• 한국생산제조학회지
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• 제20권6호
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• pp.778-784
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• 2011

This paper presents the study on orientations interpolation of 6-axis articulated robot using quaternion. In this paper, we propose a control algorithm between given two orientations of 6-axis articulated robot by using a quaternion with spherical linear interpolation. In order to study the quaternion interpolation, We created Inverse kinematics program and Interpolation program using LabVIE$^{(R)}$. The rotation angle of each axis were calculated using both euler orientations interpolation program and quaternion orientations interpolation program. The proposed control algorithm is shown to be effective in terms of motor angles and torques when compared to a conventional Euler angle interpolation, by using both LabVIEW$^{(R)}$ and RecurDyn$^{(R)}$.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 1999년도 추계 학술대회논문집
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• pp.167-173
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• 1999

An Euler-based CFD tool has been developed for the performance evaluation of a thrust reverser mounted on a high bypass ratio turbofan engine. The computational domain surrounded by the ground and non-reflection boundary includes the whole nacelle configuration with a deployed thrust reverser. The numerical algorithm is based on the modified Godunovs scheme to allow the second order accuracy in both space and time. The grid system is generated by using eleven multi-blocks, of which the total cell number is 148,400. The thrust reverser is modeled as if it locates at the nacelle simply in all circumferential direction. The existence of a fan and an OGV(Outlet Guide Vane) is simulated by adopting the actuator disk concept, in which predetermined radial distributions of stagnation pressure ratio and adiabatic efficiency coefficient are used for the rotor type disk, and stagnation pressure losses and flow outlet angles for the stator type disk. All boundary conditions including the fan and OGV simulation are treated by Riemann solver. The developed solver is applied to a turbofan engine with a bypass ratio of about 5.7 and the diameter of the fan cowl of 83 inch. The computational results show that the Euler-based inviscid method is very useful and economical to evaluate the performance of thrust reversers.

• 로봇학회논문지
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• 제14권1호
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• pp.65-73
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• 2019

In this paper, we propose an algorithm that estimates the location of lunar rover using IMU and vision system instead of the dead-reckoning method using IMU and encoder, which is difficult to estimate the exact distance due to the accumulated error and slip. First, in the lunar environment, magnetic fields are not uniform, unlike the Earth, so only acceleration and gyro sensor data were used for the localization. These data were applied to extended kalman filter to estimate Roll, Pitch, Yaw Euler angles of the exploration rover. Also, the lunar module has special color which can not be seen in the lunar environment. Therefore, the lunar module were correctly recognized by applying the HSV color filter to the stereo image taken by lunar rover. Then, the distance between the exploration rover and the lunar module was estimated through SIFT feature point matching algorithm and geometry. Finally, the estimated Euler angles and distances were used to estimate the current position of the rover from the lunar module. The performance of the proposed algorithm was been compared to the conventional algorithm to show the superiority of the proposed algorithm.

• 한국전자파학회논문지
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• 제26권8호
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• pp.758-764
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• 2015

본 논문에서는 2차 함수 곡선의 회전체형 도체 곡면 위에 있는 컨포멀 배열 안테나의 패턴을 EAGA(Enhanced Adaptive Genetic Algorithm)를 이용하여 합성한 내용을 보이고 있다. 다양한 곡면의 회전체 도체를 고찰하기 위해 2차 함수의 계수를 바꿔 세 가지 유형의 회전체형 곡면을 형성시켰고, 각 유형의 컨포멀 배열 안테나 패턴을 합성하였다. 패턴 합성에 소요되는 시간의 단축을 위해 3차원 컨포멀 배열 안테나의 능동 소자 패턴 대신에 2차원 평면 배열 안테나의 능동 소자 패턴을 구한 후, 이를 오일러 변환(Euler transform)시켜 이용하였다. EAGA를 이용하여 합성된 패턴의 검증을 위해 MWS(Microwave Studio)를 통해 구한 패턴과 비교하였으며, 두 패턴은 전반적으로 유사하였다.

• 제어로봇시스템학회논문지
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• 제7권1호
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• pp.1231-1239
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• 2001

This paper presents a new leveling algorithm that estimates the initial horizontal angles composed of roll angle and pitch angle for a moving or stationary vehicle. The system model of the EKF is designed by linearizing the nonlinear Euler angle differential equation. The measurement models are designed for the moving case and for the stationary case, respectively. The simulation results show that the leveling algorithm is ade-quate not only for acquiring the initial horizontal angles of the vehicle in the motion with acceleration and rotation but also for the stationary one.

• International Journal of Aeronautical and Space Sciences
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• 제18권2호
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• pp.300-314
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• 2017

This paper examines finite rotation angle (FRA) applications for spacecraft attitude control. The coordinate transformation matrix and the attitude kinematics represented by FRAs are introduced. The interpolation techniques for the angular orientations are thoroughly investigated using the FRAs and the results are compared to those using traditional methods. The paper proposes trajectory description techniques by using extremely smooth polynomial functions of time, which can describe point-to-point attitude maneuvers in a realizable and accurate manner with the help of unique FRA features. In addition, new controller design techniques using the FRAs are developed by combining the proposed interpolation techniques with a model predictive control framework. The proposed techniques are validated through their attitude control applications for an aggressive point-to-point maneuver. Conclusively, the FRAs provide much more flexibility than quaternions and Euler angles when describing kinematics, generating trajectories, and designing attitude controllers for spacecraft.

• 한국전산구조공학회논문집
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• 제23권2호
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• pp.183-189
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• 2010

본 논문에서는 자동차의 구동계 등에 사용되는 유니버설 조인트의 기구학적 거동을 관찰하기 위하여 오일러 각과 4원수(quaternion)를 적용한 두 가지 방법을 비교하였다. 이와 관련된 종래의 연구자들은 오일러 각을 사용하여 회전체의 동적인 거동을 해석하였으나 결과의 일관성과 정확도가 부족하였다. 유니버설 조인트 시스템 해석에서도 이러한 단점을 확인하였고 이를 극복하고자 4원수를 적용하였다. 구동시 원동축 1개축 회전과 원동축과 직각방향 회전축 2개의 축이 동시에 존재하는 경우에 대하여 수치해석을 통하여 기하학적인 물리량을 산출하였다. 4원수를 채용한 방법이 세차운동을 포함하는 2개축 회전에서 유니버설 조인트 시스템을 해석하는데 있어 더욱 유용한 방법임을 보여 주었다.

• ETRI Journal
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• 제16권2호
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• pp.27-41
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• 1994

A new mathematical model to predict the beam pointing instability of a nonconservative two-body satellite system in spinning injection mode has been developed by using Newton-Euler and projection methods. Since the on-axis and null axis of the omni antenna with toroidal pattern beam form a right angle, wobbling of the antenna on-axis is measured by determining the Euler angles which represent the orientation of the satellite's spin axis. Because of the complexity of the system which is a time varying, nonstationary, nonlinear dynamical system, a numerical method is used for the analysis. Computer simulation results present the effects of the mass distribution and internal mass motion on the antenna beam pointing.

• 한국멀티미디어학회:학술대회논문집
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• 한국멀티미디어학회 2002년도 춘계학술발표논문집(상)
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• pp.474-478
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• 2002

본 논문에서는 광학식 모션 캡쳐를 이용하여 얻은 한국인의 발레 동작에 대한 모션 캡쳐 데이터를 사용하여 다른 모션으로 변형함으로써 새로운 형태의 동작을 생성하거나 원래 데이터의 에러가 생긴 경우에 보정이 쉽게 수정 가능하도록 하였다. 즉, 모션 캡쳐 데이터의 구조는 다양한 포맷들로 되어 있는 스켈레톤 구조로서 관절의 각도나 위치에 대해 변형을 가하기 힘들다. 그러므로 모션 수정에 관련된 기술을 이용하여 선택된 조인트(joint), 엔드이펙터(end effecter), 마커(marker)들을 보여주고, 오일러(Euler Angles), 쿼터니언(Quaternions), 지수 맵(Exponential Map) 보간이 가능하여 실시간에서도 재생 되도록 구현하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2000년도 추계 학술대회논문집
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• pp.32-38
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• 2000

Wing flap deflection angles of a supersonic transport are optimized to improve transonic cruise performance. For this end, a numerical optimization method is adopted using a three-dimensional unstructured Euler code and a discrete adjoint code. Deflection angles of ten flaps; five for leading edge and five fur railing edge, are employed as design variables. The elliptic equation method is adopted for the interior grid modification during the design process. Interior grid sensitivities are neglected for efficiency. Also tested is the validity of the approximate gradient evaluation method for the present design problem and found that it is applicable for loading edge flap design in cases of no shock waves on the wing surface. The BFGS method is used to minimize the drag with constraints on the lift and upper surface Mach numbers. Two design examples are conducted; one is leading edge flap design, and the other is simultaneous design of leading edge and trailing edge flaps. The latter gave a smaller drag than the former by about two counts.