• 한국ITS학회 논문지
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• 제14권1호
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• pp.22-30
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• 2015

최근 교통문제를 완화하기 위하여 ITS를 적용하는 도로가 늘어나고 있다. 특히 가변전광표지(VMS: Variable Message Sign)는 전방도로상황, 기상상황 등 교통정보를 제공하여 교통흐름관리 및 교통안전관리를 하는 ITS 중 하나이다. 이런 VMS의 교통정보제공의 교통안전효과를 분석하기 위하여 현장조사를 통해 데이터를 수집하고 수집된 데이터에 대한 통계학적 검증을 시행하였다. VMS 교통정보제공 전 후의 차량주행특성은 교통정보제공 시 1차로와 2차로 모두 평균주행속도가 감소하고 차로 내 차량통행이 차로중심을 기준으로 통행하는 것으로 나타났다. 또한 VMS 교통정보제공이 교통안전효과에 미치는 영향을 분석하기 위하여 교통위험지역을 선정하고 구간을 통과하는 차량에 대한 확률분포를 Anderson-Darling Test를 통해 산정하여 비교하였다. 비교결과 1차로에서 VMS 교통정보제공으로 인해 교통안전효과가 차로양쪽 각각 0.69%와 7.07% 향상되는 것으로 나타났으며, 2차로의 경우 차로양쪽 각각 2.71%와 0.02% 향상되는 것으로 분석되었다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.671-679
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• 2008

The effect of Pre-cooled Turbojet Engine installation and nozzle exhaust jet on Hypersonic Turbojet EXperimental aircraft(HYTEX aircraft) were investigated by three-dimensional numerical analyses to obtain aerodynamic characteristics of the aircraft during its in-flight condition. First, simulations of wind tunnel experiment using small scale model of the aircraft with and without the rectangular duct reproducing engine was performed at M=5.1 condition in order to validate the calculation code. Here, good agreements with experimental data were obtained regarding centerline wall pressures on the aircraft and aerodynamic coefficients of forces and moments acting on the aircraft. Next, full scale integrated analysis of the aircraft and the engine were conducted for flight Mach numbers of M=5.0, 4.0, 3.5, 3.0, and 2.0. Increasing the angle of attack $\alpha$ of the aircraft in M=5.0 flight increased the mass flow rate of the air captured at the intake due to pre-compression effect of the nose shockwave, also increasing the thrust obtained at the engine plug nozzle. Sufficient thrust for acceleration were obtained at $\alpha=3$ and 5 degrees. Increase of flight Mach number at $\alpha=0$ degrees resulted in decrease of mass flow rate captured at the engine intake, and thus decrease in thrust at the nozzle. The thrust was sufficient for acceleration at M=3.5 and lower cases. Lift force on the aircraft was increased by the integration of engine on the aircraft for all varying angles of attack or flight Mach numbers. However, the slope of lift increase when increasing flight Mach number showed decrease as flight Mach number reach to M=5.0, due to the separation shockwave at the upper surface of the aircraft. Pitch moment of the aircraft was not affected by the installation of the engines for all angles of attack at M=5.0 condition. In low Mach number cases at $\alpha=0$ degrees, installation of the engines increased the pitch moment compared to no engine configuration. Installation of the engines increased the frictional drag on the aircraft, and its percentage to the total drag ranged between 30-50% for varying angle of attack in M=5.0 flight.