• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2012년도 제38회 춘계학술대회논문집
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• pp.356-363
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• 2012

This paper addresses an analytical study on the gas-solid two phase flows in a nozzle. The primary purpose is to get recognition into the gas-solid suspension flows and to investigate the particle motion and its influence on the gas flow field. The present study is the primal step to comprehend the gas-solid suspension flow in the convergent-divergent nozzle. This paper try to made a development of an analytical model to study the back pressure ratio, particles loading and the particle diameter effect on gas-solid suspension flow. Mathematical model of gas-solid two phase flow was developed based on the single phase flow models to solve the quasi-one-dimensional mass, momentum equations to calculate the steady pressure field. The influence of particles loading and particle diameter is analyzed. The results obtained show that the suspension flow of smaller diameter particles has almost same trend as that of single phase flow using ideal gas as working fluid. And the presence of particles will weaken the strength of the shock wave; the bigger particle will have larger slip velocity with gas flow. The thrust coefficient is found to be higher for larger particles/gas loading or back pressure ratio, but it also depends on the ambient pressure.

• Wind and Structures
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• 제17권3호
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• pp.263-274
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• 2013

A numerical technique for fluid-structure interaction, which is based on the finite element method (FEM) and computational fluid dynamics (CFD), was developed for application to an industrial chimney equipped with a pendulum tuned mass damper (TMD). In order to solve the structural problem, a one-dimensional beam model (Navier-Bernoulli) was considered and, for the dynamical problem, the standard second-order Newmark method was used. Navier-Stokes equations for incompressible flow are solved in several horizontal planes to determine the pressure in the boundary of the corresponding cross-section of the chimney. Forces per unit length were obtained by integrating the pressure and are introduced in the structure using standard FEM interpolation techniques. For the fluid problem, a fractional step scheme based on a second order pressure splitting has been used. In each fluid plane, the displacements have been taken into account considering an Arbitrary Lagrangian Eulerian approach. The stabilization of convection and diffusion terms is achieved by means of quasi-static orthogonal subscales. For each period of time, the fluid problem was solved and the geometry of the mesh of each fluid plane is updated according to the structure displacements. Using this technique, along-wind and across-wind effects have been properly explained. The method was applied to an industrial chimney in three scenarios (with or without TMD and for different damping values) and for two wind speeds, showing different responses.

• 반도체디스플레이기술학회지
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• 제8권3호
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• pp.31-37
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• 2009

This paper presents one and two dimensional simulation results with discontinuous features (shocks) of capacitively coupled rf plasmas. The model consists of the first two and three moments of the Boltzmann equation for the ion and electron fluids respectively, coupled to Poisson's equation for the self-consistent electric field. The local field and drift-diffusion approximations are not employed, and as a result the charged species conservation equations are hyperbolic in nature. Hyperbolic equations may develop discontinuous solutions even if their initial conditions are smooth. Indeed, in this work, secondary electron emission is shown to produce transient electron shock waves. These shocks form at the boundary between the cathodic sheath (CS) and the quasi-neutral (QN) bulk region. In the CS, the electrons emitted from the electrode are accelerated to supersonic velocities due to the large electric field. On the other hand, in the QN the electric field is not significant and electrons have small directed velocities. Therefore, at the transition between these regions, the electron fluid decelerates from a supersonic to a subsonic velocity in the direction of flow and a jump in the electron velocity develops. The presented numerical results are consistent with both experimental observations and kinetic simulations.

• 한국추진공학회지
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• 제22권6호
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• pp.37-46
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• 2018

초음속 연소기에 대해 연료에 의한 연소기 재생 냉각을 가정하여 재생 냉각 유로 형상 설계를 수행하였다. 준일차원 모델을 사용하여 고온 측 및 저온 측 유동 계산을 수행하였으며 이 과정에서 양쪽 사이의 열전달을 계산하였다. 기준 형상에서 총 열교환량은 10.7 kW, 열유속은 $566kW/m^2$, 열교환기 입출구에서의 연료 온도 변화는 153 K으로 계산되었다. 7개의 열교환기 유로 형상에 대하여 열전달 성능을 비교하였다.

• Smart Structures and Systems
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• 제24권2호
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• pp.173-182
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• 2019

Due to the degradation of beamforming properties at angles close to $0^{\circ}$ to $180^{\circ}$, linear array does not have a complete $180^{\circ}$ inspection range but a smaller one. This paper develops a improved sensor array with two additional sensors above and below the linear sensor array, and presents time difference and two dimensional multiple signal classification (2D-MUSIC) based impact localization for omni-directional localization on composite structures. Firstly, the arrival times of impact signal observed by two additional sensors are determined using the wavelet transform and compared, and the direction range of impact source can be decided in general, $0^{\circ}$ to $180^{\circ}$ or $180^{\circ}$ to $360^{\circ}$. And then, 2D-MUSIC based spatial spectrum formula using uniform linear array is applied for locate accurate position of impact source. When the arrival time of impact signal observed by two additional sensors is equal, the direction of impact source can be located at $0^{\circ}$ or $180^{\circ}$ by comparing the first and last sensor of linear array. And then the distance is estimated by time difference algorithm. To verify the proposed approach, it is applied to a quasi-isotropic epoxy laminate plate and a stiffened composite panel. The results are in good agreement with the actual impact occurring position.

• 한국재료학회지
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• 제31권1호
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• pp.43-53
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• 2021

Dynamic behavior of piezoelectric ZnO nanowires is investigated using finite element analyses (FEA) on FE models constructed based on previous experimental observations in which nanowires having aspect ratios of 1:2. 1:31, and 1:57 are obtained during a hydrothermal process. Modal analyses predict that nanowires will vibrate in lateral bending, uniaxial elongation/contraction, and twisting (torsion), respectively, for the three ratios. The natural frequency for each vibration mode varies depending on the aspect ratio, while the frequencies are in a range of 7.233 MHz to 3.393 GHz. Subsequent transient response analysis predicts that the nanowires will behave quasi-statically within the load frequency range below 10 MHz, implying that the ZnO nanowires have application potentials as structural members of electromechanical systems including nano piezoelectric generators and piezoelectric dynamic strain sensors. When an electric pulse signal is simulated, it is predicted that the nanowires will deform in accordance with the electric signal. Once the electric signal is removed, the nanowires exhibit a specific resonance-like vibration, with the frequency synchronized to the signal frequency. These predictions indicate that the nanowires have additional application potential as piezoelectric actuators and resonators.

• 한국추진공학회지
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• 제26권1호
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• pp.20-27
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• 2022

본 나노에너지 기술 해석연구에서는 알루미늄/니켈 나노 다층박막구조 내 이종금속 반응파의 박막층 수직방향 전파현상을 대상으로 모델링 및 해석을 진행하였다. Al/Ni층이 교차하는 반무한영역에서 열 및 화학종 확산 방정식을 기반으로 1차원적 전산해석을 수행하였다. 해석결과로 이종금속 반응파의 수직방향 정상 전파 확립 등 반응파 특성을 발견하였다. 수평방향 전파현상 해석과 비교하여 이와 같은 나노구조물에서 반응파 자체전파속도에 대한 방향성 변화 영향이 매우 약하게 나타남을 확인하였다.

• Advances in aircraft and spacecraft science
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• 제10권1호
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• pp.1-18
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• 2023

This paper investigates the integrated control of an air-breathing hypersonic vehicle considering the safety of propulsion system under acceleration. First, the vehicle/engine coupling model that contains a control-oriented vehicle model and a quasi-one-dimensional dual-mode scramjet model is established. Next, the coupling process of the integrated control system is introduced in detail. Based on the coupling model, the integrated control framework is studied and an integrated control system including acceleration command generator, vehicle attitude control loop and engine multivariable control loop is discussed. Then, the effectiveness and superiority of the integrated control system are verified through the comparison of normal case and limiting case of an air-breathing hypersonic scramjet coupling model. Finally, the main results show that under normal acceleration case and limiting acceleration case, the integrated control system can track the altitude and speed of the vehicle extremely well and adjust the angle deflection of elevator to offset the thrust moment to maintain the attitude stability of the vehicle, while assigning the two-stage fuel equivalent ratio to meet the thrust performance and safety margin of the engine. Meanwhile, the high-acceleration requirement of the air-breathing hypersonic vehicle makes the propulsion system operating closer to the extreme dangerous conditions. The above contents demonstrate that considering the propulsion system safety will make integrated control system more real and meaningful.

• Communications for Statistical Applications and Methods
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• 제15권4호
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• pp.563-585
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• 2008

본 연구는 다양하고 복잡해지는 파생상품 추세에 상응하는 적절한 가치평가에 대한 연구의 필요성을 인지하고 가격 및 민감도 평가에 있어서 속도와 정확도를 향상시키는데 그 의의를 두고자 한다. 몬테카를로 시뮬레이션에서 의사난수 대신 저불일치수열인준난수를 이용하면 시행횟수의 감소와 정확도 개선이 가능한데, 미국형 옵션이나 경로의존형 상품 등 다차원의 난수가 필요할 경우 기존의 준난수를 사용하면 상관관계가 증가하는 문제로 적용에 한계가 있다. 이런 단점을 보완하기 위해 문제를 발생시키는 차원의 난수를 제외시켜 상관계수를 특정값 이하로 제어하는 새로운 방법을 고안하여 다차원 상품에 적용이 가능토록 하였고 미국형 풋옵션에 적용하여 새로운 방법의 유용성을 검증하였다. 또한, 몬테카를로 시뮬레이션에서 민감도 계산방법으로 우도비율법과 경로의존형 근사방법을 사용하면 속도 및 정확도가 개선됨을 보인다. 이러한 결과는 최근 시장의 추세인 기초자산이나 위험요소가 여러 개인 경우 그리고 경로의존형 및 조기상환형 상품 등에 적용 가능토록하여 몬테카를로 시뮬레이션 방법에 있어 가장 큰 단점으로 지적되는 수행시간을 단축시키고 민감도 계산의 오차를 줄여줌을 보여준다. 또한, 2개 이하의 기초자산으로 이루어진 파생상품의 가치 및 민감도 평가에 가장 효율적인 수치해석적 방법론으로 알려져 있는 유한차분법의 적용시 격자생성구간의 설정이 매우 중요하다는 사실을 비대칭 나비형스프레드에 적용하여 실증적으로 보인다.

• 한국항공우주학회지
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• 제36권2호
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• pp.156-162
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• 2008

본 연구에서는 자유후류기법을 이용하여 복합재 무힌지 로터 블레이드에 대한 정적 공탄성 해석을 수행하였다. 1차원 보의 거동을 해석하기 위하여 대변형 보 이론이 적용되었다. 또한, 복합재 블레이드의 단면 해석을 위하여 이방성 보 이론이 적용되었다. 공탄성 해석에 필요한 공력 하중들은 와류격자법(VLM)에 기초한 3차원 공기력 모델을 통하여 계산되었다. 이때, 정지비행시의 후류는 순차적 시간 적분 자유후류법을 통하여 묘사되었다. 복합재 무힌지 로터 블레이드의 정적 변형에 대한 해석 결과를 2차원 준정상 공기력과 경험후류기법을 통한 해석 결과들과 비교하여 살펴보았다. 결과적으로, 정지비행시 후류 효과에 의해 정적 변형의 결과가 달라짐을 확인하였다.