Relevant bibliographies by topics / Patran-Nastran

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Conference papers
  5. Reports

Academic literature on the topic 'Patran-Nastran'

Author: Grafiati
Published: 20 February 2023

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Patran-Nastran.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Patran-Nastran"

1

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
2

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
3

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
4

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
5

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
6

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.

Full text
Abstract:
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
APA, Harvard, Vancouver, ISO, and other styles
7

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
8

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
9

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
10

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.

Full text
Abstract:
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.
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Patran-Nastran"

1

Knott, George Anthony. "A Modal Analysis of the Violin Using MSC/NASTRAN and PATRAN." Thesis, Monterey, California: Naval Postgraduate School, 1987. http://hdl.handle.net/10945/14837.

Full text
Abstract:
The MSC/NASTRAN finite element computer program and a Cray XMP computer were used to study the modal characteristics of a violin with the Stradivari shape . The violin geometry was modeled using an arcs of circles scheme with PATRAN, a finite element graphics pre/postprocessor program. The violin was modeled in-vacu and with free boundry conditions. Belly, back, sound post, bassbar, neck, bridge, tail-piece, strings, rib linings, end and corner blocks are the components of the model. Mode shapes and frequencies were calculated for free top and back plates, the violin box, and the complete violin system, including the strings . The results obtained from the finite element technique were compared to experimental data from real violins collected by other investigators.
APA, Harvard, Vancouver, ISO, and other styles
2

CARO, DIAZ FREDDY SANTIAGO. "ANALYSIS OF FLUID STRUCTURE-INTERACTION (FSI) PROBLEMS IN ANSYS." Thesis, Faculty of Engineering and Information Technologies. School of Aerospace, Mechanical & Mechatronic Engineering, 2015. https://hdl.handle.net/2123/30023.

Full text
Abstract:
The Fluid-Structure Interaction problems occur in many natural phenomena and man-made engineering systems, this fact has promoted the research in this area. The research in this field of study is implementing two different methodologies. The first one is the use of commercial programs that have developed FSI capabilities such as Ansys or ADINA. The second methodology is the development of computational codes to solve specific problems of FSI analysis. This Project in particular focuses in the evaluation of Ansys-Fluent to perform FSI simulations. Two aeroelastic cases were simulated in Ansys, they were: the delta wing, and the Onera M6 wing. The delta wing simulation is subsonic and its structure is a simple flat plate made out of aluminum. The Onera M6 wing simulation is transonic and its structure has multiple components that are made out of an orthotropic material. The FSI simulations of the delta wing were validated through comparison with experimental data reported in literature. A turbulence analysis and a mesh independence analysis were carried out as well. The validation showed a limited capability to replicate the results that were obtained in the experiment. The FSI simulations of the Onera M6 wing were validated through comparison with a simulation that was carried out in Patran-Nastran. In addition, a computational fluid dynamics (CFD) simulation in steady state was performed in Ansys in order to establish the bases of the configuration that was implemented in the FSI simulations in Ansys. The validation showed that Ansys-Fluent is able to reproduce the results obtained in Patran-Nastran.
APA, Harvard, Vancouver, ISO, and other styles
3

Beruashvili, Vasili. "Topologická optimalizace závěsu na poddajném podkladu." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2020. http://www.nusl.cz/ntk/nusl-417913.

Full text
Abstract:
Tato diplomová práce se zabývá modifikací původního tvaru součásti za účelem co nejlepšího splnění provozních podmínek daného zatížení a omezujících podmínek v programech M.S.C. NASTRAN, M.S.C. PATRAN a FUSION 360. Součást je připevněna na ortotropní desce (sendvičovém panelu). Cílem této práce je zjištění efektu elastického podkladu na výsledky optimalizace. Součást bude optimalizována za použití různých cílových funkcí a omezení. Elastický podklad změní tuhost, což může změnit napěťový stav součásti. Únosnost původního a modifikovaného tvaru bude srovnána pomocí programu M.S.C NASTRAN/PATRAN. Po tvarové optimalizaci má být 3D model připravený pro výrobní proces, který bude cenově nejefektivnější.
APA, Harvard, Vancouver, ISO, and other styles
4

Konečný, Michael. "Porovnání analytického a numerického MKP řešení vzpěrné stability laminátových kompozitních válcových skořepin." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2013. http://www.nusl.cz/ntk/nusl-230525.

Full text
Abstract:
Tato práce zkoumá možností řešení kritické síly vzpěrné stability laminátových kompozitních válcových skořepin jak analytickým tak MKP přístupem. Analytické řešení je prezentováno detailně a je zpracován Matlab program pro jeho výpočet. MKP řešení je prováděno ve dvou řešičích softwaru MSC.Nastran, jsou zjišťována vhodná nastavení těchto řešičů a jejich chování. Všechny způsoby řešení jsou na závěr porovnány a je navrženo několik závěrů.
APA, Harvard, Vancouver, ISO, and other styles
5

Sikström, Johannes. "Vibro-acoustic analysis of a satellite reflector antenna using FEM." Thesis, Umeå universitet, Institutionen för fysik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:umu:diva-39875.

Full text
Abstract:
The acoustic environment generated during launch is the most demanding structural load case for large, lightweight satellite reflector antennas. The reflector is exposed to extremely high sound pressure levels originating from the structural excitation of the rocket engines and exterior air flow turbulence. This thesis aims to predict the structural responses in the reflector due to the acoustic pressure load with a model based on Finite Element Modelling (FEM). The FE-model is validated against a previously performed Boundary Element Method (BEM) analysis. An approach called Split Loading together with a combination of BEM and FEM will be utilized to handle the surrounding air mass and the applied sound pressures. The idea of Split Loading is to divide the structure into several patches and apply a unit pressure load to each patch separately. In the last step the unit pressure is scaled and correlated by a power spectral density calculated from the acoustic pressures. Split Loading will be implemented in software packages MSC.NASTRAN/PATRAN. The model developed in this thesis handles both the added mass of the surrounding air and the sound pressure applied to the reflector. The model can qualitatively well reproduce the results of the BEM-analysis and the test data. However, the model tends to overestimate responses at low frequencies and underestimate them at high frequencies. The end results is that the model becomes too conservative at low frequencies to be used without further development.
APA, Harvard, Vancouver, ISO, and other styles
6

Pecorella, Daniele. "Methodology for the design and optimization of a morphing wing droop-nose structure for greener aircraft." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2022.

Find full text
Abstract:
Droop-Nose Leading Edge (DNLE) morphing wings are one of the most promising devices in order to achieve aerodynamic drag and noise reduction during take-off and landing phases. An accurate design of these structures could lead to the decrease of aircraft fuel consumption in the perspective of reaching a greener aviation, following the objectives indicated by Flightpath 2050 issued by the E.U. However, due to the challenges related to the realization of this technology and TRL reached, DNLE are more likely implemented in Unmanned Aerial Systems (UAS) for testing and evaluation purposes. In the present study, an optimization methodology for the DNLE composite laminate skin and morphing mechanism structure is proposed and applied to a study case represented by the UAS-S45 aircraft. The work starts from the morphing leading edge structure developed by the LARCASE laboratory at ETS Montreal. The results showed that by means of the optimization strategy adopted, the force required on the actuator mechanism is 88% lower than the original design. A significant improvement on the profile smoothness along its section and in the spanwise direction in morphing conditions has been obtained too. However, further investigations are still needed in order to achieve a more appropriate morphing shape. Despite this, it appears from the results obtained that the proposed methodology can be useful to tackle the DNLE design problem in an effective and efficient way. What developed in this work has been conceived to support the investigation of DNLE in the small leading edge profiles typical of the UAS. In this way, an easier procedure for the set up of the design flow, and a decrease in the computational effort for the optimization process can be obtained. An experimental validation of the results obtained is currently being performed at ETS, and future development regards the assessment of the errors of the numeric procedure herein presented respect to real data.
APA, Harvard, Vancouver, ISO, and other styles
7

Kunicka, Beata Iwona. "Spacecraft dynamic analysis and correlation with test results : Shock environment analysis of LISA Pathfinder at VESTA test bed." Thesis, Luleå tekniska universitet, Rymdteknik, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:ltu:diva-62910.

Full text
Abstract:
The particular study case in this thesis is the shock test performed on the LISA Pathfinder satellite conducted in a laboratory environment on a dedicated test bed: Vega Shock Test Apparatus (VESTA). This test is considered fully representative to study shock levels produced by fairing jettisoning event at Vega Launcher Vehicle, which induces high shock loads towards the satellite. In the frame of this thesis, some transient response analyses have been conducted in MSC Nastran, and a shock simulation tool for the VESTA test configuration has been developed. The simulation tool is based on Nastran Direct Transient Response Analysis solver (SOL 109), and is representative of the upper composite of Vega with the LISA Pathfinder coupled to it. Post-processing routines of transient response signals were conducted in Dynaworks which served to calculate Shock Response Spectra (SRS). The simulation tool is a model of forcing function parameters for transient analysis which adequately correlates with the shock real test data, in order to understand how the effect of shock generated by the launcher is seen in the satellite and its sub-systems. Since available computation resources are limited the parameters for analysis were optimised for computation time, file size, memory capacity,  and model complexity. The forcing function represents a release of the HSS clamp band which is responsible for fairing jettisoning, thus the parameters which were studied are mostly concerning the modelling of this event. Among many investigated, those which visibly improved SRS correlation are radial forcing function shape, implementation of axial impulse, clamp band loading geometry and refined loading scheme. Integration time step duration and analysis duration were also studied and found to improve correlation.  From each analysis, the qualifying shock environment was then derived by linear scaling in proportion of the applied preload, and considering a qualification margin of 3dB. Consecutive tracking of structural responses along shock propagation path exposed gradual changes in responses pattern and revealed an important property that a breathing mode (n = 0) at the base of a conical Adapter translates into an axial input to the spacecraft. The parametrisation itself was based on responses registered at interfaces located in near-field (where the clamp band is located and forcing function is applied) and medium-field with respect to the shock event location. Following shock propagation path, the final step was the analysis of shock responses inside the satellite located in a far-field region, which still revealed a very good correlation of results. Thus, it can be said that parametrisation process was adequate, and the developed shock simulation tool can be qualified. However, due to the nature of shock, the tool cannot fully replace VESTA laboratory test, but can support shock assessment process and preparation to such test. In the last part of the thesis, the implementation of some finite element model improvements is investigated. Majority of the panels in spacecraft interior exhibited shock over-prediction due to finite element model limitation. Equipment units modelled as lump masses rigidly attached with RBE2 elements to the panel surface are a source of such local over-predictions. Thus, some of the units were remodelled and transient responses were reinvestigated. It was found that remodelling with either solid elements, or lump mass connected to RBE3 element and reinforced by RBE2 element, can significantly improve local transient responses. This conclusion is in line with conclusions found in ECSS Shock Handbook.
APA, Harvard, Vancouver, ISO, and other styles
8

WU, YU-XING, and 吳育興. "PATRAN & MSC/NASTRAN 與整合電腦輔助設計與分析." Thesis, 1989. http://ndltd.ncl.edu.tw/handle/95171753250872524558.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Pieterse, Justin Lee. "Design and development of a composite ventral fin for a light aircraft / Justin Lee Pieterse." Thesis, 2015. http://hdl.handle.net/10394/16019.

Full text
Abstract:
The AHRLAC aircraft is a high performance light aircraft that is developed and manufactured in South Africa by Aerosud ITC in partnership with Paramount. This aircraft is the first of its kind to originate from South Africa. The aircraft has a twin boom, tandem pilot seating configuration, with a Pratt and Whitney turbine-propeller engine in a pusher configuration. The main structure of the aircraft is a conventional metallic structure, while the fairings and some secondary structures are composite. This study will focus on the design and development of the composite ventral fin of the first prototype aircraft, the experimental demonstrator model (XDM). It is crucial to ensure that the ventral fin can function safely within the design requirements of the aircraft under the loads which the fin is likely to encounter. Preceding the design process, a critical overview of composite materials used in aircraft applications is provided. This will include the materials, manufacturing methods, analysis and similar work done in this field of study. The literature will be used in the study for decision-making and validation of proven concepts and methodologies. The first part of this study entailed choosing a suitable composite material and manufacturing method for this specific application. The manufacturing method and materials used had to suit the aircraft prototype application. The limitations of using composite materials were researched as to recognize bad practice and limit design flaws on the ventral fin. Once the material and manufacturing methods were chosen, ventral fin concepts were evaluated using computer aided finite element analysis (FEA) with mass, stiffness and strength being the main parameters of concern. The load cases used in this evaluation were given by the lead structural engineer and aerodynamicist. The calculations of these loads are not covered in detail in this study. The FEA input material properties used, were determined by material testing by the relevant test methods. The ventral fin concept started as the minimal design with the lowest mass. The deflections, composite failure and fastener failure were then evaluated against the required values. The concept was modified by adding stiffening elements, such as ribs and spars, until satisfactory results were obtained. In this way a minimal mass component is designed and verified that it can adequately perform its designed tasks under the expected load conditions. Each part used in the ventral fin assembly was not individually optimized for mass, but rather the assembly as a whole. The final concept was modelled using the computer aided design software, CATIA. This model used in combination with a ply book made it possible to manufacture the ventral fin in a repeatable manner. A test ventral fin was manufactured using the selected materials and manufacturing methods to validate the design methodology. In the next step the selected load cases were used in static testing to validate the FEM through comparison. The result of the study is a composite ventral fin of which the mass, stiffness and strength are suitable to perform its function safely on the first prototype AHRLAC aircraft. The study concludes on the process followed from material selection to FEA and detail design, in order for this same method to be used on other AHRLAC XDM composite parts.
M (Mechanical Engineering), North-West University, Potchefstroom Campus, 2015
APA, Harvard, Vancouver, ISO, and other styles
10

Joe, John. "Parametric Design & an Approach to Weight Optimization of a Metallic and Carbon Fiber Wing." Thesis, 2019. http://hdl.handle.net/1805/19978.

Full text
Abstract:
Indiana University-Purdue University Indianapolis (IUPUI)
In a multifidelity structural design process, depending on the required analysis, different levels of structural models are needed. Within the aerospace design, analysis and optimization community, there is an increasing demand for automatic generation of parametric feature tree (build recipe) attributed multidisciplinary models. Currently, this is mainly done by creating separate models for different disciplines such as mid-surface model for aeroelasticity, outer-mold line for aerodynamics and CFD, and built-up element model for structural analysis. Since all of these models are built independently, any changes in design parameters require updates on all the models which is inefficient, time-consuming and prone to deficiencies. In this research, Engineering Sketch Pad (ESP) is used to create attribution and maintain consistency between structural models with different fidelity levels. It provides the user with the ability to interact with a configuration by building and/or modifying the design parameters and feature tree that define the configuration. ESP is based an open-source constructive solid modeler, named OpenCSM, which is built upon the OpenCASCADE geometry kernel and the EGADS geometry generation system. The use of OpenCSM as part of the AFRL’s CAPS project on Computational Aircraft Prototype Syntheses for automatic commercial and fighter jet models is demonstrated. The rapid generation of parametric aircraft structural models proposed and developed in this work will benefit the aerospace industry with coming up with efficient, fast and robust multidisciplinary design standardization of aircraft structures. Metallic aircraft wings are usually not optimized to their fullest potential due to shortage of development time. With roughly \$1000 worth of potential fuel savings per pound of weight reduction over the operational life of an aircraft, airlines are trying to minimize the weight of aircraft structures. A stiffness based strategy is used to map the nodal data of the lower-order fidelity structural models onto the higher-order ones. A simple multi-fidelity analysis process for a parametric wing is used to demonstrate the advantage of the approach. The loads on the wing are applied from a stick model as is done in the industry. C program is created to connect the parametric design software ESP, analysis software Nastran, load file and design configuration file in CSV format. This problem gets compounded when it comes to optimization of composite wings. In this study, a multi-level optimization strategy to optimize the weight of a composite transport aircraft wing is proposed. The part is assumed to initially have some arbitrary number of composite super plies. Super plies are a concept consisting of a set of plies all arranged in the same direction. The thickness and orientation angles of the super plies are optimized. Then, each ply undergoes topometry optimization to obtain the areas of each super ply taking the least load so that it could be cut and removed. Each of the super plies are then optimized for the thickness and orientation angles of the sub plies. The work presented on this paper is part of a project done for Air Force Research Laboratory (AFRL) connecting the parametric geometry modeler (ESP) with the finite element solver (Nastran).
APA, Harvard, Vancouver, ISO, and other styles

Books on the topic "Patran-Nastran"

1

Knott, George Anthony. A modal analysis of the violin using MSC/NASTRAN and PATRAN. Monterey, Calif: Naval Postgraduate School, 1987.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
2

Sucharitpwatskul, Sedthawat, and Pramote Dechaumphai. Finite Element Analysis with PATRAN / MSC NASTRAN. Alpha Science International, Limited, 2020.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
3

Msc. Msc - Patran Msc - Nastran Preference Guide Vol. 2: Thermal Analysis. MacNeal-Schwendler Corporation, the, 1997.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
4

Perel, Victor. Introduction to Stability Analysis of Elastic Structures with MSC Patran/Nastran and Abaqus CAE. Independently Published, 2022.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
5

National Aeronautics and Space Administration (NASA) Staff. Strategy for Integrating a Large Finite Element Model Using Msc Nastran/Patran: X-33 Lessons Learned. Independently Published, 2018.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
6

George C. Marshall Space Flight Center., ed. A strategy for integrating a large finite element model using MSC NASTRAN/PATRAN: X-33 lessons learned. [Huntsville, Ala.]: National Aeronautics and Space Administration, Marshall Space Flight Center, 1999.

Find full text
APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Patran-Nastran"

1

Shah, M. A. S. Aziz, M. A. Yunus, and M. N. Abdul Rani. "A comparison of FE modelling techniques of composite structure using MSC Patran/Nastran software." In Proceeding of 2nd International Colloquium on Computational & Experimental Mechanics (ICCEM 2021). AIP Publishing, 2022. http://dx.doi.org/10.1063/5.0103287.

Full text
APA, Harvard, Vancouver, ISO, and other styles
2

Blyukher, Boris, Tadeusz Niezgoda, Jerzy Malachowski, and Wieslaw Szymczyk. "Computer Simulation of Pipeline Deformations on the Basis of Data From an Intelligent Caliper Inspection Tool." In ASME 2003 Pressure Vessels and Piping Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/pvp2003-1917.

Full text
Abstract:
The method of pipeline inspection data usage for needs of numerical analysis of technical condition of pipeline is considered. A real crude oil pipeline was taken into considerations to make numerical assessment of stress state in case of large deformations which were measured by an intelligent caliper inspection tool. The pipeline was rested on concrete supporting blocks in a boggy terrain. The tool detected very large deformations of the pipe in the areas of these supports which were caused by washouts. Data from the tool were processed into the format readable for MSC/PATRAN-graphical pre-processor of the computational system MSC/NASTRAN based on the Finite Element Method – FEM. Then a mesh of discrete model was generated by means of MSC/PATRAN.
APA, Harvard, Vancouver, ISO, and other styles
3

Xiangyi, Zou, and Ye Linchang. "Calculation and Analysis of Global and Local Vibration of New Scientific Research Ship Based on MSC. Patran & NASTRAN." In 2022 IEEE Asia-Pacific Conference on Image Processing, Electronics and Computers (IPEC). IEEE, 2022. http://dx.doi.org/10.1109/ipec54454.2022.9777415.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Rakita, Milan, Damir Kakas, Branko Skoric, Mileta Tomovic, Qingyou Han, and Mark Jackson. "S-Type Cultivator Tines Which Comply With ISO Standard: FEM Analysis of Stresses and Manufacturing Issues." In ASME 2009 International Manufacturing Science and Engineering Conference. ASMEDC, 2009. http://dx.doi.org/10.1115/msec2009-84162.

Full text
Abstract:
ISO Standard is propagating in all aspects of industries worldwide. In order to keep competitiveness, companies are subjected to necessity for their production to be in accordance with ISO. S-type cultivator tines are used in agriculture for the soil preparation. Dimensions and the methods of testing S-tines are proposed by the standards ISO 5678-1993(E) and ISO 8947-1993(E), respectively. The fatigue test defined by ISO-8947(E) proved to be very rigorous. Stresses which develop in the S-type tine during the fatigue test were determined by the finite element method, using MSC Patran/MD Nastran software packages. Results show that tensile stresses during the test are as high as 1100 MPa (around 160 ksi). It is very strict requirement to have the yield strength higher than that value. This requirement is possible to achieve using thermomechanical treatment, a combination of metal working and heat treatment of mainly high-strength low-alloy (HSLA) steels.
APA, Harvard, Vancouver, ISO, and other styles
5

Carrera, E., A. Pagani, and M. Petrolo. "Static and Dynamic Analysis of Aircraft Structures by Component-Wise Approach." In ASME 2013 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/imece2013-63600.

Full text
Abstract:
This paper proposes an advanced approach to the analysis of reinforced-shell aircraft structures. This approach, denoted as Component-Wise (CW), is developed by using the Carrera Unified Formulation (CUF). CUF is a hierarchical formulation allowing for the straightforward implementation of any-order one-dimensional (1D) beam theories. Lagrange-like polynomials are used to discretize the displacement field on the cross-section of each component of the structure. Depending on the geometrical and material characteristics of the component, the capabilities of the model can be enhanced and the computational costs can be kept low through smart discretization strategies. The global mathematical model of complex structures (e.g. wings or fuselages) is obtained by assembling each component model at the cross-section level. Next, a classical 1D finite element (FE) formulation is used to develop numerical applications. It is shown that MSC/PATRAN can be used as pre- and post-processor for the CW models, whereas MSC/NASTRAN DMAP alters can be used to solve both static and dynamic problems. A number of typical aeronautical structures are analyzed and CW results are compared to classical beam theories (Euler-Bernoulli and Timoshenko), refined models and classical solid/shell FE solutions from the commercial code MSC/NASTRAN. The results highlight the enhanced capabilities of the proposed formulation. In fact, the CW approach is clearly the natural tool to analyze wing structures, since it leads to results that can be only obtained through three-dimensional elasticity (solid) elements whose computational costs are at least one-order of magnitude higher than CW models.
APA, Harvard, Vancouver, ISO, and other styles
6

Clerici, Paolo, Ambrogio Girotti, and Alessandro Perazzolo. "Comparison of Web Stress Concentration Factors and Safety Margins for a Thin Webbed Spur Gear Subjected to Static and Cyclic Loading Conditions." In ASME 1992 Design Technical Conferences. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/detc1992-0007.

Full text
Abstract:
Abstract The stress distribution in the holed web of a gear was studied in order to evaluate the effects of overstress caused by a reduction in weight in comparison with a gear without lightening holes. The analysed gear is a component of a helicopter principal transmission: geometry and dimensions (web with eight circular holes) are usually employed. A 3-D mesh of the gears was made using PATRAN and a FEM analysis was carried out using NASTRAN 65a2. Moreover the principal stress history in one revolution of the gear was reconstructed at the critical points of the web. Thus it was possible to evaluate the actual fatigue cycle and the consequent safety margin for the different load conditions under which helicopter transmissions are generally checked. It was found that the stress variations in one revolution of the gear are significant even in constant power conditions and that the stresses at each point on the border of the holes always have the same sign in a complete revolution. Safety margins in the web were evaluated and compared using different formulas.
APA, Harvard, Vancouver, ISO, and other styles
7

Goldstraw, M. W., C. Bil, and C. Nicholson. "Aerodynamic Loads Prediction in an Integrated Computer-Based Conceptual Design Environment." In ASME/JSME 2003 4th Joint Fluids Summer Engineering Conference. ASMEDC, 2003. http://dx.doi.org/10.1115/fedsm2003-45693.

Full text
Abstract:
An important aspect of successful aircraft design is the concept of ‘right first time’, as any design changes downstream can be costly and may cause project delays. This is most applicable to the conceptual design phase. However, in the early stages of aircraft design, data is limited and prone to inaccuracies. Consequently, a design will typically traverse through a number of iterations, improving and refining with each step. Over the past 15 years, computer-based tools have become commonplace in aircraft design [1]. In general, most computer-based tools have been developed for the more advanced stages of the design process. For these tools to be useful in conceptual design, they must be user-friendly, interactive, and provide quick return times. A classic example is the aerodynamic load data required for structural design. Both are dependent on geometric parameters, which may still be subject to change. To complete the analysis within practical time constraints, a highly integrated and automated system is required [2, 3]. This paper presents such a system, developed using industry accepted software components including AutoCAD, VSAERO and MSC Nastran. This system allows an automatic, structured topology mesh to be generated from a basic three-view aircraft drawing, which inputs directly into VSAERO for loads calculations. The loads are subsequently transferred to MSC Patran as a pre-processor for structural analysis using MSC Nastran. If the result is unsatisfactory, the geometry or placement of structural components can easily be changed and the process repeated. The design environment was developed using FORTRAN90. The results of an application of this system to a simple wing, as well as a regional transport aircraft, are also presented.
APA, Harvard, Vancouver, ISO, and other styles
8

Kong, Changduk, Sungjin Lim, and Hyunbum Park. "A Study on Optimal Design of Filament Winding Composite Tower for 2 MW Class Horizontal Axis Wind Turbine Systems." In ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94124.

Full text
Abstract:
Although the tower of the horizontal axis wind turbine system is a simple structure relatively to the wind turbine rotor system, its production cost tower is about 20–25% of the whole wind turbine system cost. If a composite materials tower is used instead of the existing steel tower, the production cost can be reduced due to use of low cost composite materials, simple manufacturing process, easy transportation and easy assembly. However studies on the composite materials towers are very few. Therefore, in this study a specific structural design procedure for 2 MW class glass/polyester face sheets-sand/ polyester core sandwich composite wind turbine system towers is newly proposed through load case study, trade-off study, optimal structural design and structural analysis. Optimal tower design can minimize both weight and cost. In the structural design of the tower, three kinds of loads such as wind load, blades, nacelle and tower weight and blade aerodynamic drag load should be considered. Initial structural design is carried out using the netting rule and the rule of mixture. Then the structural safety and stability are confirmed using a commercial finite element code, MSC NASTRAN/PATRAN. It is confirmed that the finally proposed tower meets the tower design requirements.
APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Patran-Nastran"

1

Shoales, Gregory A., and Scott A. Fawaz. Stress Concentration Factor Determination for Various Tensile Test Specimen Configuration by the Finite Element Method Using MSC/PATRAN and MSC/NASTRAN. Fort Belvoir, VA: Defense Technical Information Center, February 2004. http://dx.doi.org/10.21236/ada430477.

Full text
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Patran-Nastran' for particular source types:
Journal articles
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography