• Journal of the Korean Society for Railway
• /
• v.13 no.6
• /
• pp.583-588
• /
• 2010

Track irregularities is one of key factors influencing running behavior of train. In order to ensure safety and ride comfort, it is highly important that relationship between track irregularity and running behavior of vehicle is identified and the criteria for track irregularities is adequately established. Numerical analysis was conducted to investigate influence of surface on running behavior of KTX and various wavelength and amplitude of surface were considered in numerical analysis. Derailment, lateral load, bogie acc., body acc. of numerical analysis results were investigated to evaluate the effect on track profile on safety and ride comfort of KTX.

• Aerospace Engineering and Technology
• /
• v.13 no.1
• /
• pp.96-107
• /
• 2014

Korea Aerospace Research Institute has a plan to launch experimental lunar orbiter in 2017, and lunar orbiter and lander in 2020. In the mission planning phase, LOI(Lunar Orbit Insertion) maneuver strategy should be designed using finite burn model because on-board propulsion system of lunar orbiter in finite burn type. LOI maneuver plan and amount of required ${\Delta}V$ using finite burn model depend on the spacecraft attitude at burn, a type of propellant, thrust level and burn timing. This paper describes the LOI maneuver of lunar orbiter of foreign space agency and then comes up with the LOI maneuver plan of Korean lunar orbiter. Adequate thrust level and burn duration of Korean lunar orbiter also present by performing simulation.

• Proceedings of the KIEE Conference
• /
• 2004.11c
• /
• pp.471-473
• /
• 2004

현재 세계적인 열차제어의 추세는 궤도회로에 의한 고정폐색방식을 이용한 열차 운행이 아닌 발리스 또는 무선통신에 의한 이동권한을 이용한 열차제어방식을 적용하고 있으며, 국내에서도 이에 맞추어 철도청에서는 ATP 사업을 통하여 발리스에 의한 이동권한을 이용한 열차제어시스템을 적용하고 있다. 기존의 궤도회로를 이용한 열차제어시스템에서는 열차를 궤도회로에 의해 검지하였으나 발리스 또는 무선통신에 의한 이동권한을 이용한 열차제어시스템에서는 궤도회로를 사용하지 않기 때문에 이에 패한 새로운 접근이 요구된다. 본 논문에서는 특히 발리스를 이용하였을 때 열차 검지 및 속도 검지를 위한 방안에 대해 연구하였다.

• Journal of Astronomy and Space Sciences
• /
• v.9 no.1
• /
• pp.120-125
• /
• 1992

The normalized line profiles of VV Cep have been calculated by integrating the equation of transfer. The Sobolev theory was adopted and the wind velocity distribution was assumed to be V(r) = V$\infty(1-R_c/r)^{1/2}$. The peaks of the line profiles for the phase 0.06 and 0.80 appear at near half maximum and zero velocity surface of the wind, respectively.

• Journal of Astronomy and Space Sciences
• /
• v.17 no.1
• /
• pp.107-116
• /
• 2000

This paper presents the preliminary survey and simulation results of the prediction of Leonid stream's orbital motion. Based on the model survey on eject velocity and perturbation of meteoroid particles, a simulation program was developed and applied to orbital motion of Leonid stream. The Jones ejection distribution model was used to describe the particle's eject velocity and the orbital dynamic model includes perturbations of major planet's gravity. DE405 ephemeris file generated by Solar System Dynamics Group at Jet Propulsion Laboratory in NASA was used for the planet's ephemeris calculations. Solar radiation pressure were also considered in the simulation and 8th order Runge-Kutta algorithm was used a numerical integration method.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2003.10a
• /
• pp.65-70
• /
• 2003

In this work variations of orbital parameters are first derived from the perturbation equations using difference equation method under Earth oblateness and atmospheric drag. A simple and effective scheme is proposed to compute the required delta v and fuel consumption to compensate for atmospheric drag. The scheme is applied to KOMPSAT example. And by means of numerical simulations we quantitatively analyze influences due to each perturbation source, i.e., nonspherical Earth, atmospheric drag, third body gravities (Sun, Moon), and solar radiation.

• Journal of the Korean Society for Railway
• /
• v.2 no.2
• /
• pp.15-20
• /
• 1999

철도의 초창기부터 선로 기술자들은 다음과 같은 목적을 위하여 최적의 궤도 표준을 달성하도록 노력하여 왔다. ㆍ 레일 이음매 보수의 제거 ㆍ 궤도 수명의 증가 ㆍ 더 높은 운전 속도와 더 무거운 하중을 위한 시설의 마련 ㆍ 승차감의 개선 이들 목적을 달성함에 있어 오랜 기간을 통하여 진보가 이루어져 왔으며, 이것은 장척과 장대 레일의 생산에서 가장 중요한 용접의 기술에 크게 의지하였다. 본고에서는 장대용접레일의 생산과 관련된 플래시 버트(Flash butt) 용접 기술의 원리와 고속철도용 장대용접 레일의 생산 등을 위하여 건설된 중앙궤도기지의 시설과 설비에 관하여 간략하게 소개한다.(중략)

• Journal of the Korean Geotechnical Society
• /
• v.29 no.10
• /
• pp.57-66
• /
• 2013

Societal interest on a faster transportation demands an increase of the train speed exceeding current operation speed of 350 km/h. To trace the pattern of variations in displacements and subsoil stresses in the concrete slab track system, finite element simulations were conducted. For a simple track-vehicle modeling, a mass-point system representing the moving train load was developed. Dynamic responses with various train speeds from 100 to 700 km/h were investigated. As train speeds increase the displacement at rail and subsoil increases nonlinearly, whereas significant dynamic amplification at the critical velocity has not been found. At low train speed, the velocity of elastic wave carrying elastic energy is faster than the train speed. At high train speed exceeding 400 km/h, however, the train speed is approximately identical to the elastic wave velocity. Nonlinearity in the stress history in subsoil is amplified with increasing train speeds, which may cause significant plastic strains in path-dependent subsoil materials.

• Journal of Aerospace System Engineering
• /
• v.18 no.1
• /
• pp.72-78
• /
• 2024

It is essential to coincide with moving target planet at future arrival changing point during space flight time in an interplanetary orbit design. Transition orbit elements can be obtained from traditional Lambert solutions by adjusting initial and final positions include flight time. Two-point boundary values of orbits can be selected in the design process. From this point of view, interplanetary orbits are infinite if they can be acquired from departure velocity without limit. However, appropriate and optimized procedures are needed to obtain an optimum interplanetary orbit to meet given conditions. The departure velocity is highly dependent on space launch vehicle's ability up to now. In this paper, algorithms of professor Howard Curtis at Embry-Riddle Aeronautical University were applied to obtain Lambert solution and orbit elements.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.177.2-177.2
• /
• 2012

위성의 궤도를 해석하기 위해서 일반적으로 STK(Satellite Tool Kit)나 Matlab Tool을 많이 사용한다. 이 도구들은 훌륭한 그래픽 사용자 인터페이스 환경과 다양한 라이브러리를 제공하기 때문에 사용하기에 상당히 편리하다. 하지만 STK의 경우는 다양한 해석을 수행하기 위한 Flexibility가 다소 제한적이고 상당히 고가라는 단점이 있으며, Matlab Tool의 경우는 계산 속도가 상대적으로 느려서 장기간에 대한 궤도해석이나 통계적인 분석에는 활용이 제한되는 측면이 있다. 항공우주연구원에서는 1993년부터 FORTRAN 언어로 구성된 Astro Library라는 궤도계산용 도구를 개발하였으며 그 후 정밀도를 개선하고 성능을 분석하는 작업들을 수행해 왔다. 또한 FORTRAN 언어가 가지는 비구조적인 특징으로 인하여 사용상 불편한 점들이 발견되어 Astro Library를 C++언어로 변환하여 객체화하는 작업을 수행하였다. 즉 시간, 태양, 지구, 달, 위성, 궤도 및 이들을 정의하는 속성을 각각의 객체로 정의하여 직관적으로 코딩 작업을 수행할 수 있도록 구성하였다. 개발된 프로그램은 무궁화위성, 천리안위성의 해석에 적용되어 편리성 및 정밀도가 입증되었다. 다양한 환경에서의 사용경험을 통하여 특히 복수위성에 대한 궤도 해석에 상당히 효과적임을 알 수 있었다. 본 논문에서는 개발된 궤도해석 프로그램인 Astro Library의 객체 구조에 대하여 정리하였고 몇 개의 적용 사례를 소개하였다.