• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.2
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• pp.101-107
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• 2012

In this study, Constraint Force Equation Methodology (CFEM) is used to develop a multi-body dynamic analysis program with constraints. Seven constraint models are implemented to analyze constraint motions of multiple bodies. The augmented equations with the constraints are solved with the 4th order Runge-Kutta method for higher degree of accuracy. The analysis code is verified by comparing the analysis results of the motion of bodies with various constraints to published results.

• Proceedings of the KIEE Conference
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• 2003.11b
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• pp.7-10
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• 2003

뱀형 로봇은 자유도보다 액추에이터의 수가 적은 논홀로믹 구속조건(nonholonomic constraint)을 가지며, 단순한 신체구조 이지만 초-여유자유도 구속조건(hyper-redundant constraint)을 이용해서 기밀한 운동과 다양한 기능을 만들어내는 특징을 가지고 있다. 본 논문에서는 6개의 관절로 각 링크가 2차원 상에서 직렬로 연결된 뱀형 로봇의 기구설계 및 기구학과 동력학을 바탕으로 설계된 기구에 대해 해석하여 운동방정식을 유도하여 추진원리와 운동원리에 관하여 알아본다. 기본적인 운동 메커니즘을 해석하여 구현한 알고리즘을 제작한 로봇에 적용하여 추진 원리와 운동원리를 검증한다. 실험용 로봇은 링크 중앙에 법선 방향으로 마찰력이 발생할 수 있도록 수동바퀴를 가지고 있으며, PC와 RF(Radio Frequency)로 직렬통신을 하며 PC에서의 운동 명령의 조작에 의해 전진, 후진, 좌/우 방향으로 회전을 할 수 있도록 운동 알고리즘을 적용할 수 있도록 제작되었다. 특징으로는 일반적으로 토크를 입력으로 하지 않고 각도를 입력으로 하여 관절을 제어하고 있다는 점이 있으며, 운동방정식 또한 이에 대한 관계를 바탕으로 유도한 것이다.

• Journal of the Korea Computer Graphics Society
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• v.3 no.1
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• pp.1-7
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• 1997

Technology for the realistic model and the motion control of human is applied to many areas of computer graphics, virtual reality and computer simulations. Human body is a multi-articular body. Generally, to create a human model and motions. articulated body models are generated and their motions are controlled based upon kinematics. The hand of the human consists of many small articulations and each articulations have a various degree of freedom. This paper presents a model of human hand which is based on the two kinds of constraints to control the motions of the hand realistically. To build a hand model, we experimented the anatomy of the human hand, and the diverse motions of the hand are tested.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.1
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• pp.21-30
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• 2021

Mid-course trajectory of the missiles equipped with seeker should be designed to detect target within FOV of seeker and to maximize the maneuverability at the point of transition to terminal guidance phase. Because the trajectory optimization problems are generally hard to obtain the analytic solutions due to its own nonlinearity with several constraints, the various numerical methods have been presented so far. In this paper, mid-course trajectory optimization problem for boost-glide missiles is calculated by using SOCP (Second-Order Cone Programming) which is one of convex optimization methods. At first, control variable augmentation scheme with a control constraint is suggested to reduce state variables of missile dynamics. And it is reformulated using a normalized time approach to cope with a free final time problem and boost time problem. Then, partial linearization and lossless convexification are used to convexify dynamic equation and control constraint, respectively. Finally, the results of the proposed method are compared with those of state-of-the-art nonlinear optimization method for verification.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.11
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• pp.881-888
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• 2020

In this paper, research on estimation of states of a target of interest using Line Of Sight(LOS) angle measurement is performed. Target's position, velocity, and acceleration are chosen to be the states of interests. The LOS measurement is known to be highly non-linear, making target dynamic modeling hard to be implemented into a filter. To solve this issue, the Pseudomeasurement equation was applied to the LOS measurement equation. With the help of this equation, 3D variable turn target dynamic model is applied to the filter model. For better performance, Kinematic Constraint is also implemented into the filter model. As for the filter, Bias Compensation Pseudomeasurement Filter (BCPMF) is used which is known for its robustness to initial conditions. Moreover, Two-Stage Kalman Filter (TSKF) form was also implemented to benefit from the parallel computation. As a result, TBCPMF 3DVT-KC is proposed and simulated to assess performance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.1
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• pp.42-54
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• 2009

Contrast to the 6-DOF nonlinear dynamic modeling of nonlinear tracking problem, 3-DOF point-mass modeling of flight mechanics is efficient and adequate for applying the trajectory optimization problem. There exist limitations to apply an optimal trajectory from point-mass modeling as a reference trajectory directly to conduct the nonlinear tracking control, In this paper, new matching trajectory optimization scheme is proposed to compensate those differences of mismatching. To verify performance of proposed method, full ascent three-dimensional flight trajectories are obtained by reflecting the real constraints of flight conditions and airship performance with and without jet stream condition. Then, they are compared with the optimal trajectories obtained from conventional method.

• The Journal of the Acoustical Society of Korea
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• v.10 no.6
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• pp.23-42
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• 1991

본 논문은 시스템 운동학적 자유보다도 많은 수의 input을 사용하여 비선형 구속조건을 갖는 메 카니즘의 정역학적 평형을 유지시키는 경우와 같이 일반 로봇 시스템의 협력 작업시 일어나는 antagonistic stiffness를 연구하였다. 이러한 antagonistic 상황은 coordinations of multiple manipulators, multi-fingered end-efector, walking machine, 그리고 인간의 움직임등을 포함하는 많은 로봇 시스템의 작동시에 일어난다. Antagonism으로 야기되는 stiffness는 이러한 시스템의 특성을 파악하는 좋은 척도 가 될 수 있다. Antagonistic stiffness의 개념은 시스템을 구성하는 강체들의 상대 변위의 함수로 얻어 지기 때문에 바강체들이 변형하는 특성을 나타내는 structural stiffness와는 구별된다. 따라서 이 개념은 여유입력들에 의해 얻어지는 시스템의 effective stiffness로 해석될 수 있고, 일반 로봇 mechanism의 개 경로 안정도의 척도로 이용될 수 있으며 목적에 따라서 stiffness의 제어가 가능한 비선형 spring을 만 드는 데에도 응용이 가능하다. 본 논문에서는 antagonism이 일어나는 몇가지 상황에서의 stiffness 특성 과 개경로 안정성 조건등을 해석적, 기하학적 관점에서 다루었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.5
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• pp.56-64
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• 2006

Station collocation of closely placed multiple GEO spacecraft is required to avoid the problem of collision risk, attitude sensor interference and/or occultation. This paper presents the method of obtaining the orbit correction scheme for collocating two GEO spacecraft within a small station-keeping box. The relative motion of each spacecraft with respect to the virtual geostationary satellite is precisely expressed in terms of power and trigonometry functions. This closed-form orbit propagator is used to define the constraint conditions which meet the requirements for the station collocation. Finally, the technique of constrained optimization is used to find the orbit maneuver sequence. Nonlinear simulations are performed and their results are compared with those of the classical method.

• Journal of Navigation and Port Research
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• v.34 no.3
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• pp.195-203
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• 2010

This paper concerns about total dynamic analysis of integrated mining system. This system consists of vertical steel pipe, intermediate buffer station, flexible pipe and self-propelled miner. The self-propelled miner and buffer are assumed as rigid-body of 6-dof. Discrete models of vertical steel pipe and flexible pipe are adopted, which are obtained by means of lumped-parameter method. The motion of mining vessel is not considered. Instead, the motion of mining vessel is taken into account in form of various boundary conditions (e.g. forced excitation in slow motion and/or fast oscillation and so on). A terramechanics model of extremely cohesive soft soil is applied to the self-propelled miner. Hinged and ball constraints are used to define the connections between sub-systems (vertical steel pipe, buffer, flexible pipe, self-propelled miner). Equations of motion of the coupled model are derived with respect to the each local coordinates system. Four Euler parameters are used to express the orientations of the sub-systems. To solve the equations of motion of the total dynamic model, an incremental-iterative formulation is employed. Newmark-${\beta}$ method is used for time-domain integration. The total dynamic responses of integrated mining system are investigated.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.9
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• pp.884-890
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• 2008

A new guidance law to reach circular target area with grazing angle constraint is proposed as one of midcourse guidance laws of unmanned air vehicles. The purpose of the law is to control the grazing angle between the velocity vector of the vehicle and the line of sight to the aiming point, the center of the circular target area, when the vehicle passes any point on the circle. The optimal solution is derived based on the optimal control theory minimizing a range weighted control energy subject to the nonlinear dynamic equations of the vehicle approaching to the circular target area with grazing angle constraint. The major properties including a convergence of the solution are examined and the performance of the law applied to some typical scenarios is shown by the numerical simulation.