• 한국도로학회논문집
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• 제15권6호
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• pp.135-141
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• 2013

PURPOSES : The lack of details of design guideline for zig-zag shaped section approaching central bus stop leads an traffic accident proneness. So, this study analysed the geometric elements of central bus stop area in terms of vehicle dynamics and suggested design alternatives. METHODS : The study analysed a dynamic behaviour of bus moving in and out of zig-zag shaped section using Auto-Turn under scenarios. Based upon dynamic analysis, the study found out the width of overtaking lane is the most influential factor for a safe moving at zig-zag alignment. RESULTS : The width of overtaking lane at design speed of 40, 50, and 60 km/h respectively was suggested given taper ratio of 1 to 10 required for Bus Rapid Transit (BRT), and the lane width is not wider than 4.0m which possibly makes two vehicles using the same lane. Also, the width of overtaking lane which mitigates the taper ratio was suggested with the same restriction about the maximum lane width. CONCLUSIONS : The results of the study can be used to prepare a design guideline on zig-zag shaped alignment of central bus exclusive lanes. The more stable moving is expected by applying the design alternatives suggested, therefore the lower rate of traffic crashes at the vicinity of central bus stops.

• 대한교통학회지
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• 제26권4호
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• pp.251-264
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• 2008

정확하고 신뢰성 있는 실시간 교통자료의 수집은 다양한 교통운영관리 전략의 구현 및 교통정보제공을 위한 필수요소이다. 본 연구에서는 보다 seamless한 고급 교통정보가공을 위해 차량 간 무선통신기술(Vehicle-To-Vehicle Communication; V2V)을 활용한 새로운 교통정보수집체계를 제안하였다. GPS를 이용하여 개별차량의 주행궤적을 추출하고 V2V를 이용한 교통정보수집 방안을 제시하였다. 본 연구에서 제안한 교통정보수집체계의 기술적 요구사항분석을 위해 몬테카를로 시뮬레이션 기반의 평가체계를 개발하였다. 미시적 교통시뮬레이터 AIMSUN으로부터 개별차량의 주행궤적을 추출하고, 이를 이용한 구간통행시간 산출기법을 몬테카를로 시뮬레이션 기반 평가체계에 결합하여 기술적 요구사항을 도출하였다. 구간통행시간 정확도에 영향을 미치는 요인으로서 V2V 및 개별차량 주행궤적 추출이 가능한 equipped vehicle의 market penetration rate, V2V 통신반경, 통행시간 산출주기를 분석하였다. 또한, 제안된 시스템의 기술적 타당성 확인을 위해 prototypical implementation을 수행하였다. 본 연구의 결과물은 보다 seamless하고 정확한 교통정보가공을 위한 차세대 수집시스템 개발 및 구현을 위한 유용한 기초자료로 활용될 것으로 기대된다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2004년도 ICCAS
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• pp.57-62
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• 2004

This paper deals with a waypoint trajectory following problem for the tilt-rotor UAV under development in Korea (TR-KUAV). In this problem, dynamic model inversion based on the linearized model and Sigma-Phi neural network with adaptive weight update are involved to realize the waypoint following algorithm for the vehicle in the helicopter flight mode (nacelle angle=0 deg). This algorithms consists of two main parts: outer-loop system as a command generator and inner-loop system as stabilizing controller. In this waypoint following problem, the position information in the inertial axis is given to the outer-loop system. From this information, Attitude Command/Attitude Hold logic in the longitudinal channel and Rate Command/Attitude Hold logic in the lateral channel are realized in the inner-loop part of the overall structure of the waypoint following algorithm. The nonlinear simulation based on the TR-KUAV is carried out to evaluate the stability and performance of the algorithm. From the numerical simulation results, the algorithm shows very good tracking performance of passing the waypoints given. Especially, it is observed that ACAH/RCAH logic in the inner-loop has the satisfactory performance due to adaptive neural network in spite of the model error coming from the linear model based inversion.

• 대한교통학회지
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• 제20권2호
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• pp.81-92
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• 2002

차량과 보행자의 충돌시에는 충돌의 원인을 규명하는데 필요한 선회특성이 나타나게 된다. 지금까지의 연구에서는 보행자의 운동형태를 기초 물리학에서 유도된 공식으로 표현하였다. 그 결과 차량과 보행자의 다양한 변수에 대해 충분한 고려를 하지 못하였다. 그러한 한계를 극복하기 위하여 동역학적 시뮬레이션 프로그램인 MADYMO를 이용하여 다양한 조건하에서의 보행자 충돌 형태를 시뮬레이션하였다. 시뮬레이션에서 차체와 보행자 더미는 강체, 조인트, 스프링으로 모델링하였다. 보행자 시뮬레이션은 차량의 속도별로 수행되었으며 그 결과를 이전의 기초 물리학 공식과 비교하였는데 이전의 공식은 보행자의 상태조건을 제대로 반영하지 못함을 알수 있었다. 따라서, 보행자 충돌시에 차량과의 충돌현상에 대해 명확히 설명해 주는 동역학적 시뮬레이션을 사용하여야 한다.

• Journal of Astronomy and Space Sciences
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• 제35권3호
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• pp.119-131
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• 2018

In spite of a short history of only 30 years in space development, Korea has achieved outstanding space development capabilities, and became the $11^{th}$ member of the "Space Club" in 2013 by launching its own satellites with its own launch vehicle from a local space center. With the successful development and operation of more than 10 earth-orbiting satellites since 1999, Korea is now rapidly expanding its own aspirations to outer space exploration. Unlike earth-orbiting missions, planetary missions are more demanding of well-rounded technological capabilities, specifically trajectory design, analysis, and navigation. Because of the importance of relevant technologies, the Korean astronautical society devoted significant efforts to secure these basic technologies from the early 2000s. This paper revisits the numerous efforts conducted to date, specifically regarding flight dynamics and navigation technology, to prepare for future upcoming planetary missions in Korea. However, sustained efforts are still required to realize such challenging planetary missions, and efforts to date will significantly advance the relevant Korean technological capabilities.

• 대한전기학회:학술대회논문집
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• 대한전기학회 1995년도 하계학술대회 논문집 B
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• pp.874-876
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• 1995

Force and compliance control has been used in the control of legged walking vehicles to achieve superior terrain adaptability on rough terrains. The compliance control requires distribution of the vehicle load over the supporting legs. However, the constraint equations for ground reaction forces of supporting legs are generally underdetermined, allowing an infinite number of solutions. Thus, it is possible to apply an optimization criteria in solving the force setpoint problem. It has been observed that the previous force setpoint optimization methods sometimes cause a system stability problem and/or the load distribution among supporting legs is not well balanced due to a memory effect on the solution trajectory, This paper presents an iterative force setpoint method to solve this problem using an interpolation technique. By simulation it was shown that an excessive load unbalance among supporting legs and the memory effect in the force trajectory are alleviated much with the proposed method.

• Advances in aircraft and spacecraft science
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• 제7권3호
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• pp.271-290
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• 2020

The paper describes the analysis of deployment strategies and trajectories design suitable for executing the inspection of an operative spacecraft in orbit through re-usable CubeSats. Similar missions have been though indeed, and one mission recently flew from the International Space Station. However, it is important to underline that the inspection of an operative spacecraft in orbit features some peculiar characteristics which have not been demonstrated by any mission flown to date. The most critical aspects of the CubeSat inspection mission stem from safety issues and technology availability in the following areas: trajectory design and motion control of the inspector relative to the target, communications architecture, deployment and retrieval of the inspector, and observation needs. The objectives of the present study are 1) the identification of requirements applicable to the deployment of a nanosatellite from the mother-craft, which is also the subject of the inspection, and 2) the identification of solutions for the trajectories to be flown along the mission phases. The mission for the in-situ observation of Space Rider is proposed as reference case, but the conclusions are applicable to other targets such as the ISS, and they might also be useful for missions targeted at debris inspection.

• 한국추진공학회지
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• 제22권5호
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• pp.141-151
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• 2018

발사체 경량화에 따른 한국형발사체 투입성능 예측을 위해 궤적계산 프로그램을 작성하였다. 이 프로그램을 이용하여 단 별 구조비 감소 및 엔진 성능 개선에 따른 지구 저궤도 및 태양동기궤도 투입성능을 추정하였으며, 목표궤도에 투입 가능한 페이로드 중량을 성능 판단지표로 두었다. 한국형발사체의 구조비를 기존 대비 60% 수준까지 경량화 할 경우, 지구 저궤도 및 태양동기궤도에 최대 4.5톤, 3톤의 우주화물을 수송할 수 있을 것으로 보인다. 구조 경량화와 함께 90톤급, 10톤급의 개선 엔진을 탑재할 경우 태양동기궤도에 최대 3.65톤의 페이로드를 투입할 수 있다.

• 응용통계연구
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• 제34권5호
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• pp.773-794
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• 2021

교통량 예측은 지방 행정의 의사결정에 매우 중요한 정보를 제공한다. 교통량 예측을 통해 교통혼잡비용을 줄이고 지역경제를 활성화 함으로써 사회적, 경제적 이익을 창출할 수 있다. 교통량은 미지의 확률적 규칙하에서 시간의 흐름에 따라 궤적을 가지며 변화하는 함수데이터의 일종이다. 본 논문에서는 세 가지 함수회귀모형을 이용하여 과거에 관측된 교통량 궤적을 기반으로 미래의 관측되지 않은 교통량 궤적을 예측하는 방법을 제시한다. 본 논문에서 소개하는 세가지 방법은 전국 고속도로 영업소 중 서울, 춘천, 강릉 세 개 영업소에서 수집된 고속도로 영업소 데이터에 적용한다. 각 영업소 별로 세가지 방법의 예측오차를 비교함으로써 영업소별 최적 교통량 예측모형을 찾는다.

• Advances in aircraft and spacecraft science
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• 제7권4호
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• pp.371-385
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• 2020

A forward-facing aerospike attached to a payload fairing of a satellite launch vehicle significantly alters its flowfield and decreases the aerodynamic drag in transonic and low supersonic speeds. The present payload fairing is an axisymmetric configuration and consists of a blunt-nosed body along with a conical section, payload shroud, boat tail and followed by a booster. The main purpose of the present numerical simulations is to evaluate flowfield and assess the performance of aerodynamic drag coefficient with and without aerospike attached to a payload fairing of a typical satellite launch vehicle in freestream Mach number range 0.8 ≤ M_∞ ≤ 3.0 and freestream Reynolds number range 33.35 × 10⁶/m ≤ Re_∞ ≤ 46.75 × 10⁶/m whichincludes the maximum aerodynamic drag and maximum dynamic conditions during ascent flight trajectory of the satellite launch vehicle. A numerical simulation has been carried out to solve time-dependent compressible turbulent axisymmetric Reynolds-averaged Navier-Stokes equations. The closure of the system of equations is achieved using the Baldwin-Lomax turbulence model. The aerodynamic drag reduction mechanism is analysed employing numerical results such as velocity vector plots, density and Mach contours in conjunction with the experimental flow visualization pictures. The variations of wall pressure coefficient over the payload fairing with and without aerospike are exhibiting different kind of flowfield characteristics in the transonic and low supersonic speeds. The numerically computed results are compared with schlieren pictures, oil flow patterns and measured wall pressure distributions and exhibit good agreement between them.