• Geomechanics and Engineering
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• 제17권4호
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• pp.343-354
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• 2019

The present study demonstrates the application of seismic petrophysics and amplitude versus angle (AVA) forward modeling to identify the reservoir fluids, discriminate their saturation levels and natural gas composition. Two case studies of the Lumshiwal Formation (mainly sandstone) of the Lower Cretaceous age have been studied from the Kohat Sub-basin and the Middle Indus Basin of Pakistan. The conventional angle-dependent reflection amplitudes such as P converted P ($R_{PP}$) and S ($R_{PS}$), S converted S ($R_{SS}$) and P ($R_{SP}$) and newly developed AVA attributes (${\Delta}R_{PP}$, ${\Delta}R_{PS}$, ${\Delta}R_{SS}$ and ${\Delta}R_{SP}$) are analyzed at different gas saturation levels in the reservoir rock. These attributes are generated by taking the differences between the water wet reflection coefficient and the reflection coefficient at unknown gas saturation. Intercept (A) and gradient (B) attributes are also computed and cross-plotted at different gas compositions and gas/water scenarios to define the AVO class of reservoir sands. The numerical simulation reveals that ${\Delta}R_{PP}$, ${\Delta}R_{PS}$, ${\Delta}R_{SS}$ and ${\Delta}R_{SP}$ are good indicators and able to distinguish low and high gas saturation with a high level of confidence as compared to conventional reflection amplitudes such as P-P, P-S, S-S and S-P. In A-B cross-plots, the gas lines move towards the fluid (wet) lines as the proportion of heavier gases increase in the Lumshiwal Sands. Because of the upper contacts with different sedimentary rocks (Shale/Limestone) in both wells, the same reservoir sand exhibits different response similar to AVO classes like class I and class IV. This study will help to analyze gas sands by using amplitude based attributes as direct gas indicators in further gas drilling wells in clastic successions.

• 항공우주시스템공학회지
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• 제16권1호
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• pp.49-55
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• 2022

최근 드론의 역할은 농업∙건설∙물류등의 다양한 영역으로 확대되고 있으며 특히 농업인구가 고령화되는 현 상황에 따라 드론은 노동력 부족 문제를 해결할 효과적인 대안으로 떠오르고 있다. 이에 본 논문에서는 농업 현장에서의 부족한 노동력을 보완하고 높은 위치의 과일도 안전하게 수확할 수 있는 드론 탑재형 과일수확 시스템을 제안한다. 과일수확 시스템은 과일인식 알고리즘과 과일수확 메커니즘으로 구성되어 있다. 과일인식 알고리즘은 딥러닝 기반의 객체탐지 알고리즘인 You Only Look Once를 사용하였고, 가상 시뮬레이션 환경을 구축하여 가능성을 검증하였다. 또한, 하나의 모터로 구동이 가능한 과일수확 메커니즘을 제안하였다. 모터의 회전운동을 기반으로 Scotch yoke을 구동시켜 선형운동으로 변환하여 gripper가 전개된 상태에서 과실에 접근 후 과실을 잡고 돌려 수확하는 메커니즘이다. 제안된 메커니즘에 대한 다물체동역학 해석을 수행하여 구동 가능성을 검증하였다.

• 한국통신학회논문지
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• 제22권6호
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• pp.1210-1230
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• 1997

본 논문에서는 기준신호를 나타내는 하나의 파일럿채널과 다수의 트래픽채널을 갖는 DS/CDMA용 송수신기구조를 제안한다. 파일럿채널은 데이타 변조가 되지 않은 순수 PN 부호성분을 전송하며 수신단에서 PN 동기 및 동기복조의 기준신호로 이용한다. 또한 이러한 구조는 순방향뿐만 아니라 역방향 링크에도 적용된다. 제안된 DS/CDMA 방식의 특징은 다음과 같다. 첫째, 트래픽채널의 확산 방식은 I-phase 및 Q-phase의 확산부호를 파일럿채널의 그것과 교차하게 배치한 interlaced quardrature-spreading(IQS) 구조를 갖는데 이는 기존의 확산방식에 비해 데이타 신호의 영교차율을 줄여 송신단 출력신호 레벨의 변화를 작게한다. 둘째, PN부호의 초기동기 및 동기초적시 임계값을 적응적으로 자동설정하며, 초기동기시 PN 부호를 한 칩씩 이동하게 하여, 기존의 방식에 비해 초기동기 시간을 절반으로 줄이게 했으며, 수신부에서 PN 부호 발생기를 하나만 사용하여 초기동기 및 동기추적이 되게했다. 또한 state machine을 이용하여 재동기 timing을 자동설정 하도록 설계했다. 셋째, 본 방식에서는 자동주파수조절(automatic frequency control: AFC)기능, 입력신호의 크기에 따라 능동적으로 유효한 출력 레벨을 조절하는 자동 레벨조절(automatic level control: ALC)기능, bit-error-rate(BER)을 자동계산하는 기능, 인접 채널과의 간섭을 최소화하기 위한 스펙트럼 성형기능 등을 도입하여 사용자 편의를 도모했다. 넷째, 데이타 전송속도를 16Kbps~1.024Mbps로 가변이 되게함으로써 다양한 응용에 대처할 수 있게 설계했다. 한편, 본 논문에서 제안한 DS/CDMA 모뎀구조는 다양한 simulation을 통하여, 알고리즘 검증 과정을 거쳤으며, 제안된 DS/CDMA 모뎀 구조는 VHDL을 이용하여 ASIC으로 구현하였다. DS/CDMA용 ASIC은 송신부 ASIC과 수신부 ASIC으로 나누어 개발 하였으며, 한개의 ASIC당 3개의 채널을 동시에 수용할 수 있으며, 다수의 ASIC을 사용하여 여러 채널의 다중접속이 가능하다. 제작완료된 ASIC은 기능시험을 완료했으며 실제 line-of-sight(LOS) 시스템 구현에 적용중이다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.91-93
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• 2003

A comprehensive numerical study is carried out to investigate for the understanding of the flow evolution and flame development in a supersonic combustor with normal injection of ncumally injecting hydrogen in airsupersonic flows. The formulation treats the complete conservation equations of mass, momentum, energy, and species concentration for a multi-component chemically reacting system. For the numerical simulation of supersonic combustion, multi-species Navier-Stokes equations and detailed chemistry of H2-Air is considered. It also accommodates a finite-rate chemical kinetics mechanism of hydrogen-air combustion GRI-Mech. 2.11[1], which consists of nine species and twenty-five reaction steps. Turbulence closure is achieved by means of a k-two-equation model (2). The governing equations are spatially discretized using a finite-volume approach, and temporally integrated by means of a second-order accurate implicit scheme (3-5).The supersonic combustor consists of a flat channel of 10 cm height and a fuel-injection slit of 0.1 cm width located at 10 cm downstream of the inlet. A cavity of 5 cm height and 20 cm width is installed at 15 cm downstream of the injection slit. A total of 936160 grids are used for the main-combustor flow passage, and 159161 grids for the cavity. The grids are clustered in the flow direction near the fuel injector and cavity, as well as in the vertical direction near the bottom wall. The no-slip and adiabatic conditions are assumed throughout the entire wall boundary. As a specific example, the inflow Mach number is assumed to be 3, and the temperature and pressure are 600 K and 0.1 MPa, respectively. Gaseous hydrogen at a temperature of 151.5 K is injected normal to the wall from a choked injector.A series of calculations were carried out by varying the fuel injection pressure from 0.5 to 1.5MPa. This amounts to changing the fuel mass flow rate or the overall equivalence ratio for different operating regimes. Figure 1 shows the instantaneous temperature fields in the supersonic combustor at four different conditions. The dark blue region represents the hot burned gases. At the fuel injection pressure of 0.5 MPa, the flame is stably anchored, but the flow field exhibits a high-amplitude oscillation. At the fuel injection pressure of 1.0 MPa, the Mach reflection occurs ahead of the injector. The interaction between the incoming air and the injection flow becomes much more complex, and the fuel/air mixing is strongly enhanced. The Mach reflection oscillates and results in a strong fluctuation in the combustor wall pressure. At the fuel injection pressure of 1.5MPa, the flow inside the combustor becomes nearly choked and the Mach reflection is displaced forward. The leading shock wave moves slowly toward the inlet, and eventually causes the combustor-upstart due to the thermal choking. The cavity appears to play a secondary role in driving the flow unsteadiness, in spite of its influence on the fuel/air mixing and flame evolution. Further investigation is necessary on this issue. The present study features detailed resolution of the flow and flame dynamics in the combustor, which was not typically available in most of the previous works. In particular, the oscillatory flow characteristics are captured at a scale sufficient to identify the underlying physical mechanisms. Much of the flow unsteadiness is not related to the cavity, but rather to the intrinsic unsteadiness in the flowfield, as also shown experimentally by Ben-Yakar et al. [6], The interactions between the unsteady flow and flame evolution may cause a large excursion of flow oscillation. The work appears to be the first of its kind in the numerical study of combustion oscillations in a supersonic combustor, although a similar phenomenon was previously reported experimentally. A more comprehensive discussion will be given in the final paper presented at the colloquium.