• Journal of the Korean Geotechnical Society
• /
• v.34 no.10
• /
• pp.39-49
• /
• 2018

In this study, aimed at determining the elastic modulus of deep mixed samples, 320 test specimens were developed by mixing 8%, 10%, 12%, and 14% of stabilizer mixture in the granular conditions of clay, sand and gravel. Uniaxial compression tests were carried out using these specimens, and the uniaxial compression strength and strain were analyzed to determine the secant elastic modulus and tangent elastic modulus. Laboratory test results showed that the uniaxial compression strength of all deep mixed samples increased with increasing curing time and stabilizer mixing ratio, and that the secant elastic modulus and the tangen elastic modulus also increased. The increase of the elastic modulus according to the curing period turned out greater in the tangent elastic modulus than in the secant elastic modulus. In order to measure elastic modulus with changes in stabilizer mixing ratio, the correlation coefficient between the elastic modulus for stabilizer mixing ratio of 8% and that of 10%, 12% and 14% was calculated respectively by the specimen condition. The elastic modulus tended to increase as the grain size in a deep mixed specimen increased. The distribution of grain size that had the greatest effect appeared when the composition ratio of sand was high. On the other hand, the increase in the elastic modulus was larger in the sand specimens than in the clay and gravel specimens. Based on these results, it is suggested that a pertinent soil parameter of the deep mixed ground in the field may be obtained by the particle size distribution and the mixing ratio of stabilizer of the deep mixed soil.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.43 no.9
• /
• pp.781-786
• /
• 2015

An aeroelastic stability can be degraded due to an aeroelastic modeling error and a structural uncertainty. Therefore it is necessary to predict the aeroelastic stability boundary considering an aeroelastic modeling error and a structural uncertainty. Robust aeroelastic analysis was proposed to predict the aeroelastic stability boundary considering these error and uncertainty. In the present study, the robust aeroelastic modeling and analysis were performed by using the ${\mu}$ analysis technique and the aeroelastic model of the control fin with modal approach and MSA. The computer program for the robust aeroelastic analysis was developed and verified by comparing its results with those of conventional aeroelastic analysis methods.

• Journal of the Computational Structural Engineering Institute of Korea
• /
• v.20 no.6
• /
• pp.709-717
• /
• 2007

This paper discussed on the effect of an intermediate support on the stability of a beam resting on elastic foundation subjected to follower force. The stability and dynamic responses of a beam resting on elastic foundation subjected to follower force are analyzed based on the finite element method. The dynamic responses of the system are studied by the mode superposition method to observe the damping rate of the motion. The beam resting on elastic foundation subjected to follower force loses its stability by flutter type or divergence type, depending on the location of the intermediate support.

• Journal of Aerospace System Engineering
• /
• v.14 no.5
• /
• pp.1-8
• /
• 2020

The aeroservoelastic analysis that deals with the interactions of the inertial, elastic, and aerodynamic forces and the influence of the control system have been performed. MSC Nastran was used for the free vibration analysis of the structure model as the pre-analysis. ZAERO was used to calculate the unsteady aerodynamic forces. The unsteady aerodynamic forces were verified by comparing with Doublet Hybrid Method. Karpel's Minimum-State Approximation method was used for approximation of the aerodynamic forces to the Laplace domain in the frequency domain. The aeroservoelastic state-space equation was obtained by combining the aeroelastic equation with the actuator dynamics. The analysis of aeroservoelastic stability concerning the elevator input of the high aspect ratio model was performed. The root-locus method and time-integration method were used for the analysis of aeroservoelastic in frequency and time domain.

• Transactions of the Korean Society of Mechanical Engineers
• /
• v.16 no.12
• /
• pp.2205-2215
• /
• 1992

The stability of the flexible rotor mounted on circumferentially grooved floating ring journal bearings was investigated theoretically and experimentally. The floating ring journal bearing was analyzed by using JFO reformation boundary condition. The flexible shaft was analyzed by the finite element method based on Rayleigh beam theory. It was found that the measured ring speed agrees well with the theoretical results. The instability of the system due to not only the outer film but also the inner film of the bearing could be predicted by the theory which allows negative vapor pressure. The tendency that reducing the supply pressure of lubricant stabilizes the system was observed both experimentally and theoretically.

• Aerospace Engineering and Technology
• /
• v.7 no.2
• /
• pp.205-212
• /
• 2008

This paper describes the modeling data and final analysis results of rotor resonance, rotor aeroelastic stability and whirl flutter stability for Smart UAV (SUAV). The effects of wing beamwise, chordwise and torsional stiffness on the whirl flutter stability were investigated considering the possibility of design change of SUAV wing structure. The parametric study showed that wing torsional and beamwise stiffness changes have much stronger influence on the wing mode damping than chordwise stiffness. It was analytically demonstrated that the final designed rotor system is aeroelastically stable and free from resonance, and that rotor/pylon/wing system of SUAV TR-S4 has enough rotor stability and whirl flutter stability margin.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.34 no.6
• /
• pp.75-82
• /
• 2006

Tiltrotor aircraft can fly about twice faster and several times further than conventional helicopters. These aircraft provide advantages preventing compressibility of advancing side and stall of retreating side of blades because they take forward flight with tilting rotor systems. However, they have limit on forward flight speed because of the aeroelastic instability known as whirl flutter. First, the parametric study on the aeroelastic stability of the isolated rotor system has been performed in this paper. And the effects of pitch-link stiffness, gimbal spring constant, and precone angle on the whirl flutter stability of Smart-UAV have been investigated through CAMRAD II analysis.

• Journal of the Korea Computer Graphics Society
• /
• v.12 no.2
• /
• pp.39-44
• /
• 2006

컴퓨터 그래픽스 분야에서 변형체 애니메이션은 매우 중요한 기법으로 그 응용 범위가 매우 넓다. 본 논문에서는 큰 회전 변형에도 부피의 왜곡이 발생하지 않으며, 변형체의 어느 한 부위가 고정되어 있지 않고 자유롭게 움직일 수 있는 동적 탄성 변형을 실시간에 시뮬레이션 하는 기법을 제안한다. Choi와 Ko [3]가 제안한 모달 와핑 기법은 실시간에 부피의 왜곡이 없는 동적 탄성 변형을 생성할 수 있지만 탄성체의 어느 한 부위가 고정 되어 있어야 하며, Hauser 등 [9]이 제안한 임펄스 기반의 충돌 반응을 고려한 선형 모달 해석법은 안정적인 시뮬레이션 결과를 주지만 큰 변형에 있어서 부피 왜곡이 있다. 본 논문에서는 Choi와 Ko [3]가 제안한 모달 와핑 기법을 임펄스 기반의 충돌 반응을 포함하도록 확장하여 큰 회전 변형에도 부피의 왜곡을 방지하며 또한 자유롭게 움직이는 탄성체의 충돌 반응을 안정적으로 시뮬레이션 할 수 있게 한다.

• Proceedings of the Acoustical Society of Korea Conference
• /
• 1991.06a
• /
• pp.143-147
• /
• 1991

본 논문에서는 결합 모드 이론에 기초한 새로운 위상조건을 제시한다. 새로운 위상조건은 탄성표면파의 보강이라는 관점에서 유도된 것이다. 컴퓨터 시뮬레이션 결과, 새로운 위상조건에 의해 설계된 150MHz 탄성표면파 공진기는 IDT의 쌍 수에 관계없이 안정된 공진특성을 나타냈다.

• Proceedings of the Computational Structural Engineering Institute Conference
• /
• 2009.04a
• /
• pp.496-499
• /
• 2009

본 논문은 기하학적 비선형성을 가진 보존적 단일 하중 매개변수의 탄성 상태 공간구조의 분기이론에 관한 수치 해석적 기본 방법 및 경로 추적, pin-pointing, 경로 전환을 기술하고 있다. 비선형 탄성 불안정 상태는 극한점과 분기점으로 분류될 수 있으며, 평형경로상의 평형점의 계산 및 평형경로상의 특이점을 찾기 위한 pin-pointing 반복계산을 수행하는 일반적인 비선형 수치해석법으로 극한점을 계산할 수 있다. 그러나 분기좌굴 해석을 위해서는 좌굴 후 분기경로의 추적을 위한 분기경로 전환 알고리즘이 추가적으로 필요하다. 본문에서는 에너지이론에 기초한 일반 탄성안정이론을 소개하고, 평형경로 추적, 분기 좌굴점을 찾기 위한 직접법과 분기경로 전환에 관한 이론을 전개한다. 분기좌굴 해석예제로 트러스로 이루어진 스타돔, 핀지지의 평면아치, 평면프레임, 3차원 공간프레임의 분기좌굴 해석을 수행하여 본문에서 제시한 수치해석법의 정확성 및 실용성을 검증한다.