• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2013년도 춘계학술대회 논문집
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• pp.835-841
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• 2013

Modern solid-state gyroscopes (HRG) with hemispherical resonators from high-purity quartz glass and special surface superfinishing and ultrathin gold coating become the best instruments for precise-grade inertial reference units (IRU) targeting long-term space missions. Designing of these sensors could be a notable contribution into development of Korea as a space nation. In participial, 40mm diameter thin-shell resonator from high-purity fused quartz, fabricated as a single-piece with its supporting stem has been designed, machined, etched, tuned, tested, and delivered by STM Co. (ATS of Ukraine) several years ago; an extremely-high Q-factor (upto 10~20 millions) has been shown. Understanding of the best way how to match such a unique sensor with inner glass assembly of the gyro means how to use the high potential in a maximal extent; and this has become the urgent task. Inner quartz glass assembly has a very thin indium (In) layer soldered the resonator and its silica base (case), but effects of internal resonances between operational modal pair of the shell-cup and its side (parasitic) modes can notable degrade the potential of the sensor as a whole, instead of so low level of resonator's intrinsic losses. Unfortunately, there are special combinations of dimensions of the parts (so-called, "resonant sizes"), when intensive losses of energy occurs. The authors proposed to use the length of stem's fixture as an additional design parameter to avoid such cases. So-called, a cyclic scheme of finite element method (FEM) and ANSYS software were employed to estimate different combinations of gyro assembly parameters. This variant has no mismatches of numerical origin due to FEM's discrete mesh. The optimum length and dangerous "resonant lengths" have been found. The special attention has been paid to analyses of 3D effects in a cup-stem transient zone, including determination of a difference between the positions of geometrical Pole of the resonant hemisphere and of its "dynamical Pole", i.e., its real zone of oscillation node. Boundary effects between the shell (cup) and 3D short "beams" (inner and outer stems) have been ranged. The results of the numerical experiments have been compared with the classic model of a quasi-hemispherical shell band with inextensional midsurface, and the solution using Rayleigh's functions of the $1^{st}$ and $2^{nd}$ kinds. To guarantee the truth of the recommended sizes to a designer of the real device, the analytical and FEM results have been compared with experimental data for a party of real resonators. The consistency of the results obtained by different means has been shown with errors less than 5%. The results notably differ from the data published earlier by different researchers.

• 한국도로학회논문집
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• 제19권6호
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• pp.67-74
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• 2017

PURPOSES : In this study, a three-dimensional nonlinear finite element analysis (FEA) model for airport concrete pavement was developed using the commercial program ABAQUS. Users can select an analysis method and set the range of input parameters to reflect actual conditions such as environmental loading. METHODS : The geometrical shape of the FEA model was chosen by considering the concrete pavement located in the third-stage construction site of Incheon International Airport. Incompatible eight-node elements were used for the FEA model. Laboratory test results for the concrete specimens fabricated at the construction site were used as material properties of the concrete slab. The material properties of the cement-treated base suggested by the Federal Aviation Administration(FAA) manual were used as those of the lean concrete subbase. In addition, preceding studies and pavement evaluation reports of Incheon International Airport were referred for the material properties of asphalt base and subgrade. The kinetic friction coefficient between the concrete slab and asphalt base acquired from a preceding study was used for the friction coefficient between the layers. A nonlinear temperature gradient according to slab depth was used as an input parameter of environmental loading, and a quasistatic method was used to analyze traffic loading. The average load transfer efficiency obtained from an Heavy falling Weight Deflectomete(HWD) test was converted to a spring constant between adjacent slabs to be used as an input parameter. The reliability of the FEA model developed in this study was verified by comparing its analysis results to those of the FEAFAA model. RESULTS : A series of analyses were performed for environmental loading, traffic loading, and combined loading by using both the model developed in this study and the FEAFAA model under the same conditions. The stresses of the concrete slab obtained by both analysis models were almost the same. An HWD test was simulated and analyzed using the FEA model developed in this study. As a result, the actual deflections at the center, mid-edge, and corner of the slab caused by the HWD loading were similar to those obtained by the analysis. CONCLUSIONS : The FEA model developed in this study was judged to be utilized sufficiently in the prediction of behavior of airport concrete pavement.

• 대한치과보철학회지
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• 제49권4호
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• pp.316-323
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• 2011

연구 목적: 본 연구의 목적은 치과용 임플란트 나사산 디자인이 변연골 응력에 미치는 영향에 정량적인 분석을 하고자 한다. 연구 재료 및 방법: 외경 4.1 mm (경부직경 3.5 mm), 매식부 길이 10 m인 표준형 ITI 임플란트 시스템(ITI Dental Implant System; Straumann AG, Waldenburg, Switzerland)을 기본모델(대조모델)로 채택하고, 그 몸체의 나사산은 다른 임플란트 시스템에 채택되고 있는 삼각형, 사각형, buttres형 디자인을 가지는 가상의 해석모델을 4종 만들었다. 해석모델은 나사산 형태와 크기에 따라 (1) 모델 A (작은 삼각형 나사산), (2) 모델 B (큰 삼각형 나사산), (3) 모델 C (buttres형 나사산), 및 (4) 모델 D (사각형 나사산)로 구분하였다. 유한요소 모델링과 해석에는 NISA II/DISPLAY III (Engineering Mechanics Research Corporation, Troy, MI, USA) 프로그램을 사용하였다. Mesh 구성에는 NKTP type 34형 solid 요소(4각형 축대칭 요소, 요소당 절점수 8개)를 사용하여 임플란트 장축과 평행한 축대칭 하중은 물론 장축과 경사각을 갖는 비축대칭 하중조건을 모두 해석할 수 있도록 하였다. 임플란트의 표면으로부터 각각 0.2, 0.4, 0.6, 0.8, 1.0 mm 떨어진 위치에 5개의 응력관찰점(stress monitoring point)을 설정 하여 기록된 응력 값으로부터 회귀분석을 통하여 변연골 응력 최대값(peak stress)을 정량화하였다. 해석에 사용한 하중 조건은 2가지로, 임플란트 축에 평행한 수직하중 100 N과 임플란트 축과 $30^{\circ}$를 이루는 경사력 100 N 조건이었다. 결과: 임플란트 경부와 접하고 있는 인접 변연골에 응력집중현상이 보이고 있었으며, 그 양상은 임플란트 나사산 디자인과 무관하게 거의 유사하게 관찰되었다. 수직력 100 N 조건에서 산출된 변연골 최대응력값은 대조모델과 실험모델 A, B, C, D에서 7.84, 6.45, 5.96, 6.85, 5.39 MPa이었고, 경사력 조건에서는 각각 29.18, 26.45, 25.12, 27.37, 23.58 MPa이었다. 결론: 임플란트 나사산의 디자인은 변연골의 응력에 영향을 미치는 중요한 요소이다.