This study is to analyze and test the extrusion process of a hollow spur gear and a solid helical product with magnesium alloy. In the hollow spur gear part, firstly, a design criterion to determine the forming parameters is proposed. Then, the Finite Element Analysis is used to simulate the flow pattern of the billet from separating channel, welding chamber to die bearing part. From a series of simulation results, the effect of separating channel length, mandrel entrance angle, welding chamber height, etc. on the radial filling ratio, welding pressure, extrusion load, etc. are found. By using the Taguchi Methods, we can find the most important parameters. Finally, a better die geometry is designed to obtain a sound product. In the helical product part, the Finite Element Analysis is used to get the understandings of radical filling ratio of magnesium alloy in the helical zone. Then, a better die geometry is designed from the results of analyses. Finally, hot extrusion experiments of a hollow spur gear and a solid helical product are conducted. The experimental values of the extrusion load and the product¡¦s dimension are compared with the analytic values to verify the validity of the analytic models.

The temperature and thermal stress distributions and variations of the high power LED module were studied in this work. The thermal-elastic-plastic 3D finite element models of MSC.marc software package are employed to simulate these performances for the high power LED module. Two high power white light LED module designs are investigated¡G one is the traditional phosphorescent silicone with blue LED module and the other is a phosphor glass lens with blue LED module. The distributions of temperature and thermal stress of in these two operating LED modules are compared and discussed. The effects of different packaging parameters¡Ge.g. bonding materials, substrate materials, lens materials on the temperature and thermal stress have also been studied in this work. The simulated results reveal that the serious thermal crack may occur for these two designs if the power of single die is over 10 watt. The simulated results also indicate that an attached fin cooler may improve these thermal crack disadvantaged significantly. The effect of fin design parameters on the peak temperature reduction has studied. A feasible fin design for the high power LED module has also been proposed.

Profile strips have been used in various industries and now the demand of profile strip is still growing. Due to different reductions at different parts of the strips, profile strips after rolling generate a defect which looks like a wave. This study will design and manufacture a four-high profile rolling mill, which can roll profile strips. Experiments and finite element simulation are conducted to discuss the effects of different parameters on strip size and the defect of the profiled strips. In this study, a finite element analysis software is used to establish profile rolling models with different material setting mode, reduction, temperature, material, tension, and roll shape. From the simulation results, the effects of these parameters on the defects are discussed. Secondly, profiled rolls are designed and a heating equipment is added on the four-high rolling mill, and rolling experiments with different reduction, materials, passes of process, roll shape and temperature are conducted. From the experimental results the effects of these parameters on size of the defect of profile strip are discussed. Finally, from the comparisons between simulation results and experiment results, the feasibility of finite element models are verified.

Anti ram perimeter barriers are part of the protection of important facilities such as power plants, air ports and embassies against unrestricted vehicle access. Many different systems can be used to achieve the containment goal. One of these systems makes use of soil embedded posts either single posts if the soil is hard enough or groups of soil embedded posts tied together by beams if the soil is not hard enough for a single post to stop the in-coming truck. The design of these soil embedded posts needs to take account a number of influencing factors which include the soil strength and stiffness, the post strength and stiffness, the mass of the vehicle and its approach velocity. This dissertation describes the work done to develop a set of design recommendations to select the embedment of a single post or group of posts. The post is a steel beam with an H shape cross section: W14X109 for the single post system and W14X90 for the group system with a double beam made of square hollow steel section HSS8X8X1/2. The spacing of the posts for the group includes 2.44 m, 4.88 m, and 7.32 m. The soil strength varies from loose sand and soft clay to very dense sand and very hard clay. The vehicle has a mass of 6800 kg and the velocities include 80 km/h, 65 km/h, and 50 km/h. The design guidelines presented here are based on 10 medium scale pendulum impact tests, 2 medium scale bogie impact tests, 1 full scale impact test on a single post, 1 full scale impact test on a group of 8 side by side posts with a 5.2 m spacing and connected with two beams, approximately 150 4-D numerical simulations of full scale impact tests using LS-DYNA, as well as fundamental theoretical concepts.

This thesis provides a detailed field analysis of a specially designed axial-flow radial-flux permanent magnet motor for cooling fan applications. By implementing an iron strip segment at the stator base, this motor can provide a stable guidance force in its axial direction, such that the operational vibration effects can be minimized and the undesired forces applied onto associated bearing system can be alleviated. Supported by adaptive magnetic equivalent circuit and three-dimensional finite element analyses, the motor operational fluxes and forces can be analyzed. Results show that excellent performance and enhanced reliability objectives can all be achieved.

Assembling of the compliant parts used in aviation industry is a challenging process. Assembly fixtures are quite important tools in this effort and widely used in industry. In fixturing of easily deformable sheet metal parts, besides restraining the rigid body motion of the parts, the possible deformations that may occur during the assembly process and the spring-back effect on the final product need to be taken in to consideration. In order to guarantee a successful assembling, in other words, to obtain the final product within specified tolerances, a systematic approach to the fixture design problem is required. The designer should predict the correlation between the input variations and the final assembly variation, especially, for the complex assemblies. This study proposes a design and analysis approach in fixturing of sheet metal assemblies for helicopter components. The design of an assembly fixture for a particular tail cone has been completed convenient to the existing locating principles. Finite Element Analysis (FEA) has been realized in simulating the assembling process in order to predict the possible variation of the interested feature on a complex assembly due to deformations.

During the last years, biomechaniccs, the understanding of the very complex mechanical behavior of living tissue, becomes a very important field of research of the wide bravch of mechanichs. Thia study is very important, for instance , to improve the design of implants, with the important social and economical impact. one of important challenges in implant design is to model the complex material behavior of the bone. Remodeling of the bone due to the lodaing is one of the essential behaviors of the bone which can cause for the dental implants, marginal bone loss accuring particallary in the first years of function. On the other hand the finite element method(FEM) has become the most extended tool for engineers to analyse the mechanical behavior of the products which usualy have a complex material behavior and complicated geometries. The aim of this study is to model the remodeling behavior of the bone using FEM and to use the new bone material method to evaluate the implant performance for some commercial implants, taking account of the bone adaptation.

In this thesis aeroelastic analysis of a typical Unmanned Aerial Vehicle (UAV) using MSC&reg / FlightLoads and Dynamics module and MSC&reg / NASTRAN Aero 1 solver was performed. The analyses were carried out at sea level, 1000m, 2000m and 4000m altitudes for Mach Numbers M=0.2, 0.4 and 0.6 for the full model of the UAV. The flutter characteristics of the UAV for different flight conditions were obtained and presented. The effect of altitude on flutter characteristics has been examined and compared with the theoretical and experimental trends in the literature. Also the divergence characteristics of the full model UAV was obtained. In the study, some verification and test cases are also included. The results of the analyses of an untapered swept-wing and AGARD 445.6 wing models were compared with wind tunnel data and a maximum error of 1.3 % in the flutter speed prediction was obtained. In two different wing models the effect of taper was investigated.

This study mainly covers the finite element analysis of a micro satellite structure by considering the vibration effects at the time interval from the launching to the Earth&rsquo / s orbit landing. Micro-satellites have a great importance in the satellite industry and several developing countries deal with micro-satellite design and production. Turkey is one of these countries by conducting new satellite projects. RASAT project is one the continuing micro-satellite project, which has being developed by T&Uuml / BiTAK Space Technologies Research Institute. In this thesis, the RASAT satellite is taken as the model for the study. On this model, many mechanical design studies which are performed according to the specified requirements and constraints are verified by finite element analyses. These analyses cover all the essential vibration loads during launching. In the study, firstly, a finite element model of RASAT is prepared. Then, the essential analyses are performed according to the specifications required by the launchers. In the analyses, commercially available finite element software is used. Finally all the results obtained from the finite element analyses are compared with the predefined requirements and constraints. The results show that the structural design verification regarding the reliability of the structure for the desired mission has been successfully completed.

The aim of this study is to perform the shape optimization of the lower chassis of the wheeled excavator. A computer program is designed to generate parametric Finite Element Analysis (FEA) of the structure by using the commercial program, MSC. Marc-Mentat. The model parameters are generated in the Microsoft Excel platform and the analysis data is collected by the Python based computer codes. The previously developed software Smart Designer [5], which performs the shape optimization of an excavator boom by using genetic algorithm, is modified and embedded in the designed program.