• 한국산학기술학회논문지
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• 제16권5호
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• pp.3610-3618
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• 2015

도시철도 차량 및 역사 내 혼잡도가 최고 220%를 나타내고 있다. 특히 방향별 동선의 충돌로 인해 보행자의 이동저항이 급속히 증가해 통행시간 증가, 안전사고 발생 등 도시철도 역사의 이용효율을 저해하는 요인으로 작용하고 있다. 이러한 문제를 해결하고자 본 논문에서 도시철도 이용객의 역사 내 이동속도 및 쾌적성 향상을 위한 혼잡관리 모형을 이용한 도시철도 이용객 동선유도시스템을 제안한다. 이를 위하여 반복혼잡/비반복혼잡을 고려할 수 있는 혼잡관리 모형을 구성하셨고, 미들웨어시스템, 제어시스템, 동선유도구동시스템으로 구성된 동선유도시스템의 기본설계를 수행하였다. 동선유도시스템은 외부데이터를 알고리즘에서 사용가능한 형태로 변경하는 미들웨어시스템 단계와 실시간 데이터 및 과거 데이터를 통해 혼잡관리 알고리즘을 수행하는 단계와, 산정된 혼잡관리 알고리즘을 기반으로 LED표시장치, 방향유도 표시기, 이동식 가이드레일 등을 제어하는 제어시스템의 단계와 제어시스템의 정보를 기반으로 LED표시장치, 방향유도 표시기, 이동식 가이드레일 등의 장치를 실제로 구동하는 동선유도 구동장치 단계와 이용자가 실제로 접하는 LED표시장치, 방향유도 표시기, 이동식 가이드레일 등의 동선유도장치로 이루어진다. 향후 본 기본설계를 기반으로 시스템의 상세설계를 통해 도시철도 역사의 구조 및 지점에 따른 다양한 동선유도장치의 시작품을 제작하고 이를 제어할 수 있는 동선유도제어 모듈을 개발할 예정이다.

• International Journal of Ocean System Engineering
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• 제2권3호
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• pp.139-150
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• 2012

This paper presents an improved guidance algorithm for autonomous underwater vehicles (AUV) in 3D space for generating smoother vehicle turn during the course change at the way-points. The way-point guidance by the line-of-sight (LOS) method has been modified for correcting the reference angles to achieve minimal calculation and smoother transition at the way-points. The algorithm has two phases in which the first phase brings the vehicle to converge to a distance threshold point on the line segment connecting the first two way-points and the next phase generates an angular path with smoother transition at the way-points. Then the desired angles are calculated from the reference and correction angles. The path points are regularly parameterized in the spherical coordinates and mapped to the Cartesian coordinates. The proposed algorithm is found to be simple and can be used for real time implementation. The details of the algorithm and simulation results are presented.

• 전기학회논문지
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• 제60권6호
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• pp.1229-1238
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• 2011

This paper deals with the lateral dynamic model of an all-wheel steered articulated vehicle to design a guidance controller. Nonlinear dynamic model of articulated vehicle is developed by complementing the model about the BRT system of California PATH in U. S. A. and the Phileas system of the APTS in Netherlands. Linear lateral dynamic model has been derived from the nonlinear dynamic model under some assumptions associated with the driving conditions. To design a guidance controller, we derive a transfer function that is steering angle as input and lateral acceleration as output from the linear lateral dynamic model by applying the parameter of vehicle that is developed by Korea Railroad Research Institute. To validate the dynamic model, nonlinear dynamic model has been compared with a vehicle model that has been programmed in ADAMS, and linear dynamic model has been compared with a nonlinear dynamic model under sime assumptions.

• 한국산업정보학회논문지
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• 제7권2호
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• pp.40-45
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• 2002

본 논문에서는 웹을 통하여 탈놀이에 관한 멀티미디어 정보를 제공하는 에이전트 기반의 탈놀이안내 시스템을 설계하고 구현한다. 사용자가 요구사항을 입력하면 클라이언트는 서버에게 이를 전송하고, 서버는 입력된 조건을 만족하는 탈놀이의 동영상 및 안내음성을 웹을 통하여 클라이언트에게 전송하여 상영한다. 본 논문에서는 에이전트 기반의 안내 시스템을 개발하기 위하여 인터페이스 에이전트, 사용자 모델링 에이전트, 중재 에이전트, 자료관리 에이전트를 설계하고 구현하였다. 또한 개발한 탈놀이 안내 시스템은 멀티미디어 데이터를 생성하는 기본기능 외에도 키워드를 이용한 검색 학습 등의 다양한 기능을 제공한다.

• International Journal of Aeronautical and Space Sciences
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• 제13권1호
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• pp.90-98
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• 2012

In this paper, the Integrated Guidance and Control (IGC) law is proposed for the Rotary Unmanned Aerial Vehicle (RUAV). The objective of the IGC law is to consider the nonlinear dynamic characteristics of the RUAV and to design a guidance law which takes into consideration the nonlinear relationship between kinematics and dynamics. In order to control the RUAV system, sliding mode control scheme is adopted. As the RUAV is an under-actuated system, a slack variable approach is used to generate the available control inputs. Through the Lyapunov stability theorem, the stability of the proposed IGC law is proved. In order to verify the performance of the IGC law, numerical simulations are performed for waypoint tracking missions.

• Journal of Mechanical Science and Technology
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• 제16권6호
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• pp.770-775
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• 2002

In this paper, a game optimal receding horizon guidance law (GRHG) is proposed, which does not use information of the time-to-go and target maneuvers. It is shown that by adjusting design parameters appropriately, the proposed GRHG is identical to the existing receding horizon guidance law (RHG), which can intercept the target by keeping the relative vertical separation less than the given value, within which the warhead of the missile is detonated, after the appropriately selected time in the presence of arbitrary target maneuvers and initial relative vertical separation rates between the target and missile. Through a simulation study, the performance of the GRHG is illustrated and compared with that of the existing optimal guidance law (OGL).

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.482-485
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• 1996

We design a homing guidance law based on the proportional navigation for the fast-rolling, single-axis control missiles and analyse the misdistance of the designed guidance system. The guidance law includes a compensation scheme which compensates for the phase-shift between the commanded and achieved acceleration which is peculiar to the fast rolling airframe with single-axis control. In the error analysis of the guidance system, we calculate the misdistance with respect to the target maneuver on the 3-dimensional space via direct simulations. Also, we conduct adjoint simulation on the 2-dimensional plane in case that phase-shift is perfectly compensated. Finally we approximate the linear time-varying dynamics of the missile with autopilot to a linear time-invarient system, and as a result we can find the misdistance as a closed-form.

• 제어로봇시스템학회논문지
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• 제7권2호
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• pp.173-182
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• 2001

Ascent trajectory optimization and optimal explicit guidance problems for a satellite launch vehicle in a 2-dimensional pitch plane are studied. The trajectory optimization problem with boundary conditions is formulated as a nonlinear programming problem by parameterizing the pitch attitude control variable, and is solved by using the SQP algorithm. The flight constraints such as gravity-turn are imposed. An optimal explicit guidance algorithm in the exoatmospheric phase is also presented, the guidance algorithm provides steering command and time-to-go value directly using the current states of the vehicle and the desired orbit insertion conditions. To verify the optimality and accuracy of the algorithm simulations are performed.

• 제어로봇시스템학회논문지
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• 제20권11호
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• pp.1085-1091
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• 2014

This paper presents the guidance and control design for automatic carrier landing of a UAV (Unmanned Aerial Vehicle). Differently from automatic landing on a runway on the ground, the motion of a carrier deck is not fixed and affected by external factors such as ship movement and sea state. For this reason, robust guidance/control law is required for safe shipboard landing by taking the relative geometry between the UAV and the carrier deck into account. In this work, linear quadratic optimal controller and longitudinal/lateral trajectory tracking guidance algorithm are developed based on a linear UAV model. The feasibility of the proposed control scheme and guidance law for the carrier landing are verified via numerical simulations using X-Plane and Matlab/simulink.

• 한국항공운항학회지
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• 제23권1호
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• pp.49-55
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• 2015

This paper deals with dynamic modeling and controller design of a future Korean lunar module planned to be launched 2020's in Korea. For dynamic modeling of the lunar module, we first assume the lunar module as a rigid body. And we derive equations of motion for the lunar module by considering allocation of main thrusters and reaction thrusters. With the equation of motion, we design the controller based on the quaternion. A Pulse Width Pulse Frequency modulator(PWPFM) is selected for generating on/off signal. Finally, we construct a 2-phase descent mode including initial guidance mode, terminal guidance mode. The MATLAB simulation is performed for evaluating the descent ability and final landing velocity. The dynamic modeling and descent simulation of the lunar module in this paper could be applied for developing the future work of the Korean lunar exploration program.