• 한국정밀공학회지
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• 제13권4호
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• pp.75-86
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• 1996

In this paper, we propose a new fuzzy-neural network control scheme for the speed and azimuth control of a mobile robot. The proposed control scheme uses a gaussian function as a unit function in the fuzzy-neural network, and back propagation algorithm to train the fuzzy-neural network controller in the frame-work of the specialized learning architecture. It is proposed a learning controller consisting of two fuzzy-neural networks based on independent reasoning and a connection net woth fixed weights to simply the fuzzy-neural network. The effectiveness of the proposed controller is illustrated by performing the computer simulation for a circular trajectory tracking of a mobile robot driven by two independent wheels.

• 로봇학회논문지
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• 제19권1호
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• pp.8-15
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• 2024

This paper proposes a linear model predictive control of 6-DOF remotely operated underwater vehicles using nonlinear robust internal-loop compensator (NRIC). First, we design a integrator embedded linear model prediction controller for a linear nominal model, and then let the real model follow the values calculated through forward dynamics. This work is carried out through an NRIC and in this process, modeling errors and external disturbance are compensated. This concept is similar to disturbance observer-based control, but it has the difference that H_∞ optimality is guaranteed. Finally, tracking results at trajectory containing the velocity discontinuity point and the position tracking performance in the disturbance environment is confirmed through the comparative study with a traditional inverse dynamics PD controller.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.168-173
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• 2003

In this paper, we will present a deeper look on optimal design methods that are related to path-planning for a mobile robot. To control the motion of a mobile robot in a clustered environment, it's necessary to know a suitable trajectory assuming certain start and goal point. Up to now, there are many literatures that concern optimal path planning for an obstacle avoided mobile robot. Among those literatures, we have chosen 2 novel methods for our further analysis. The first approach [4] is based on HJB(Hamilton-Jacobi-Bellman) equation whose solution is the return-function that helps to generate a shortest path to the goal. The later [5] is called polynomial-path-planning approach, in this method, a shortest polynomial-shape path would become a solution if it was a collision-free path. The camera network plays the role as sensors to generate updated map which locates the static and dynamic objects in the space. Therefore, the exhibition of both path planning and dynamic obstacle avoidance by the updated map would be accomplished simultaneously. As we mentioned before, our research will include the motion control of a true mobile robot on those optimal planned paths which were generated by above algorithms. Base on the kinematic and dynamic simulation results, we can realize the affection of moving speed to the stable of motion on each generated path. Also, we can verify the time-optimal trajectory through velocity tuning. To simplify for our analysis, we assumed the obstacles are cylindrical circular objects with the same size.

• 한국항공우주학회지
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• 제35권7호
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• pp.647-654
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• 2007

본 논문에서는 일정한 추력을 이용한 지구-달의 연료 최적 궤적해를 이용하여, 가변 추력기를 이용한 지구 탈출 궤적에서의 에너지 및 연료 최적 궤적을 설계하였다. 에너지 최적의 지구 탈출 궤적은 여러 차례 지구를 공전하게 되고, 궤도 천이 시간이 일반적인 궤도 천이 시간 보다 상대적으로 오래 소요되므로 최적화 문제를 해를 구하기가 쉽지 않다. 따라서 에너지 최적 해를 구하기 위하여, 초기 상태변수를 조정하면서 Discrete continuation의 기법을 적용하였다. 최적화 문제의 종말 조건은 일정한 추력기를 이용한 지구 탈출 궤적의 종말 조건을 이용하였고, 구속 시간은 일정한 추력기를 이용한 궤도 천이의 경우보다 큰 값으로 설정하였다. 한편, 연료 최적 궤적은 제어 입력의 형태가 불연속적이기 때문에 해를 구하기가 쉽지 않다. 따라서 연료 최적 궤적은 에너지 최적의 해와 호모토피(Homotopy) 기법을 적용시켜 그 해를 구하였다.

• Journal of Computing Science and Engineering
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• 제5권3호
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• pp.210-222
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• 2011

In this work, we study the problem of privacy-preservation data publishing in moving objects databases. In particular, the trajectory of a mobile user in a plane is no longer a polyline in a two-dimensional space, instead it is a two-dimensional surface of fixed width $2A_{min}$, where $A_{min}$ defines the semi-diameter of the minimum spatial circular extent that must replace the real location of the mobile user on the XY-plane, in the anonymized (kNN) request. The desired anonymity is not achieved and the entire system becomes vulnerable to attackers, since a malicious attacker can observe that during the time, many of the neighbors' ids change, except for a small number of users. Thus, we reinforce the privacy model by clustering the mobile users according to their motion patterns in (u, ${\theta}$) plane, where u and ${\theta}$ define the velocity measure and the motion direction (angle) respectively. In this case, the anonymized (kNN) request looks up neighbors, who belong to the same cluster with the mobile requester in (u, ${\theta}$) space: Thus, we know that the trajectory of the k-anonymous mobile user is within this surface, but we do not know exactly where. We transform the surface's boundary poly-lines to dual points and we focus on the information distortion introduced by this space translation. We develop a set of efficient spatiotemporal access methods and we experimentally measure the impact of information distortion by comparing the performance results of the same spatiotemporal range queries executed on the original database and on the anonymized one.

• 한국강구조학회 논문집
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• 제12권6호
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• pp.715-725
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• 2000

본 논문은 링크구성 설계를 통하여 결정된 하나의 이중링크 형식 수평인입 집 크레인에 대하여 작업위치에 따라 각 링크의 변위, 속도, 가속도 해석을 하고, 인입 가감속에 의한 관성력, 바람에 의한 풍하중, 크레인 자중 및 정격 권상하중 등이 크레인에 작용할 때 인입장치에 요구되는 정적 힘을 계산하였다. 모든 해석과정은 전산 프로그램으로 작성되었고, 프로그램의 신뢰성은 관련 범용 소프트웨어들의 해석 결과와 비교하여 검증하였다. 따라서, 본 논문에서 개발한 전산 프로그램은 이중링크 형식 수평인입 집 크레인의 설계 실무에 있어서 이동하중에 대한 인입궤적의 진폭 및 작업위치에 따라 인입장치에 요구되는 힘의 해석을 신속, 정확하게 처리할 수 있어 설계의 생산성 및 신뢰성 제고뿐만 아니라 기본설계 기술력의 확보 측면에서 그 의의가 있다.

• 대한공간정보학회지
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• 제25권2호
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• pp.21-29
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• 2017

최근 활발히 연구가 진행 중인 자율주행차량이나 첨단운전자보조시스템의 효율적이고 안정적인 동작을 위해서 차량 위치를 정확하게 결정하는 것이 중요하다. 주로 사용되는 위성 기반 항법은 신호 수신이 어려운 영역에서 위치 정확도가 매우 떨어지는 한계가 있다. 이를 극복하기 위해 INS 등 추가센서를 이용하는 방안이 모색되고 있지만 높은 비용이 문제가 된다. 이에 본 연구는 고가의 센서를 추가하지 않고 차량에 이미 내장된 센서와 저가의 영상센서를 통합하여 차량의 위치를 정확하게 추정하는 알고리즘을 개발하였다. 차량 내장 센서로부터 제공되는 속력, 각속도와 단영상후방교차법로 결정된 카메라의 위치, 자세를 함께 활용하여 차량의 위치를 추정하였다. 알고리즘의 성능평가를 위해 시범 시스템을 구축하였고, 시험 데이터를 취득하여 주행경로를 추정하였다. 차량 내장 센서만을 이용하였을 경우에 비해 단영상후방교차법 결과를 함께 이용하였을 경우 약 40% 높은 정확도로 차량 경로추정이 가능하였다.

• 한국항공우주학회지
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• 제30권7호
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• pp.51-60
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• 2002

통계학적 해석인 몬테-칼로 모의실험은 대기권 재진입 분산의 결과인 낙하예정지역뿐만 아니라 상태변수들의 최종조건들을 조사하는데도 사용된다. 본 논문에서 재진입 분산은 위도, 경도, 고도, 뱅크각, 비행경로각, 기수 오차, 그리고 항속거리로 생성되는 $7\times7$ 공분산 행렬로 한정된다. 감속을 목표로 하는 대기권 재진입시 이것들에 영향을 미치는 오차 원인들은 대기밀도, 온도, 초기오차, 바람, 그리고 항력계수의 추정오차 등에 관련된 불확실성들로서 이들 오차의 $3{\sigma}_n$와 공칭 비행궤적을 사용해서 상태변수의 공분산 행렬은 궤적 오차 해석을 수행함으로 결정될 수 있다. 재진입에 대한 몬테-칼로법의 적용에 있어서 주요 고려할 점은 교란궤적, 뱅크역전, 그리고 이 제적들 각각에 대한 최종 낙하지점의 결정이다. 본 논문은 불확실성에 대한 결과를 공력계수와 뱅크역전의 관점에서 해석한다.

• Bulletin of the Korean Chemical Society
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• 제31권10호
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• pp.2841-2848
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• 2010

Quasiclassical trajectory (QCT) method has been used to investigate stereodynamics information of the reaction $O(^1D)+H_2{\rightarrow}\;OH$+H on the DK (Dobbyn and Knowles) potential energy surface (PES) at a collision energy of 23.06 kcal/mol, with the initial quantum state of reactant $H_2$ being set for v = 0 (vibration quantum number) and j = 0-5 (rotation quantum number). The PDDCSs (polarization dependent differential cross sections) and the distributions of P($\theta_r$), P($\phi_r$), P($\theta_r$, $\phi_r$) have been presented in this work. The results demonstrate that the products are both forward and backward scattered. As j increases, the backward scattering becomes weaker while the forward scattering becomes slightly stronger. The distribution of P($\theta_r$) indicates that the product rotational angular momentum j' tends to align along the direction perpendicular to the reagent relative velocity vector k, but this kind of product alignment is found to be rather insensitive to j. Furthermore, the distribution of P($\phi_r$) indicates that the rotational angular momentum vector of the OH product is preferentially oriented along the positive direction of y-axis, and such product orientation becomes stronger with increasing j.

• Journal of Astronomy and Space Sciences
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• 제33권4호
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• pp.323-333
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• 2016

In this study, the uncertainty requirements for orbit, attitude, and burn performance were estimated and analyzed for the execution of the $1^{st}$ lunar orbit insertion (LOI) maneuver of the Korea Pathfinder Lunar Orbiter (KPLO) mission. During the early design phase of the system, associate analysis is an essential design factor as the $1^{st}$ LOI maneuver is the largest burn that utilizes the onboard propulsion system; the success of the lunar capture is directly affected by the performance achieved. For the analysis, the spacecraft is assumed to have already approached the periselene with a hyperbolic arrival trajectory around the moon. In addition, diverse arrival conditions and mission constraints were considered, such as varying periselene approach velocity, altitude, and orbital period of the capture orbit after execution of the $1^{st}$ LOI maneuver. The current analysis assumed an impulsive LOI maneuver, and two-body equations of motion were adapted to simplify the problem for a preliminary analysis. Monte Carlo simulations were performed for the statistical analysis to analyze diverse uncertainties that might arise at the moment when the maneuver is executed. As a result, three major requirements were analyzed and estimated for the early design phase. First, the minimum requirements were estimated for the burn performance to be captured around the moon. Second, the requirements for orbit, attitude, and maneuver burn performances were simultaneously estimated and analyzed to maintain the $1^{st}$ elliptical orbit achieved around the moon within the specified orbital period. Finally, the dispersion requirements on the B-plane aiming at target points to meet the target insertion goal were analyzed and can be utilized as reference target guidelines for a mid-course correction (MCC) maneuver during the transfer. More detailed system requirements for the KPLO mission, particularly for the spacecraft bus itself and for the flight dynamics subsystem at the ground control center, are expected to be prepared and established based on the current results, including a contingency trajectory design plan.