In this paper, stress contour plots depending on length, load, and diameter of the implant are presented. Depending on the condition and amount of cortical bone, process of implanting can be difficult and stress becomes important. Therefore deciding the right length and diameter of implant is critical. When analyzing stress in the implant, Von-mises yield criterion is often used; however, due to hardship of acquiring the actual material property of surrounding bones, simplified model of a implant was adapted in finite element analysis program of EDISON. The result acquired from EDISON program was then compared with results of different research papers.

In this paper, Shape optimal design for a chair with 4 legs and 2 stretchers consisting of stainless steel was conducted. The shape was transformed by identifying stress and deformation for the part of leg and stretcher. In addition, load condition and mesh was designed using Hypermesh. The stress analysis was carried out using CSD_Elast that is one of EDISON program. In seat test, Maximum equivalent stress was showed at the contact part between seat and legs. As a result, a leg cross-section with rectangular and arch was designed. And optimal height of stretcher was found to reduce a deformation. Also, maximum deformation was reduced by designing a stretcher with ellipse cross-section. So, Optimal chair having 4 legs with rectangular cross section and 2 stretchers with ellipse cross section was shown to satisfy the safety ratio.

자연에서 안정적이고 경제성이 높은 구조로 벌집 구조가 많이 언급이 된다. 이러한 벌집 구조의 특징으로 인해 많은 공학자들이 그 구조를 모방하여 적용하고 있다. 벌집 구조에도 다양한 종류가 존재하지만 그 중 음의 푸아송 비(Poisson’s ratio)를 갖는 Chiral Honeycomb 구조가 많이 연구되고 있다. 푸아송 비는 물질이나 구조의 고유한 물성치로 종, 횡 방향의 변형율로 나타내며 이 값으로 외부 조건으로부터의 변형을 예측 할 수 있게 된다. 흔히 푸아송 비는 양의 값을 가지지만 Chiral Honeycomb 구조는 음의 푸아송 비를 가져 기존의 구조와는 다른 기계적 성질을 가지게 된다. 이 논문에서는 Chiral Honeycomb 구조 중에서도 4개의 관절(ligament)를 가지는 Tetra Chiral Honeycomb 구조에 대해 EDISON용 CASADsovler 프로그램을 통해 유한 요소 해석을 수행하여 등가 물성치를 구해 보았으며 기존 실험의 값들과 비교를 통해 해석을 위해 필요한 적절한 대표 체적에 대해 확인해 보았다.

When spring of the suspension is exerted by an external load, a car should be designed to prevent predictable damages and designed for a ride comfort. We used experiments design to design VON-MISES STRESS and K, a constant, of spring of suspension which is installed in a car as a goal level. We analyzed the result from Edison's Elastic - Plastic Analysis SW(CSD_EPLAST) by setting D, d, n as external diameter of coil, internal diameter of coil, the number of total coil respectively. The experiment design let the outcome be as Full-second order by using Box-Behnken which is one of response surface methods. Experimented and analyzed results based on the established experiments design, We found out design parameter which has desired VON-MISES STRESS and the constant K. Additionally, we predicted life time of when the external load was exerted by repeated load by using fatigue equation, and verification of plastic deformation has also been made. Additionally we interpreted a model, which is formed by optimized design parameter, with linear analysis and non-linear analysis, at the same time we also analyzed plastic deformation with the values from the both models. Finally, we predicted fatigue life of optimized model by using fatigue estimation theory and also evaluated a ride comfort with oscillation analysis.

Recently laminated plates like composite materials has been used in a various field to grow the specific strength of the composition. However, delamination area caused by barely visible impact damage has potential risk that it can raise buckling of the delaminated plate. Because it can interrupt compressive behavior of laminated plates and reduce their strength, the whole structure can't be constituted by these materials. Many studies assume that behavior of the delaminated plate which is in lamanated plates equals theoretical buckling but their actual motion doesn't coincide because of initial imperfections of materials like deflection, residual stress, eccentricity and so on. In this paper, we change laminated plates with initial delamination into a beam of rectangular cross section with the initial crack and analyze compressive behavior according to initial imperfections through finite element method(FEM). Consequently analysis results show that behavior of laminated plates involving delamination differs from ideal buckling of the delaminated plate in actual conditions and we can predict its motion through imperfections relationship.

"Auxetic material is a material which has negative Poisson’s ratio(NPR). Auxetic material shows some distinctive property like high energy absorbing property and high shear modulus. Among these, synclastic curvature is very interesting characteristic. When synclastic-curvature-material bends, it changes its shape like dome, contrary to non-auxetic material which changes its shape like saddle(anticlastic). This distinctive property could make it easy to manufacture curved structure like nose cone or wing panel in aerospace engineering. In this study, we studied a quantitative analysis about synclastic curvature of re-entrant panel with finite element model. We suggested a concept ‘Degree of Synclasticity(DOS)’, which means a ratio of curvature of load-direction and load-orthogonal direction. We studied the variation of DOS with two factor, unit cell inner angle() and load position angle(). DOS decreases as increases because the unit cell goes out of auxetic-shape. As varies, DOS changes in a large range. So proper optimization of would be needed for application."

In this paper, a springboard for diving is analysed to find out how much force a diver should apply to reach specific height when the diver jumps. The springboard is presumed to Co-rotational plane cantilever beam(CR-beam), so EDISON program related to Co-rotational framework is used. The force of the person is supposed to sine function and the demanded height is fixed. Same velocity makes same height regardless of diver’s weight. So, the velocity of springboard when the feet of a diver are separated from the springboard is a main factor of the analysis. The result shows that there is no association between deformation and weight and also between velocity and weight. That is, the required force to reach a optimal height is fixed whatever the diver’s weight is.

In this paper, the optimized design for bow structure was investigated by using EDISON software. Considering the mechanism of the bow, non-linear FEM analysis was essential. The factors of the design are height, width, number of holes and taper value. High performance of the internal energy and lowest mass were main issues. The limit of the von-mises stress was yield strength for the material. Material was chosen by considering typical bow material, Aluminum. Using Taguchi method(), 9 models were selected and contribution rate was calculated for each factors. Following the contribution rate, 3 factors were fixed and optimized model was predicted. After making optimized model for FEM analysis, the value of internal-energy, mass for FEM model were compared with predicted value, calculated the percentage error and figure out the reliability of Taguchi method.

In this paper, crack detection method using eigen value analysis is presented. Three methods are used: theoretical analysis, finite element method with the cracked beam elements and finite element method with three dimensional continuum elements. Finite element formulation of the cracked beam element is introduced. Additional term about stress intensity factor based on fracture mechanics theory is added to flexibility matrix of original beam to model the crack. As using calculated stiffness matrix of cracked beam element and mass matrix, natural frequencies are calculated by eigen value analysis. In the case of using continuum elements, the natural frequencies could be calculated by using EDISON CASAD solver. Several cases of crack are simulated to obtain natural frequencies corresponding the crack. The surface of natural frequency is plotted as changing with crack location and depth. Inverse analysis method is used to find crack location and depth from the natural frequencies of experimental data, which are referred by another papers. Predicted results are similar with the true crack location and depth.

In this paper, to design Human Powered Aircraft(HPAC) with high aspect ratio wing which behave with large displacement under lift distribution causing a failure itself, then steel wire has been designed to prevent its failure. unit load method is used to calculate reaction force on wire and Optimal Triangle(OPT) membrane is employed to analyze its main wing spar with large displacement. EDISON CSD solver, linear static analysis and co-rotational nonlinear static anaysis both using OPT membrane produce behaviors of beam for each case of wire location about main wing spar, and aerodynamic coefficient also, by using aerodynamic analysis tool.

In this paper, an optimization study on a helicopter rotor blade cross-section was made. Generalization was made to the baseline cross-section to simplify the analysis. To have better performance in aeroelastic response, with the aerodynamic center being the origin of the baseline, the distance between aerodynamic center and shear center, and the distance between mass center and shear center of the blade were minimized. For efficient searching of optimum solutions over the design space, grid search method, which is a method of graphical search was used. Two design variables, radius of balancing weight at leading edge, and offset of the spar from leading edge were selected for the study. Cubic spline interpolation method was used to accommodate searching of the optimum solution. 2-Leveled searching system was devised in accordance with the interpolation method. Optimum solution was found to show 6% decrease in both distance between aerodynamic center and shear center, and mass center and shear center to the baseline.

Recently, carbon fiber-reinforced composite is widely used in many aerospace applications. Among most of the aerospace vehicles, human-powered aircraft essentially uses it for minimizing the weight of the vehicle and gaining high stiffness to increase its efficiency. In this paper, main wing spar of the human-powered aircraft is investigated. Finite element models were created based on the baseline model built in 2013 to make analysis of cross-section of the spar with varying ply angles of each layer of the spar. Objective function, which is affected from bending rigidity, torsional rigidity, and strength ratio, was evaluated for every cases. The model of 2013 and present cases were put into comparison by values evaluated from objective function. From the comparison, it was concluded that there are more chances to improve the baseline model to make the vehicle better in stiffness and weight than the model of 2013.

DNA origami is the most fitting nano-technology for synthesis of complex nano-structures. DNA crossover which ties DNA helices together are the main reason for the stable sustenance of origami structures with respect to other nano-scale structures. The mechanical properties of DNA crossovers have profound connection with structural rigidity, and it is a known fact that the rigidity changes depending on the arrangement of crossovers. It is possible to control the rigidity of origami structures for functionality and furthermore extends the field of DNA origami application. Here, we investigate the effect of crossovers on 2-Dimensional DNA structures varying crossover arrangement by sensitivity analysis based on finite element model. The crossover properties obtained from this analysis are compared with the existing experimental results.

본 논문에서는 흔히 볼 수 있는 전봇대가 속이 꽉 차있다는 점에서 문제제기를 시작하였다. 전봇대를 설계 할 때에 속을 꽉 채우는 것이 과연 효율적이고 경제적인 설계인지 알아보고, 그것이 아니라면 어떤 단면으로 설계를 해야 하는지에 대해 문제접근을 하게 되었고, 결과적으로 속이 빈 파이프형 부재가 실제로 저항하는 하중은 작지만 경제적으로 보았을 때 현재의 전봇대보다 효율적이라는 결론을 낼 수 있었다. 추가적으로 본 논문에서는 수직력과 Bending moment외에 다른 힘을 생각하지 않았으므로 그런 것에 대한 충분한 연구가 있은 후에 이러한 설계가 적용되면 좋을 것이라고 본다.

In this paper, vibration characteristics in terms of the airfoil cross-sectional shape was examined by using the EDISON co-rotational plane beam-transient analysis. Assuming aircraft wing as a cantilevered beam with a constant cross-sectional shape, natural frequencies of each airfoil shape was compared while varying airfoil maximum thickness and maximum camber length, using Fast Fourier Transformation(FFT). When the airfoil maximum thickness was varied, natural frequency showed peak value at 18% chord, and decreased afterwards. When the airfoil maximum camber length was varied, natural frequency either increased or decreased at 6% chord, while at 8% the natural frequency showed its maximum. Applying such trends to B-737 wing airfoil, an improved B-737_mod airfoil shape was obtained with regard to the vibration characteristics.

Holes of rivets, bolts and nuts may cause stress concentration on the plates used in aircraft, ship and other structures. Excessive stress concentration may lead to severe breakage of the plates. Thus, accurate analysis of the stress concentration at the design stage will be important. In this paper, accuracy of EDISON program in stress concentration analysis was examined. By changing hole size on a narrow plate, the change of the stress concentration factor(K) was investigated. Additionally, the same experiment was conducted about series of holes on plate to investigate the interaction between adjacent holes. Then, these numerical results were compared with the analytic prediction. EDISON program showed very high accuracy about stress concentration, since the numerical results was correlated well with the analytic prediction.

기계적 장치의 도움 없이 오직 사람의 힘으로만 비행을 해야 하는 인간 동력 항공기는 높은 동력 효율 및 최소한의 무게를 지니며 고세장비(High Aspect Ratio)날개 특성을 가지고 있다. 따라서 공력 및 구조적 최적화가 필요하며 고세장비 날개 특성에 따른 대변위 해석이 필요하다. 비행가능한 특정 순항속도에서 3차원 날개에 작용하는 양력에 대해, Edison Solver(Educational program for finite element analysis (CASADSolver))를 이용하여 2차원 spar에 분포하중으로 적용하였을 때의 응력 분포 및 끝단 변위 분석하고자 한다. 또한, 2차원 spar에 일정한 간격으로 집중하중을 작용하였을 때 생기는 변위와 3차원 spar를 이용한 하중해석 결과의 변위를 비교하고자 한다. 위의 두 분석 결과로 비교적 계산자원이 많은 3차원 해석이 아닌 2차원 해석으로 인간 동력 항공기 날개 설계 초기단계에 적용가능한 지에 대해 비교한다.