• 한국공간정보시스템학회:학술대회논문집
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• 2005.11a
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• pp.169-174
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• 2005

위치기반서비스(LBS)에서는 사람, 차량과 같은 이동체의 위치 정보를 획득하며, 이동객체 DBMS의 개발로 이동체가 움직인 궤적 정보를 효율적으로 저장 관리할 수 있다. 이동객체 DBMS에 저장된 이동체가 실제 움직인 과거 궤적정보는 다양한 형태로 가공되어 활용이 가능하다. 본 논문에서는 이동체의 과거 궤적정보를 이용하여 경로 안내를 위한 경로 산출 방법에 대하여 제안한다. 기존의 경로 안내는 교통정보 수집 장치를 통해 획득한 교통 정보를 이용하여 경로를 산출하는 방식이 많이 사용되고 있어, 교통 정보가 없는 곳에서는 단순 초행길 안내 수준이다. 그러나, 본 논문에서 제안하는 방법은 고비용이 소요되는 교통정보수집장치가 없는 곳에 대해서도 과거 차량의 움직인 궤적정보를 이용하여 보다 효율적인 경로 안내를 할 수 있는 장점이 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.72-80
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• 2004

In this paper, the design procedure of a guidance algorithm in the boosting phase of missiles with free-flight after thrust cut-off is introduced. The purpose of the guidance is to achieve a required velocity vector at the thrust cut-off. Trajectory optimizations for four cost functions are performed to investigate implementable trajectories in the pitch plane. It is observed from the optimization results that high angle of attack maneuver in the beginning of the flight are required to satisfy the constraints. The proposed guidance algorithm consists of the pitch program to produce open-loop pitch attitude command and the yaw attitude command generator to nullify the velocity to go. The pitch program utilizes the pitch attitude histories obtained from the trajectory optimization.

• Journal of Korean Society of Transportation
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• v.29 no.3
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• pp.73-82
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• 2011

Recent advancement in traffic surveillance systems has allowed the researchers to obtain more detailed vehicular movement such as individual vehicle trajectory data. Understanding the characteristics of interactions between leading and following vehicles in the traffic flow stream is a backbone for designing and evaluating more sophisticated traffic and vehicle control strategies. This study proposes a methodology for estimating rear-end crash potential, as a probabilistic measure, in real-time based on the analysis of vehicular movements. The methodology presented in this study consists of three components. The first predicts vehicle position and speed every second using a Kalman filtering technique. The second estimates the probability for the vehicle's trajectory to belong to either 'changing lane' or 'going straight'. A binary logistic regression (BLR) is used to model the lane-changing decision of the subject vehicle. The other component calculates crash probability by employing an exponential decay function that uses time-to-collision (TTC) between the subject vehicle and the front vehicle. The result of this study is expected to be adapted in developing traffic control and information systems, in particular, for crash prevention.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.5
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• pp.46-55
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• 2006

In general, 3-dimensional point-mass equation has been widely used for the trajectory optimization of the fixed-wing aircraft and reentry vehicle. But it should be modified and represent target vehicle's own characteristics. For a lighter-than-air vehicle such as an airship, there exists different and peculiar flight characteristics compared with the aircraft. The first part of this paper is to derive the dynamic equation of motion for the mid-altitude unmanned airship and the second part is to obtain the optimal trajectories under the minimal time flight given constraints. The trajectory optimization problem is converted into the nonlinear programming problem using Sequential Quadratic Programming approach. Finally numerical solutions are presented in the last part of the paper.

• Korean Journal of Remote Sensing
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• v.30 no.1
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• pp.13-24
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• 2014

Satellite remote sensing data have been valuable tool for volcanic ash monitoring. In this study, we present the results of application of satellite remote sensing data for monitoring of volcanic ash for three major volcanic eruption cases (2008 Chait$\acute{e}$n, 2010 Eyjafjallaj$\ddot{o}$kull, and 2011 Shinmoedake volcanoes). Volcanic ash detection products based on the Moderate Resolution Imaging Spectro-radiometer (MODIS) observation data using infrared brightness temperature difference technique were compared to the forward air mass trajectory analysis by the HYbrid Single-Particle Lagrangian Integrated Trajectory (HYSPLIT) model. There was good correlation between MODIS volcanic ash image and trajectory lines after the volcanic eruptions, which support the feasibility of using the integration of satellite observed and model derived data for volcanic ash forecasting.

• Bulletin of the Korean Space Science Society
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• 2004.04a
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• pp.58-58
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• 2004

인공위성 편대비행에서는 위성간 거리가 수 미터에서 수 킬로미터에 달하기 때문에 궤도 배치 및 재배치시 위성간 충돌의 문제는 매우 중요하다. 따라서 궤도 배치 및 재배치 단계에서 위성간 충돌을 피하고, 연료소모를 최소화시키면서 목적한 최종 배치를 만족시키는 최적경로를 산출하는 방법이 최근들어 연구되고 있다. 최적 경로를 산출하는 궤적 최적화 (Trajectory optimization) 문제를 풀기 위한 방법으로 크게 직접적인 (Direct) 방법과 간접적인 (Indirect) 방법이 있다. (중략)

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.173-181
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• 2013

In this paper, the design result of the trajectory-based air traffic analysis software which is going to be used to assess air-traffic efficiency in case that some modification's made in dynamic airspace configuration, is described. The software has been developed to make statistical data about air-traffic in Incheon FIR based on the RPL, and to analyze the airway utilization and controller workload using the trajectory modeling data which are derived from the aircraft type, cruise speed, cruise altitude, and routes and fixes in the RPL. Since it batch-processes the long-term trajectory data with other inputs such as airspace, route information and so on, it has the advantage of quickly predicting the traffic variation when some change in airspace and route information is made.

• Journal of Astronomy and Space Sciences
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• v.22 no.4
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• pp.451-462
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• 2005

Optimal Trajectory Correction Maneuver (TCM) design algorithm has been developed using the B-plane targeting method for future Korean Mars missions. For every-mission phase, trajectory informations can also be obtained using this developed algorithms which are essential to design optimal TCM strategy. The information were computed under minimum requiring perturbations to design Mars missions. Spacecraft can not be reached at designed aim point because of unexpected trajectory errors, caused by many perturbations and errors due to operating impulsive maneuvers during the cruising phase of missions. To maintain spacecraft's appropriate trajectory and deliver it to the designed aim point, B-plane targeting techniques are needed. A software NPSOL is used to solve this optimization problem, with the performance index of minimizing total amount of TCM's magnitude. And also executing time of maneuvers on be controlled for the user defined maneuver number $(1\~5)$ of TCMs. The constraints, the Mars arrival B-plane boundary conditions, are formulated for the problem. Results of this work show the ability to design and analyze overall Mars missions, from the Earth launch phase to Mars arrival phase including capture orbit status for future Korean Mars missions

• Journal of Korean Ophthalmic Optics Society
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• v.15 no.3
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• pp.257-262
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• 2010

Purpose: Developing a calculating program for the prism power which influenced the binocular vision according to shifts of binocular visual points in the distance vision spectacles. Methods: By using the Delphi 6.0 programming language, we developed a calculating program of the relative binocular prism power according to the movements of binocular visual points in the distance vision spectacles, which was calculated by dragging the mouse along the traces of binocular visual points on the computer window. Results: We developed a calculating program for the relative binocular prism power according to the movements of binocular visual points in the distance vision spectacles. The user of the program could confirm the trace of visual points by allowing them to display the trace of binocular visual points on the computer screen with a mouse button. An application on confirming the variation of prism power by graphs in the program also allowed the user to use the program more conveniently. Conclusions: By using the developed program, the user could easily calculate the relative binocular prism power according to shifts of binocular visual points in the distance vision spectacles. We also found that the developed program helped the user to receive a lot of assistance in analyzing the asthenopia.

• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.26.3-27
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• 2009

한 기의 영상레이더 위성을 이용하여 동일한 촬영지역에 대해 적절한 기선벡터(Baseline)을 유지하는 두 장(scene)의 영상을 획득하여 그 지역의 정밀 표고차를 추출하는 레이더 간섭계(Interferometry) 임무를 수행하기 위해서는 반복지상궤적을 유지하도록 위성의 궤도를 주기적으로 조정해 주어야 한다. 이 연구에서는 반복지상궤적 유지 정밀도를 극대화시키기 위하여 최적의 기준궤도를 생성하고 이를 유지하기 위한 속도증분 및 궤도 조정 일정을 산출할 수 있는 궤도최적화 S/W 를 개발하였다. 이 연구의 최적 궤도 설계 문제는 다음과 같다. "시작시간 $T_0$에서 초기 접촉궤도 상태벡터 (ECEF 위치 및 속도벡터) $x_0$이고, 지상궤적반복주기 p 이후의 시간 $T_0+p$에서도 초기 접촉궤도 상태벡터와 동일한$x_0$가 되도록 궤도를 유지하려고 할 때, 여명 궤도(dawn-dusk and sun-synchronous orbit)에서 운영되는 위성의 연료소모(또는 속도증분)를 최소화시키는 가상의 궤도조정(maneuver) 횟수, 시기, 크기를 찾아라." 이 연구에서는 궤도최적화 문제를 풀기 위하여 GRACE 중력모델(GGM02C)이 적용된 수치적 방법의 위성궤도예측 알고리즘을 시스템 설계에 적용하였고, 매개변수 최적화 방법 중 구속조건이 있는 비선형 최적화 기법의 하나인 연속 2차 계획법(sequential quadratic programming)을 사용하여 해를 구하였다. 개발된 궤도최적화 S/W의 성능을 분석하기 위하여 고도 550km의 여명궤도를 돌며 지상궤적반복주기가 28일인 영상레이더 위성에 대해 적용하였다. 해석 결과를 통해, 비록 시스템의 비선형이 큼에도 불구하고 최소의 속도증분으로 정밀한 반복지상궤적이 유지됨을 알 수 있었다.