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권진희 慶尙大學校 1998 論文集 Vol.37 No.-
The light aircraft, "Comet" with twin seats was developed with the fuselage made of 4130 steel tube. In this paper, the stress analysis results of the fuselage are presented. For the stress analysis, three load cases are considered based on the 4.4g symmetric pull-up, -1.8g symmetric push-over, and balanced landing conditions. The fuselage structures are idealized by the truss and bar elements. MSC/PATRAN and MSC/NASTRAN were utilized as the pre/post-processor and the solver. Margins of safety of the structures are estimated based on the static strength and the Euler buckling stress. In the first design, some elements showed the negative margins of safety by the column buckling for the load conditions 1 and 3. Finally the elements were modified to have positive values. Verification of the structural safety of the fuselage will be conducted by the flight test of the prototype.
권진희 慶尙大學校 1999 論文集 Vol.38 No.-
A nonlinear finite element method is presented for the crippling analysis of graphite/epoxy composite channel beams which are widely applied to the aircraft stringers. Channel beams are idealized using nine-node degenerated shell element. To simulate the structural stiffness degradation after local failure, complete unloading model is introduced into the fi-nite element method. A modified Riks method is used to trace the post-failure equilibrium path after local buckling. Finite element results are compared with previous experimental results and show the excellent agreement. As numerical examples, Z-section composite channel beams are considered. The numerical results show that the most important par-ameter affecting the crippling stress of channel beams is the flange width. In terms of stacking sequence, the highest crippling stress is found at the stringer with [±45/0/90]s lamination.
서영수,정희택,권진회 경상대학교 생산기술연구소 2003 工學硏究院論文集 Vol.19 No.-
The rotating machinery such as the centrifugal pump related to the safety in nuclear power plants have to evaluate their structural integrity and operability through the experimental test, computational analysis or the combination of the test and the analysis. The paper presented is currently aimed at the computational analysis of the designed nuclear pump in the sense of the structural integrity and operability for the centrifugal machinery pump. The commercial finite element analysis program(MSC/NASTRAN)was available to perform the static analysis on the horizontal centrifugal pump installed on the gas stripper system. The numerical results are analysed with respect to the natural frequency, nozzle loads as well as seismic loads, and also the shaft critical analysis along with evaluation of deflection are verified to ensure that the design results meet the seismic requirements.
Kweon, Jin-Hwe,Shin, So-Young,Choi, Jin-Ho Sage Publications 2007 Journal of composite materials Vol.41 No.17
<P>A two-dimensional progressive failure analysis is conducted to predict the failure loads and modes of combined unidirectional-fabric laminated composite joints under pin-loading. The first objective of this study is to investigate the possibility of applying ACOS-J, a two-dimensional progressive damage analysis program, to the strength analysis of composite joints. The second objective is to study how the various failure criteria could be applied, separately or in combination, to pinned joints in combined unidirectional and fabric laminated composites. An eight-node laminated shell element is used for the finite element modeling. Post-failure stiffness is evaluated based on the complete unloading method combined with various failure criteria. A total of 52 specimens with nine different geometries were tested to obtain the experimental strength and failure mode. The results show that a finite element analysis based on the combined YamadaU2014;Sun and TsaiU2014;Wu criteria most accurately predicts the failure loads of the composite laminated joints.</P>
Progressive Failure Analysis of Unidirectional-Fabric Laminated Composite Joints under Pin-Loading
Kweon, Jin Hwe,Son, Hee Jin,Choi, Ji Young,Shin, So Young,Choi, Jin Ho,Lee, Gun Myung Trans Tech Publications, Ltd. 2007 Key Engineering Materials Vol.334-335 No.1
<P>A two-dimensional progressive failure analysis is conducted to predict the failure loads and modes of carbon-epoxy composite joints under pin-loading. An eight-node laminated shell element is used for the finite element modeling. Post-failure stiffness is evaluated based on the complete unloading model combined with various failure criteria. The comparison of finite element and experimental results shows that the finite element analysis based on the combined maximum stress and Yamada-Sun criteria most accurately predicts the failure loads of the composite laminated joints.</P>