case3 and case 4, respectively. From Fig.6, it can be observed that the displacement responses of folding angle α =900 and α =1200 are closed to each other, the displacement response of α =1500 is extremely higher than the others. The different become more rapidly for Case 1. The displacement amplitude and wave of Case 4 change more dramatic in the early time. Furthermore, there is a significant increase of vibration frequencies when the plates having clamped at edges. TẠP CHÍ KHOA HỌC VÀ CÔNG NGHỆ NĂNG LƯỢNG (ISSN: 1859 – 4557) SỐ 7 - 2014 92 0 0.005 0.01 0.015 0.02 0.025 -1.5 -1 -0.5 0 0.5 1 1.5 x 10 -4 Time (sec) D e fl e c ti o n s (m ) 090 0120 0150 (a) 0 0.005 0.01 0.015 0.02 0.025 -1.5 -1 -0.5 0 0.5 1 1.5 x 10 -4 Time (sec) D e fl e c ti o n s (m ) 090 0120 0150 (b) 0 0.005 0.01 0.015 0.02 0.025 -1.5 -1 -0.5 0 0.5 1 1.5 x 10 -4 Time (sec) D e fl e c ti o n s (m ) 090 0120 0150 (c) 0 0.005 0.01 0.015 0.02 0.025 -1.5 -1 -0.5 0 0.5 1 1.5 x 10 -4 Time (sec) D e fl e c ti o n s (m ) 090 0120 0150 (d) Fig.6. Effect of folding angle α on transient response, [450/-450/450/-450]. 0 0.005 0.01 0.015 0.02 0.025 -8 -6 -4 -2 0 2 4 6 8 x 10 -5 Time (sec) D e fl e c ti o n s (m ) Case 1 Case 2 Case 3 Case 4 (a) 0 0.005 0.01 0.015 0.02 0.025 -1.5 -1 -0.5 0 0.5 1 1.5 x 10 -4 Time (sec) D e fl e c ti o n s (m ) Case 1 Case 2 Case 3 Case 4 (b) (a)- Folding angle α=900; (b)- Folding angle α=1500 Fig.7.Comparision of transient response for different stiffener conditions of composite folded plate, [450/-450/450/-450] TẠP CHÍ KHOA HỌC VÀ CÔNG NGHỆ NĂNG LƯỢNG (ISSN: 1859 – 4557) SỐ 7 - 2014 93 Fig. 7a and Fig. 7b plotted comparison of transient response of the composite folded plates for different stiffener conditions for α = 900 and α = 1500, respectively. It is revealed that the stiffness of the structure gradually reduces such as case1→ case2→ case3→ case4. With stiffener conditions, the deflection reduces and smallest amplitude in Case 3. To observe effect of fiber orientation on transient response of the plates, we compared the response of two fiber orientation ([450/-450/450/-450] and [900/00/900/00]) for four cases: Case 1- Case4. The result is given in Fig. 8. In which: Fig.11a, 11b, 11c and 11d plotted the displacement responses measurement at point A of the plates (which have the folding angle α = 1200 for: Case 1, Case2, Case3 and Case 4, respectively. 0 0.005 0.01 0.015 0.02 0.025 -8 -6 -4 -2 0 2 4 6 8 x 10 -5 Time(sec) D e fl e c ti o n s (m ) 0 0 0 0[45 / 45 / 45 / 45 ] 0 0 0 0[90 / 0 / 90 / 0 ] (a) 0 0.005 0.01 0.015 0.02 0.025 -6 -4 -2 0 2 4 6 x 10 -5 Time(sec) D e fl e c ti o n s (m ) 0 0 0 0[45 / 45 / 45 / 45 ] 0 0 0 0[90 / 0 / 90 / 0 ] (b) Fig.8 (a, b). Comparing effect of fiber orientation on transient response of the plate for different stiffener condition: Case 1 and Case 2, folding angle α =1200 0 0.005 0.01 0.015 0.02 0.025 -6 -4 -2 0 2 4 6 x 10 -5 Time(sec) D e fl e c ti o n s (m ) 0 0 0 0[45 / 45 / 45 / 45 ] 0 0 0 0[90 / 0 / 90 / 0 ] (c) 0 0.005 0.01 0.015 0.02 0.025 -5 -4 -3 -2 -1 0 1 2 3 4 5 x 10 -5 Time(sec) D e fl e c ti o n s (m ) 0 0 0 0[45 / 45 / 45 / 45 ] 0 0 0 0[90 / 0 /90 / 0 ] (d) Fig.8 (c, d). Comparing effect of fiber orientation on transient response of the plate for different stiffener condition: Case 3 and Case 4, folding angle α =1200 TẠP CHÍ KHOA HỌC VÀ CÔNG NGHỆ NĂNG LƯỢNG (ISSN: 1859 – 4557) SỐ 7 - 2014 94 Fig.8 shows that the transient response of the laminate plates does not change in significant for angle-ply off axis and cross-ply in axis fiber orientation. 4. CONCLUSION In the present study, a finite element method using an eight nodded isoparametric plate elements, based on the first order shear deformation theory were investigated for analysis of free vibration and the transient response of the unstiffened and stiffened folded laminate composite plate. Good agreement is found between the results of this technique and other published results available in the literature. The effects of various parameters as folding angle, fiber orientation on natural frequencies, dynamic responses and mode shapes of unstiffened; stiffened folded laminate composite plates were indicated by some numerical results. The applicability of the present approach covers a wide range of forced vibration problems, geometric features, and boundary conditions. The results of this study will serve as a benchmark for future research for designing folded composite structures and sandwich structures made of composite materials, as it was extremely quick and reliable in producing design results. REFERENCE [1] Turkmen, H.S., Mecitoglu, Z, Dynamic response of a stiffened laminated composite plates subjected to blast load. Journal of Sound and Vibration 221: 371–389, 1999. [2] Zhao, X., Liew, K.M., Ng, T.Y, Vibrations of rotating cross-ply laminated circular cylindrical shells with stringer and rings stiffeners. Journal of Solids and Structures 39: 529–545, 2002. [3] Sadek, E.A., Tawfik, S.A, A finite element model for the analysis of stiffened laminated plates. Computers and Structures 75: 369–383, 2000. [4] Kumar, S.Y.V., Mukhopadhyay, M., A new triangular stiffened plate element for laminate analysis. Composites Science and Technology 60, 935–943, 2000. [5] Olson, M. D. and Hazell, C. R, Vibration studies on some integral rib-stiffened plates. 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