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Journal articles on the topic 'PATRAN'

Author: Grafiati
Published: 4 June 2021
Last updated: 25 April 2022

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1

Gao, Yi Chao, Feng Jin, Yan Jie Xu, and Jian Yang. "Development of Pre-Processor for OpenSees Based on Patran Command Language." Applied Mechanics and Materials 409-410 (September 2013): 1615–19. http://dx.doi.org/10.4028/www.scientific.net/amm.409-410.1615.

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OpenSees is an object-oriented open-source finite element software platform suitable for advanced simulation of structural and geotechnical systems. Lacking of powerful pre-processor, the preparing of input scripts for OpenSees is time consuming and error-prone for large and complex models. Patran is an excellent pre-processing commercial package for finite element analysis and offers the powerful Patran Command Language (PCL) for user customization. Taking the advantage of Patran in finite element pre-processing, the finite element modeling is done in Patran and the input script for OpenSees is generated by PCL. It is an alternative approach to efficient pre-processing for OpenSees.
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Li, Zhen Yang, Hui Long Ren, and Ya Wei Qi. "Structural Parametric Modeling and Analysis of a Ship Stiffened Deck Plate Based on the Patran Command Language." Applied Mechanics and Materials 733 (February 2015): 842–45. http://dx.doi.org/10.4028/www.scientific.net/amm.733.842.

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As a numerical calculation method in math, Finite Element Analysis (FEA) has been imported into the structural analysis field for more than 30 years. MSC. Patran was launched by the MSC Corporation into the field as a pre-processing and post-processing module of FEA, its strong potential of secondary development has played an important role in the structural parametric modeling analysis. Patran Command Language (PCL) is the built-in language of MSC. Patran. In this paper, in order to introduce PCL’s theory and using method, the author created a GUI by PCL which contains a lot of response functions in a ship stiffened deck plate project.
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Bushra, Abdelmunem, Mohammed Mahdi, and Mohammed A. Elhadi. "Structural Analysis of Light Aircraft Wing Components." Applied Mechanics and Materials 225 (November 2012): 201–6. http://dx.doi.org/10.4028/www.scientific.net/amm.225.201.

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This paper aims to demonstrate the structure analysis of strut-braced wing of a typical manufactured Light-Aircraft by using FEM software (MSC PATRAN/NASTRAN) and determine the safety margin in all of its components, which are useful to determine the structure strength requirements. The geometrical model of the wing was created in CATIA and then exported to PATRAN, which is the modeler to build the finite element model. PATRAN model geometry was modified and prepared to create the mesh. The structural components have various functions and shapes, thus different element mesh was created. After creating the finite element model for all parts, the elements and material properties were assigned and the model was fixed at the spar root edge and strut-braced end, and loaded by distributing the inertia load and aerodynamic load, calculated using (CFD), acting on the rib edge. Then the model was submitted to NASTRAN for linear static analysis. The obtained Stress Results and Safety Margins of each part were calculated and found to be acceptable.
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Zhou, Jie, Ji Sheng Ma, Hui Yong Deng, Mei Yin Zhang, and Bao Jian Wu. "Modal Analysis for the Tower of Large Scale." Applied Mechanics and Materials 299 (February 2013): 31–34. http://dx.doi.org/10.4028/www.scientific.net/amm.299.31.

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The rocket launch tower is a kind tower of large scale which is used in many important palces, in order to counter the tower faults problems such as leaning, bulking, etc.According to the theory of multimodal analysis, mathematical modeling and simulation of vibrational mode were conducted for the tower. The paper describes how the finite element modal for steel tower is built by means of beam and shell elements by Patran, and the analysis of the tower’s dynamical characteristic, bulking phenomenon employing commercial software Patran/Nastran,show that the results are closer to the test data,providing a basis for the tower optimal design.
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Wang, Bin, Chun Jie Wang, and Hong Chun Wu. "Patran Based Results Processing System for Spacecraft Mechanical Analysis." Applied Mechanics and Materials 42 (November 2010): 215–18. http://dx.doi.org/10.4028/www.scientific.net/amm.42.215.

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Regarding the basic method and process of current spacecraft structural mechanics analysis, the paper used the secondary development language of Patran (PCL) to automatically extract the finite element model information such as mass property, material property, element property etc; According to the mission of spacecraft mechanical analysis, the obtained results were re-solved to get the required information. Executable program was written in Java to transform the extracted results into specific forms in accordance with the predetermined templates. Finally, using the forms and menu libraries provided by PCL language, graphical interfaces were created to integrate all the functions and procedures in to Patran so that the whole process could be accomplished through an intuitive graphical interface, which was user-friendly. Adoption of the result processing system on specific examples verified the feasibility of the system.
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Han, Qian Peng, and Bo Peng. "Research of the FEM Mesh Generation Based on Patran." Applied Mechanics and Materials 525 (February 2014): 731–35. http://dx.doi.org/10.4028/www.scientific.net/amm.525.731.

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Finite element method(FEM) have been widely used in modern mechanical design,mesh generation is an important part of the finite element analysis,this article discussed the process of mesh generation through two practical cases and put forward some issues we should pay more attention to.
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7

Zhao, Wen Tao, Yong Zheng Li, and Sen Wang. "Integrated Simulation and Structure Optimization of Rigid-Flexible Coupling Mechanical Leg Based on PATRAN, NASTRAN and ADAMS." Applied Mechanics and Materials 614 (September 2014): 16–18. http://dx.doi.org/10.4028/www.scientific.net/amm.614.16.

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According to the requirements of light weight, low-energy and short development period under the conditions that leg mobile robots exert high movement adaptability, high speed and high load capacity, integrated simulation and structure optimization of rigid-flexible coupling mechanical leg are proposed based on PATRAN, NASTRAN and ADAMS. Firstly, .bdf file is obtained via PATRAN. Secondly, MNF is acquired via NASTRAN. Thirdly, the rigid-flexible coupling mechanical leg is established, the motion of mechanical leg based on the trajectory planning is implemented, and integrated simulation is completed via ADAMS. Finally, Structure optimization is processed step-by-step and completed whenever intermediate structure meets the stress and strain requirements. The example is presented that illustrates advantages of the proposed method.
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8

Wu, Hao Wei, Yong Jie Pang, and Ye Li. "The Optimization of the Structure of Bulk Chemical Hull Based on MSC.Patran/Nastran." Applied Mechanics and Materials 105-107 (September 2011): 880–85. http://dx.doi.org/10.4028/www.scientific.net/amm.105-107.880.

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The optimization of the structure of bulk chemical hull (BCH) is derived by the finite element modeling (FEM) which is obtained by Patran and Nastran. In this paper, first of all, a new type of ship, BCH, is introduced. Then, the optimal scenario in theory is indicated by researching the transverse section of cargo holds of an ordinary BCH. And the FEM of the cargo holds of this ship is analysed, including the modeling, the load and the figures of stress and strain. The final conclusion would be obtained by comparing of the results which could verify the assumption forenamed. The simplification of the design is contributed by the new concepts and powerful capabilities of modeling of Patran and Nastran which improved the efficiency of ship designers.
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9

Han, Qian Peng, and Bo Peng. "The Finite Element Modal Analysis of Spur Gear Based on Patran." Advanced Materials Research 962-965 (June 2014): 2957–60. http://dx.doi.org/10.4028/www.scientific.net/amr.962-965.2957.

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This article summarized the general process of parametric modeling and finite element analysis of spur gear,PRO/E used to create parametric model,and Patran used to finite element analysis.Parametric modeling can reduce design period of the similar products,and modal analysis provide the basis for the selection and optimization of gear.
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Zeng, Hong, Qi Gao, Wen Guang Zhang, and Yan Li. "The Modal Analysis for Spiral Bevel Gear Based on Patran/Nastran." Advanced Materials Research 299-300 (July 2011): 1083–86. http://dx.doi.org/10.4028/www.scientific.net/amr.299-300.1083.

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The three-dimensional parametric model of spiral bevel gear was built based on Pro/E, The parametric model was converted to Patran, and the modal analysis, 10 order natural frequency and 10 order correspondence with the frequency were obtained with the Nastran. It can avoid the resonance in the design of spiral bevel gear.
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11

M.Pd, A. Arwanto,. "EKSPLORASI ETNOMATEMATIKA BATIK TRUSMI CIREBON UNTUK MENGUNGKAP NILAI FILOSOFI DAN KONSEP MATEMATIS." Phenomenon : Jurnal Pendidikan MIPA 7, no. 1 (July 21, 2017): 40. http://dx.doi.org/10.21580/phen.2017.7.1.1493.

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Etnomatematika merupakan studi tentang ide-ide matematika dari masyarakat tradisional yang diterapkan dalam masyarakat tertentu, etnomatematika merupakan matematika yang dipraktikkan oleh kelompok budaya seperti masyarakat perkotaan dan pedesaan, kelompok buruh, anak-anak dari kelompok usia tertentu, masyarakat adat, dan lainnya. Batik Trusmi berhasil menjadi ikon batik dalam koleksi kain nasional. Batik Cirebon sendiri termasuk golongan Batik Pesisir, namun juga sebagian batik Cirebon termasuk dalam kelompok batik keraton. Hal ini dikarenakan Cirebon memiliki dua buah keraton yaitu Keratonan Kasepuhan dan Keraton Kanoman, yang konon berdasarkan sejarah dari dua keraton ini muncul beberapa desain batik Cirebonan Klasik yang hingga sekarang masih dikerjakan oleh sebagian masyarakat desa Trusmi di antaranya seperti motif Mega Mendung, Paksinaga Liman, Patran Keris, Patran Kangkung, Singa Payung, Singa Barong, Banjar Balong, Ayam Alas, Sawat Penganten, Katewono, Gunung Giwur, Simbar Menjangan, Simbar Kendo, yang dapat di explorasi etnomatematikanya untuk mengungkap nilai filosofi yang luhur dan konsep matematis.Penelitian ini adalah penelitian kualitatif dengan menggunakan metode etnografi. Tujuan penelitian ini untuk mengunkap filosofi dan konsep matematika.
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12

Tong, Gang, and Tong Fei Liu. "Finite Element Analysis of Woven Fabric Laminates Structural Strength." Advanced Materials Research 785-786 (September 2013): 199–203. http://dx.doi.org/10.4028/www.scientific.net/amr.785-786.199.

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The characteristics of the woven fabric laminates structure is described. The steps and method of building the woven fabric laminates structure finite element model in MSC Patran is provided. The accuracy of this method is verified by a group of finite element calculation and experimental data.
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13

Widianti, An-nisaa Kurnia, and Anung Bambang Studyanto. "Membaca Makna Ornamen Pepatraan Meja dan Kursi di Ruang Pengadilan Kerthagosa Klungkung Bali." Jurnal Muara Ilmu Sosial, Humaniora, dan Seni 1, no. 1 (May 10, 2017): 152. http://dx.doi.org/10.24912/jmishumsen.v1i1.345.

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Bali merupakan salah satu pusat seni ukir atau seni pahat yang menghasilkan suatu wujud citra visual yaitu ornamen (ragam hias). Wujud perupaan dari sebuah ornamen merupakan hasil pemikiran tradisi adat budaya (local genius) serta keagamaan yang memiliki unsur keindahan (estetika) dan makna. Ornamen yang akan dibahas dalam penelitian ini adalah pepatraan. Pepatraan sendiri berasal dari kata patran yang artinya daun. Ornamen patra sendiri merupakan hasil stilasi dari bentuk tumbuh-tumbuhan yang disusun berjajar dan berulang sehingga membentuk satu kesatuan. Penulis berusaha mengkaji kembali makna pepatraan (motif tumbuh-tumbuhan) di mana saat ini pengetahuan tentang kekayaan seni tradisional sudah hampir memudar. Pendekatan-pendekatan yang dipergunakan dalam penelitian ini adalah ilmu tafsir (hermeunetik) atas persepsi ornamentik pepatraan pada meja dan kursi di ruang pengadilan Kertha gosa Klungkung Bali. Adanya akulturasi antara budaya China yang mempengaruhi Majapahit di Bali membawa pengaruh sampai kepada sistem pemerintahannya yang terdapat di Kerajaan Klungkung Kertha gosa Bali. Kehadiran sebuah ornamen tidak semata sebagai pengisi ruang kosong dan tanpa arti, terlebih untuk karya peninggalan masa lalu seperti meja dan kursi di Kertha gosa Bali. Kata Kunci : ornamen pepatraan, Kerthagosa, Bali
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14

Tong, Gang, Tong Fei Liu, and Yang Chen Deng. "A Wing Structure Design Based on Topology Optimization." Advanced Materials Research 889-890 (February 2014): 272–76. http://dx.doi.org/10.4028/www.scientific.net/amr.889-890.272.

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Introduces the characteristics of topology optimization and bionics, proposes the steps and method of using MSC.Patran to establish the model of the wing structure topology optimization, and through to illustrate the feasibility of the method and the application value of the wing structure topology optimization and bionics design. Key words: topological optimization; wing structure; bionics design ;finite element; MSC Patran;MSC Nastran
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15

Saragi, Elfrida, Abdul Hafid, and Geni Rina Sunaryo. "APLIKASI MSC PATRAN UNTUK PENENTUAN RENTANG MAKSIMUM PENYANGGA PIPA PRIMER REAKTOR AP1000." Jurnal Pengembangan Energi Nuklir 17, no. 1 (June 15, 2015): 1. http://dx.doi.org/10.17146/jpen.2015.17.1.2613.

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ABSTRAK APLIKASI MSC PATRAN UNTUK PENENTUAN RENTANG MAKSIMUM PENYANGGA PIPA PRIMER REAKTOR AP1000. Penyangga pipa digunakan antara lain untuk menjaga agar pipa tidak membebani komponen dan mencegah terjadinya lendutan yang berlebihan. Penentuan posisi penyangga pipa ditetapkan oleh beberapa faktor, seperti adanya katup, adanya belokan pipa dan jarak antara dua komponen utama reaktor yaitu tangki reaktor dan pembangkit uap.Untuk transpor panas dari tangki reaktor ke pembangkit uap digunakan pipa hotleg. Tujuan penelitian ini adalah untuk dapat menentukan batas jarak penyangga yang baik dan sudut belok pipa pada pipa primer reaktor daya AP1000 berdiameter 37,5inchi diameter luar dan 31 inchi diameter dalam. Metode analisis yang digunakan adalah metode komputasi dengan pemodelan menggunakan software MSC Patran.Hasil perhitungan menunjukkan bahwa semakin jauh jarak penyangga pipa maka besar lendutan yang terjadi makin besar.Nilai maksimal yang cukup baik dan sesuai standar ASME adalah pada jarak 5 m dengan sudut belok pipa 45 derajat.Pada jarak tersebut defleksi maksimumyang terjadi sebesar 1.76 cm dan tegangan tekuk sebesar 2.06 MPa. Kata kunci: Tegangan tekuk, Defleksi, Penyangga pipa, Hotlegreaktor AP1000. ABSTRACT APPLICATION OF MSC-PATRANTO DETERMINE THE MAXIMUM RANGE SUPPORT OF PRIMARY PIPES NUCLEAR REACTOR AP1000. Pipe supports used among others, to keep the pipes from overloding the components and prevent excessive deflection. The position of the pipe support is determined by several factors, such as the presence of valves, pipe bends and the distance between the two main components of reactor. Heat transport from reactor tank to the steam generatorare performed using hotleg pipe. The purpose of this study was to determine a safe support distance limit and the angle of the pipe turn and bendingon the primary pipe of AP1000 power reactor with the outer pipe diameter of 37.5 inches, and the inner diameter of the pipe is 31 inches.The analytical method used is the computational modeling methodsusing the MSC Patran software. The calculation resultsshow that the greater the distance of the pipe support, then deflection occurs is greater. The maximum value that is quite good, andin accord to ASME standards is at a distance of 5 meter and the angle of pipe turn is 45 degree. At that distance, the maximum deflection occurs is 1.76 cm and bending stress is 2.06 MPa. Keywords: Deflection, Bending stress, Support pipes, Hotleg reactor AP1000.
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Zheng, Yuan Zhou, Yan Ling Huang, and Kai Zhou Peng. "Research on Structural Strength of Catamaran Superstructure Constructed with Aluminum Alloy." Advanced Materials Research 538-541 (June 2012): 3165–69. http://dx.doi.org/10.4028/www.scientific.net/amr.538-541.3165.

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The design of Superstructure constructed with aluminum alloy do not have to follow the traditional standard design method. It can be designed by applying strength theory and ANSYS program or MSC Patran / Nastran program, which can ensure the strength requirements with the selected aluminum alloy components and make the weight of the ship lightest. In this paper, the 42.4m catamaran sightseeing boat is used as an example. The structural strength of the superstructure constructed with aluminum alloy is calculated by MSC Patran / Nastran program. The distribution of the superstructure stress is obtained, which proved the size of the selected components of the superstructure can meet the requirements of the local strength and can be the reference of selecting the structure size. As the other conditions are unchanged, the the local thickness of the junction of the front wall and the side wall of the compass deck is changed. the relationship between plate thickness and stress is obtained. It is found that as The plate thickness is thicker, the stress there decreases; and as the thickness is smaller, it is obvious to reduce stress as the plate thickness Increase. when the thickness increases to a certain extent, the effect of the plate stress decreases is not obvious.
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Zhao, X. R., S. Hameed, H. Huang, and O. Rehman. "Simultaneous size and shape optimization for satellite adapter by using patran command language." Journal of Physics: Conference Series 1509 (April 2020): 012009. http://dx.doi.org/10.1088/1742-6596/1509/1/012009.

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Cui, Qing Bin, Jing Zhu Zhang, Guan Hai Xue, Shi Chun Chen, and Lei Lei. "Fatigue Life Prediction of Gear Based on Simulation Technology." Key Engineering Materials 324-325 (November 2006): 431–34. http://dx.doi.org/10.4028/www.scientific.net/kem.324-325.431.

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Dynamic analysis, finite element analysis and fatigue life analysis of transmission gear of Self-Propelled Gun is achieved in this paper according to the theory of multi-body dynamics, finite element and cumulative fatigue damage, and the well-known software Pro/E, ADAMS, PATRAN and FE-Fatigue are integrated in the research. The virtual prototyping model of self-propelled gun’s transmission box is built by ADAMS software. The dynamic load spectrum of transmission gear is achieved by virtual driving of Self-Propelled Gun. The finite element model of the gear is built by using PATRAN software, after defining reasonable boundary conditions, material and element properties, according to the load and the fatigue failure criterion of the gear, the stress-strain state of gear on load is studied. The dynamic load spectrum and the stress-strain state of the gear are considered as basic input data, the fatigue life of the gear is calculated by using FE-fatigue software. The road haul of gear without fault is predicted when the self-propelled gun drives on the second-class load surface at low speed. This method offers a new idea to the fatigue life prediction. It can predict fatigue life without experiments, and save cost and time. It has the great significance to the optimization design of the self-propelled gun.
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Zhang, Zhi Zeng, Yong Tao Li, and Xiao Chang Li. "Analysis on Surrounding Rock Stability of Joints Strike Parallel to the Cavern." Applied Mechanics and Materials 501-504 (January 2014): 1694–700. http://dx.doi.org/10.4028/www.scientific.net/amm.501-504.1694.

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In order to study the influence on the different parts of the cavern by joints, the three-dimensional model is built by Patran and then calculated with FLAC3D after meshing. Seven working conditions about different inclination of joints (0°15°30°45°60°75°90°) are considered in the calculation. The results show that low dip joints in vault and steep joints in the sidewall are more dangerous. Therefore, some measures should be used when encountered this situation in this project.
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Li, Ang, and Chun Jie Wang. "Construction of Lander Multidisciplinary Optimization Platform." Key Engineering Materials 407-408 (February 2009): 180–84. http://dx.doi.org/10.4028/www.scientific.net/kem.407-408.180.

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In the course of present space lander’s optimization, the problems, such as hardness of information integration, partiality of optimization, still exist. In order to solve these problems, Lander Multidisciplinary Optimization Platform has been built. Four engineering tools (Pro/Engineer, Patran, Nastran, ADAMS) are integrated into the platform based on optimization software—iSIGHT, which could ensure space lander’s kinematics and dynamics characteristics. Good optimum scheme is obtained after comprehensive optimization of the platform. Besides, the platform is managed by simulation management software—MSC.SimManage. Multidisciplinary optimization can be realized automatically through parameterized interface of the platform.
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Zhang, Ming, Rui Jiang, Chun Yang, and Li Cao. "Study on Dynamic Simulation of Buffering Mechanism with Liquid Bag." Applied Mechanics and Materials 397-400 (September 2013): 546–50. http://dx.doi.org/10.4028/www.scientific.net/amm.397-400.546.

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The finite element model of buffering mechanism with liquid bag is constructed using finite element software MSC. Patran. The liquid bag is clamped between the inner part and outer part, and the contact relation is modeled by contact method in the finite element software MSC. Dytran. An airbag module in MSC. Dytran is used to simulate the buffering effect of the liquid bag equivalently. Then dynamic simulation results is presented and compared with the experimental results. The validity of the model is verified and contributes to further analyses of liquid bag.
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Khine, Ei Ei, Yi Du Zhang, and Qiong Wu. "Investigation of Static Failure for Cemented Carbide Cylindrical End Mill." Advanced Materials Research 383-390 (November 2011): 1769–75. http://dx.doi.org/10.4028/www.scientific.net/amr.383-390.1769.

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Investigation of the cutting tool failure is one of the important factors in order to optimize the cutting parameters. This paper studies the cutting tool stresses (maximum principal, maximum shear and von Mises) at the shank and at the tip using three failure theories. These stresses are analyzed by means of the finite element method using MSC patran/nastran software and the experimental method using electrical-resistance strain gages. The comparison of the stresses obtained from these two methods for different feed rates and different rotation speeds are depicted in figures.
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Fojtík, František, Petr Ferfecki, and Zbyněk Paška. "Computer Aided Evaluation of the Stress Tensor in the Two-Dimensional Photoelasticity." Applied Mechanics and Materials 827 (February 2016): 181–84. http://dx.doi.org/10.4028/www.scientific.net/amm.827.181.

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Photoelasticity is a whole field experimental technique for the measurement and visualizing of the stress and strains in the loaded members. This work is intended to create a unique procedure that allows the use of a computer aided technique in the evaluation of the measurement results. The specimens of the thin annular disk, the thin disk and the shaped beam were tested. The PATRAN program is used for the finite element solution of stress analysis in the investigated specimens. The excellent agreement is established between the results of experimental technique based on the created computer procedure and the results of numerical computations.
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Van Doan, Do, Adam Szeleziński, Lech Murawski, and Adam Muc. "Modelling Method of Dynamic Characteristics of Marine Thin-Walled Structure." Journal of KONES 26, no. 4 (December 1, 2019): 39–46. http://dx.doi.org/10.2478/kones-2019-0087.

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AbstractThin-walled structures are very popular in industries, especially in the field of shipbuilding. There are many types of equipment and structures of ships, which are made up of thin-walled structures such as hull, deck and superstructure. Therefore, the analysis and understanding of the static and dynamic characteristics of a thin-walled structure are very important. In this article, we focus on vibration analysis of a typical thin-walled structure-rectangular plate, a basic structure of the hull. Vibration analysis of a rectangular thin plate is conducted by two methods: numerical modelling method of the finite element on Patran-Nastran software platform and experimental method implemented in the laboratory of Gdynia Maritime University. Thin rectangular plate is fixed one end by four clamping plates and is modelled with finite elements and different meshing densities. The numerical model of thin rectangular plate is divided into four cases. Case 1, thin rectangular plate, and clamping plates are modelled with two-dimensional elements. Case 2, the rectangular thin plate is modelled with two-dimensional elements; the clamping plates are modelled with three-dimensional elements. Case 3, both the rectangular thin plate and clamping plates are modelled with three-dimensional elements. Case 4, the rectangular thin plate, and clamping plates are modelled with three-dimensional elements with larger mesh density to increase the accuracy of the calculation results. After that, the results of vibration analysis according to the numerical modelling method on Patran-Nastran software platform for these cases were compared with the measurement results. From there, assess the accuracy of analysis results of selected numerical model methods and the ability to widely apply this numerical model method to other marine structures.
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Wang, Wei, and Zhi Jin Wang. "Optimum Design of the Launch Vehicle Composite Cross Beam Structure Based on Equivalent Model." Advanced Materials Research 160-162 (November 2010): 860–65. http://dx.doi.org/10.4028/www.scientific.net/amr.160-162.860.

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The iterative optimization method of using equivalent model is used to design launch vehicle payload bearing structure—composite cross beam. The strategy is based on the idea of the substitution of equivalent models for detailed models. Using the engineering software Patran/Nastran, optimization finds geometry of cross-sectional with a minimum weight and stacking sequences satisfying laminate design rules. Equivalent model method can decrease numbers of design variable as well as ensures reliability of result. The strategy showed weight savings of 38% compared with the initial design with little computational effort. This has demonstrated that the strategy appears efficient, reliable and extendable into the cross beam structure.
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Thanarasi, Karthigesu. "Thermal Analysis of CUBESAT in Worse Case Hot and Cold Environment Using FEA Method." Applied Mechanics and Materials 225 (November 2012): 497–502. http://dx.doi.org/10.4028/www.scientific.net/amm.225.497.

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One of the necessary parts of CubeSat’s design is the thermal analysis. It will provide the operating temperatures and their distribution for all devices inside the CubeSat. For decision, which temperature standard can be used for components it is necessary to know the maximum and the minimum value of the temperature. In virtue of these results the position of the all devices must be also optimized. Some methods of the thermal control are also proposed. Contrary to most subsystems the thermal subsystem is not independent of the others. All elements in the spacecraft have an influence on the thermal housekeeping by either emitting or absorbing energy or both respectively. The objective of thermal subsystem is to ensure that the spacecraft operate within the spacecraft operating temperature range. There are two types of thermal control technique; passive and active. Due to the size and power constraint of CubeSat, passive thermal control will be more suitable but analysis must be done in order to know that passive control is sufficient. The FEA methodology would be utilized in order to determine the spacecraft operating temperature within the range. To accomplish this, MSC Nastran Patran software will be used as the FEA modeling tool. The MD Patran will act as preprocessing tool whereas MD Nastran will act as post processing tool. If the simulated thermal range is deviates, temperature sensors and heaters will be mounted on the CubeSat to monitor the deviation. Alternatively, mounting Kapton tape onto the CubeSat structure and laying gold coating would be another method to maintain the desired temperature range. The design of the thermal system shall be based on passive methods. This approach is vital to avoid power consumption in cases where it would not be necessary. As conclusion the thermal subsystem is designed to operate the spacecraft throughout its mission phases without any failure.
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Lakhov, A. Y., and K. A. Lakhov. "TRANSLATION OF GEOMETRIC MODELS OF SINGLE-CONTOUR GEODESIC DOMES FROM ARCHICAD TO A NEUTRAL STEP FORMAT." Construction and industrial safety, no. 21 (73) (2021): 107–14. http://dx.doi.org/10.37279/2413-1873-2021-21-107-114.

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The methods of data exchange between CAD and CAE systems are described. The first method is using direct conversion, the second method is using neutral formats. The description of the modular system for designing and analysis the strength and stability of single-contour and double-contour geodesic shells GeoTran is given. The direct translation of geometric models from ArchiCAD to Patran/Nastran / Dytran has the disadvantage of having to develop translators for each data exchange scheme. It is proposed to implement the translation of geometric models in a neutral STEP format, which reduces the number of required translators. It is noted that the STEP format is recognized by various CAE systems that implement the finite element method (Autodesk Mechanical Desktop, Bentley Microstation, CATIA V4, CATIA V5, MSC Patran/Nastran, UGS PLM Solutions NX). The characteristics of the OBJ format used for storing a geometric model in the ArchiCAD CAD system and the STEP format used for data exchange with CAE systems are studied. A translator of geometric models of single-contour geodesic shells from ArchiCAD to STEP format in the Visual Basic programming language has been developed. For this purpose a syntactically oriented approach was used. The translator has a graphical user interface that makes it easier to use. The translator allows you to automate the exchange of data between the ArchiCAD CAD system and various CAE systems designed for strength analysis and supporting import from the STEP format. The applicability of the translator for the exchange of data on geometric models of single-contour geodesic domes with triangular plates between ArchiCAD and the Delcam Exchange converter program is verified. It is demonstrated that the STEP file format generated by the OBJSTEPTranslator is recognized by an external program.
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BARAN, Daniela, and Mihaela PETRE. "Hydrostatic pressure loads for a tank using “CID Distributed Loads” fields in a PATRAN FEM model." INCAS BULLETIN 13, no. 4 (December 5, 2021): 197–204. http://dx.doi.org/10.13111/2066-8201.2021.13.4.16.

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The purpose of this paper is to present a practical way to introduce distributed loads on the walls of a tank in order to perform a FEM analysis using PATRAN/NASTRAN programs. The problem is generated mainly by the fact that there are gravitational accelerations in the three directions of the moving airplane that produce a great number of combinations of inertial loads and consequently a great number of critical load cases. We compared the performed stress analysis with the loads obtained with this method in different cases for 𝑛𝑛=1. (Different forms of the fuel tanks and different placements of the tank inside the aircraft). The form and the density of the grid do not significantly affect the precision of the real inertia loads. Using the presented method one can reduce the volume of FEM files used in the analysis and can quite accurately reproduce the pressure loads on the fuel of a moving aircraft.
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29

Firly, Raden Rubani, Hendri Syamsudin, Muhammad Kusni, and Djarot Widagdo. "Numerical and Experimental Analysis of Flexural Properties of Bamboo Tali Laminate Composite." Advanced Materials Research 1125 (October 2015): 100–105. http://dx.doi.org/10.4028/www.scientific.net/amr.1125.100.

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This research was done to evaluate flexural properties (flexural strength, flexural modulus, and failure mode) of Bambu Tali (Gigantochloa Apus) composite. Lycal 1101 was used as matrix. Two types of laminate were tested in four point bending, unidirectional (00/00) s and symmetric cross ply (00/900) s. Results were then compared with numerical simulation using MSC PATRAN-NASTRAN to determine flexural strength and failure mode prediction for both specimens. All specimens were manufactured using cold press manufacturing method. Results show there was around 28% reduction in flexural strength from unidirectional specimen to symmetric cross ply. Numerical simulation results on failure mode prediction show good agreements with actual four point bending test.
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Lu, Yun Tong, Chun Jie Wang, Ang Li, and Han Wang. "Multidisciplinary Design Optimization of a Lunar Lander’s Soft-Landing Gear." Applied Mechanics and Materials 42 (November 2010): 118–21. http://dx.doi.org/10.4028/www.scientific.net/amm.42.118.

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The rapid development of Multidisciplinary Design Optimization (MDO) approach can simultaneously guarantee the cut of cost on design and optimal performance of spacecraft. Based on the theory of Collaborative Optimization approach (CO) of MDO, present paper proposes the method of CO by integrating Pro/E(3D modeling), Patran/Nastran(FEM analysis) and ADAMS(multi-body dynamic analysis) with the Isight software. In the analysis of the soft-landing gear of Lunar Lander, this method can optimize the mass of the landing gear and meanwhile ensures the reliability of structure statics, structure dynamics and multi-body dynamics. Thus the feasibility, applied value and guideline significance of this method in spacecraft structural design are proven.
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31

Zhen, Jun Wei, Ling Li Cui, and Xue Chen. "Mechanics Modeling for Bearing Rigid-Flexible Coupling Multi-Body System Based on ADAMS." Applied Mechanics and Materials 364 (August 2013): 124–28. http://dx.doi.org/10.4028/www.scientific.net/amm.364.124.

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Rigid-flexible coupling model is the most common mechanics model for multi-body system, and discovering the law of multi-body system modeling is an important part of the study on multi-body mechanics. This paper uses finite element analysis software PATRAN to make flexibility treatment on the parts of deep groove ball bearing, combines with the virtual prototype technology and establishes the multi-flexibility body rigid-flexible coupling model which can truly reflect the dynamic characteristics of the bearing, and discusses the process and the matters needing attention for generating modal neutral file, realizes the precise modeling for fault bearing, and provides a new method for using virtual prototype to create model.
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32

Hartini, Dwi. "ANALISIS ELEMEN HINGGA UNTUK FAKTOR KONSENTRASI TEGANGAN PADA PELAT ISOTROPIK BERLUBANG DENGAN PIN-LOADED." Angkasa: Jurnal Ilmiah Bidang Teknologi 8, no. 1 (August 31, 2017): 69. http://dx.doi.org/10.28989/angkasa.v8i1.133.

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Hole in the structure is often a serious problem, because the hole would trigger a surge in stress concentration which resulted cracks in the structure. In this research will analyze the stress concentration factor on isotropic plate with hole. The method used is numeric method. The technique used to collect data is the study of literature and comparative study of several similar research. Then the design is modeled and analyzed using Patran/Nastran. Based on this analysis the final result obtained is a mathematical equation that can be used to predict the stress concentration factor at the isotropic plate with hole where the results approached to Peterson distribution is used as reference in this research.
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33

Yu, Cheng Guo, Zhen Hua Chen, and Xu Tao Nie. "Multi-Jack Single-Drive Semi-Flexible Nozzle Mechanism Design and Simulation." Advanced Materials Research 503-504 (April 2012): 892–95. http://dx.doi.org/10.4028/www.scientific.net/amr.503-504.892.

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In order to reduce the cost of wind tunnel construction, simplify the requirement of control, and increase the security in the operation of nozzle, the multi-jack single-drive semi-flexible nozzle is designed. Based on the planar linkage design theory, the movement of multi-jack semi-flexible nozzle with single drive organ was achieved by using the software of MATLAB. Furthermore, the rigid-flexible coupling kinematics simulation of multi-jack single-drive semi-flexible nozzle is done to testify the rationality of the mechanism design by using the software of ADAMS and PATRAN/NASTRAN. The comparisons of four Mach numbers show that the simulation surfaces have good agreements with the aerodynamics surfaces.
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34

Xu, Ke Jun, Yong Qi Wang, Yi Rui Xia, and Ming Ming Jia. "The Stress Calculating and Analysis of the Second HP Turbine Disc of a Certain Type of Aeroengine." Applied Mechanics and Materials 331 (July 2013): 176–80. http://dx.doi.org/10.4028/www.scientific.net/amm.331.176.

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This paper takes the 2nd HP turbine disc of an aeroengine as research object, construct its finite element model in software-Patran. According to the work environment of 2nd HP turbine disc, the boundary conditions of stress field analysis and temperature field analysis are confirmed. Based on the finite element theory of thermal analysis and structure analysis, we use finite element software-Nastran to analyze centrifugal stress and thermal stress. Numerical calculation method was used to fit the data and finally we got the thermal elastic stress field. According to the computed results, the life assessment points of disc were confirmed. The static strength of 2nd HP turbine disc was tested based on the EGD-3 criterion. All the work established the foundation for subsequent life analysis.
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Zhang, Chao Ying, Hu Liu, and Yun Peng Ma. "Optimization of Aircraft Mid-Fuselage Structure Design Based on Parametric Modeling." Advanced Materials Research 933 (May 2014): 423–27. http://dx.doi.org/10.4028/www.scientific.net/amr.933.423.

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In aircraft preliminary design, fuselage structure design is important, and to reach the lightest weight is the main target for aircraft design, especially for civil aircraft. Based on CAD/CAE technology, the paper selects a typical structure layout form of aircraft mid-fuselage to study the method of structure model quickly creation and optimization. First, it focuses on fuselage parameterized modeling method, based on CATIA secondary development technology, to create the mid-fuselage parametric model. Then, based on Patran command language, the CAD model achieves automatic meshing. Finally, selecting an appropriate strategy and using iSIGHT integrated with fuselage parametric model and finite element model, and referring to the calculated the structural response by Nastran to realize mid-fuselage structure optimization.
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36

Manuylov, Gaik, Sergey Kosytsyn, and Irina Grudtsyna. "INFLUENCE OF BUCKLING FORMS INTERACTION ON STIFFENED PLATE BEARING CAPACITY." International Journal for Computational Civil and Structural Engineering 16, no. 2 (June 26, 2020): 83–93. http://dx.doi.org/10.22337/2587-9618-2020-16-2-83-93.

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The work is devoted to studying the influence of initial geometric imperfections on a value of the peak load for the compressed stiffened plate with the two-fold buckling load. The finite-element set MSC PATRAN – NASTRAN was used for solving the set tasks. When modelling the stiffened plate, flat four-unit elements were used. Geometric non-linearity was assumed for calculations. The plate material was regarded as perfectly elastic. Buckling forces of stiffened plate at the two-fold buckling load were calculated (simultaneous buckling failure on the form of the plate total bending and on the local form of wave formation in stiffened ribs). Equilibrium state curves, peak load decline curves depending on initial imperfection values and the bifurcation surface were plotted.
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37

Manuylov, Gaik A., Sergey B. Kositsyn, and Irina E. Grudtsyna. "Numerical analysis of stability of the stiffened plates subjected aliquant critical loads." Structural Mechanics of Engineering Constructions and Buildings 16, no. 1 (December 15, 2020): 54–61. http://dx.doi.org/10.22363/1815-5235-2020-16-1-54-61.

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The aim of the work is to research the precritical and postcritical equilibrium of the stiffened plates subjected aliquant critical loads. Methods. The finiteelement complex MSC PATRAN - NASTRAN was used in the paper. To simulate the plates, flat four-node elements were used. Calculations taking into account geometric nonlinearity were carried out. The material of the shells was considered absolutely elastic. Results. A technique has been developed to study the stability of reinforced longitudinally compressed plates; the critical forces of the stiffened plates of various thicknesses had been calculated. Graphs of deflections dependences on the value of the compressive load had been constructed. The influence of initial geometric imperfections on the value of the critical loads for stiffened plates has been investigated.
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38

Han, Xue Feng, Yang Bai, Ming Li, and Hong Guang Jia. "Alternating Stress Dynamics Analysis of Harmonic Gear Flexible Wheel." Advanced Materials Research 546-547 (July 2012): 102–9. http://dx.doi.org/10.4028/www.scientific.net/amr.546-547.102.

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This article is the study of alternating stress of flexible wheel in harmonic gear drive system. Firstly, according to elasticity theory to theoretically analyze flexible wheel stress; then, based on the basic principle of sub-structure modal synthesis method , use the software of UG、PATRAN and ADAMS to carry out co-simulation; Finally, based on the dynamics simulation, to analyze the alternating stress simulation results of flexible wheel and compare theoretical results and simulation results to come conclusion. The results show that: altering stress simulation results of flexible wheel are coincident with theoretical simulation results, have a deeper understand the stress change trend in the drive process of flexible wheel, lay a foundation for further carrying out dynamics simulation of harmonic gear drive system.
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39

Pavan, G., and N. Kishore. "Static and Fatigue Analysis on a Wing Spar Joint for a Light Jet Aircraft Structure Using 2024 T351 Material." Applied Mechanics and Materials 895 (November 2019): 244–52. http://dx.doi.org/10.4028/www.scientific.net/amm.895.244.

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The main objective of this paper is to present prototype of wing spar joint using CATIA V5 software to study the behavior of wing spar joint as per actual working condition and to perform structural analysis of the wing spar joint based on condition of cyclic loading (fatigue loading). Determining the loading modes in the spar joint is subjected to static load and fatigue loads which should be taken into account in the evaluation of the strength and fatigue life. Initially, the components were modeled with CATIA V5 and imported to MSC PATRAN; MSC NASTRAN is used as a solver. From the obtained maximum tensile stresses, fatigue analysis was carried out to find fatigue life of the spar joint with different fatigue load spectra.
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40

Ye, Hongling, Ning Chen, Yunkang Sui, and Jun Tie. "Three-Dimensional Dynamic Topology Optimization with Frequency Constraints Using Composite Exponential Function and ICM Method." Mathematical Problems in Engineering 2015 (2015): 1–10. http://dx.doi.org/10.1155/2015/491084.

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The dynamic topology optimization of three-dimensional continuum structures subject to frequency constraints is investigated using Independent Continuous Mapping (ICM) design variable fields. The composite exponential function (CEF) is selected to be a filter function which recognizes the design variables and to implement the changing process of design variables from “discrete” to “continuous” and back to “discrete.” Explicit formulations of frequency constraints are given based on filter functions, first-order Taylor series expansion. And an improved optimal model is formulated using CEF and the explicit frequency constraints. Dual sequential quadratic programming (DSQP) algorithm is used to solve the optimal model. The program is developed on the platform of MSC Patran & Nastran. Finally, numerical examples are given to demonstrate the validity and applicability of the proposed method.
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41

Rathi, Ankita. "Deras Beyond Caste: Remedies for Developmental Pressures." South Asia Research 40, no. 3 (September 1, 2020): 416–33. http://dx.doi.org/10.1177/0262728020944785.

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In the northern regions of India, the rising popularity of alternative religious sects, prominently Deras, has sparked much interest in explaining this phenomenon. Current literature, based on case studies of specific Dalit Deras, relates the emergence of these religious sects to caste-based social discrimination and exclusion of lower castes by the mainstream Sikh religion. This article presents a case study of a small town, Patran, in the state of Punjab. Confirming the popularity of these alternative religious sects for upper and lower castes in the town, the article argues that the contemporary attractiveness of Deras needs to be understood also as a result of localised agrarian dynamics and related social pressures engendered by the process of rural to urban and agrarian to non-agrarian transition.
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., K. S. Vishwanath Vashisht. "DAMAGE TOLERANCE EVALUATION OF AN AIRCRAFT SKIN STRUCTURE BY MVCCI TECHNIQUE (2D ANALYSIS) USING MSC – NASTRAN / PATRAN." International Journal of Research in Engineering and Technology 05, no. 05 (May 25, 2016): 510–16. http://dx.doi.org/10.15623/ijret.2016.0505096.

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43

Zhou, Jie, Ji Sheng Ma, Zhong Xing Sun, and Cai Gang Wu. "Dynamic Simulation of the Movement of the Rocket Launch Tower on ADAMS Based on the Material of the Tower." Advanced Materials Research 625 (December 2012): 3–6. http://dx.doi.org/10.4028/www.scientific.net/amr.625.3.

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The rocket launch tower’s movement involve opening and closing.During these two process,the tower shakes severely. This study using ADAMS to simulate the movement of the tower and finding that the material of the tower’s components showing a characteristic of flexibility, the material’s characteristic of flexibility of the tower is a main reason of the vibration. In oreder to establish the rocket launch tower’s model,using Pro/E and Mech/pro to create the model.Then ,with the use of mechanical system simulation software ADAMS and finite element analysis software, Patran / Nastran to simulate the rocket launch tower’s movement. The results showed that although the rocket launch tower’s material is steel,it’s main components still showing the flexible feature. And its various components’ influence of flexibility for the tower’s vibration are quite different from each other.
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44

Guan, Peng, Yu Tao, Wei Wang, and Wan Shan Wang. "Research on Dynamic Characteristics Analysis of the Whole Grinding Machine Tool Based on FEM." Advanced Materials Research 472-475 (February 2012): 2874–78. http://dx.doi.org/10.4028/www.scientific.net/amr.472-475.2874.

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Dynamic characteristics is the foundation of the dynamic design of the machine tool, while the key factor of establishing the accurate dynamic model of the machine tool is the treatment of the joint surface. In this paper, the whole machine tool model is built with the software PRO/ E, and the software MSC. Patran is used to mesh the finite element of super-high-speed grinder and set up the boundary conditions. Then Yoshimura method is used to determine the junction parameters and establish the dynamic model of the junction. The software MSC. Nastran is used to analyze the modal of the whole machine. At last, on basis of identifying the weaknesses of the structure of the machine tool, the paper provides a theoretical basis for the improvement of the machine tool design.
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45

Ai, Yan Ting, Yan Bai, Xue Zhai, and Dan Zhao. "Finite Element Simulation in the Dynamics Calculation of Bolted-Joint Interface." Applied Mechanics and Materials 215-216 (November 2012): 1009–12. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.1009.

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Many components in modern mechanical structure are connected with bolts, and the behaviour of joints significantly affects the dynamic response of these structures. Based on the software of MSC. patran, firstly, a linear dynamic model for bolted joints and interface is developed. The joint interface is modeled using a technology of interface layer element(ILE) and multi-point constrains(MPC) technique. And then, using the MATLAB language, the properties of ILE material are optimized to simulate the bolted-joint interface stiffness. The material properties parameters are identified by using experimental data. This work takes aero-engine case model as an example, researching its model analysis under different pre-stress conditions to check the method and provide insight on how to model the joint interface in the dynamics calculation of bolted structure.
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Liu, Xiao Chao, Da Zheng Wang, Lei Mei, and Qiang Ma. "Equivalent Research on Main Components of FRP Fishing Boat." Materials Science Forum 1001 (July 2020): 121–26. http://dx.doi.org/10.4028/www.scientific.net/msf.1001.121.

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Fiberglass reinforced plastic fishing boats is a new type of energy saving and emission reduction boats, which is a significant revolution of fishing craft. However, the design of FRP fishing vessels in China continue to use the similar method employed by steel fishing vessels, which ignores the designability of fiberglass, leading to the light and high strength characteristic of glass fiber buried. the typical structure of FRP boats were analyzed, including the study on the influence of core material on the mechanical properties of cap type girder and the feasibility by using the equal sectional dimension in the Patran software of beam element to equivalent simulate the cap-type material, which simplified the whole ship building process of the finite element model and improved the computational efficiency in this pape.
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47

Xu, Jie, and Jian Guo Cao. "An Analysis on the Failure of Bearing Coordination." Applied Mechanics and Materials 271-272 (December 2012): 757–61. http://dx.doi.org/10.4028/www.scientific.net/amm.271-272.757.

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There are many forms of bearing failure. One of the forms often arises in engineering is that the outer ring of heavy-duty bearing and the corresponding wheel hub generating relative motion. In this article, AutoCAD was used to establish the three-dimensional model of the hub and bearing. With the help of HyperWorks, meshing, setting properties and imposing constraints to three-dimensional model were done. Then the model was imported into Patran to set the exposure and parameters. Therefore, the complete finite element model of was established. And then it was solved using SOL600. Finally, the calculation results were analyzed, and we found out the reason for the failed bearing. Finally, by analyzing the calculation results, the reason for the failure of the bearing was found out. This paper is of certain practical significance and theoretical engineering guiding value.
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48

Wang, Wei, Zhou Zhou, and Xiao Ping Zhu. "Solar Array Mounting Effects on Flutter Characteristics of Solar-Powered UAV." Advanced Materials Research 940 (June 2014): 410–14. http://dx.doi.org/10.4028/www.scientific.net/amr.940.410.

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Solar powered UAV has the characteristics of high aspect ratio, low structural surface density, high structural flexibility and low flutter speed. Different solar array mountings will affect the flutter characteristics of the structure. The mechanical properties of solar arrays packaged and unpackaged are measured in this paper and the solar powered UAV structural finite element model based on Patran/Nastran was also established in the paper. Two solar array mounting ways are researched: embedded solar arrays and patching solar arrays. To investigate the flutter characteristics under the two solar array mounting ways, the Doublet lattice method (DLM) aerodynamic model is used to model the unsteady aerodynamic loads. Finally, flutter speed of the structure was determined by using the P-K method and the analysis result indicate that patching solar arrays is more conductive to improve the flutter characteristics of the structure.
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Hartini, Dwi, Buyung Junaidin, and Habibi Habibi. "STRENGTH ANALYSIS OF CARGO-X UAV WING STRUCTURE USING SANDWICH COMPOSITE MATERIALS." Vortex 3, no. 1 (January 15, 2022): 1. http://dx.doi.org/10.28989/vortex.v3i1.1153.

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The Cargo-X UAV aircraft is a UAV aircraft designed to carry medicines, packages and blood bags in areas that require fast and efficient handling. One of the important components of the Cargo-X UAV aircraft is the wing, so the strength of the wing structure must be seriously considered to ensure safety during flight under unexpected conditions. The purpose of this study was to analyze the wing structure of the UAV Cargo-X aircraft made of sandwich composite material to determine the level of safety of the wing structure. The loading of the wing structure uses the load due to the lift. The wing structure modeling uses CATIA software, while the analysis uses PATRAN/NASTRAN software. From the analysis results, the skin and spar wing structures are safe against loading, while the core section is not safe against loading.
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Chen, Shi Cai, Xiao Ming Tian, and Chun Yang Liu. "Thermomechanical Analysis System for Building Structures under Fire Based on MSCPATRAN Platform." Advanced Materials Research 243-249 (May 2011): 6159–64. http://dx.doi.org/10.4028/www.scientific.net/amr.243-249.6159.

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In order to analyze the behavior of building structures in a real fire, a numerical method is proposed, which employs fire zone model to simulate the fire growing and the temperature distributions in a firing room. Two computer programs are developed to predict the thermomechanical response of the structures, one for thermal response analysis, and another for structural analysis. The structural analysis program contains a fiber beam element and a layered shell element. These elements, validated against data from experimental tests, can be used to predict the response of beam/column and slabs in fire conditions. Based on these programs, a system for analyzing the behavior of structures under fire is developed on MSC/PATRAN platform. The behavior of building structures under fire can be simulated with this system and the results can be used as the reference for the fire safety analysis and assessment of general building structures under fire.
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