• Journal of rehabilitation welfare engineering & assistive technology
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• v.7 no.2
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• pp.91-99
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• 2013

The purpose of this study was to investigate the muscular activity and muscle strength for swing track of upper limbs during rowing exercise. Subject was all twenty healthy adults and they were divided into linear exercise group and elliptical exercise group in random. Subjects performed rowing exercise 3-times for a week and performed all 8-weeks. We measured realtime-surface EMG. Also we measured joint torque of elbow, ankle and lumbar in subjects using BIODEX. The result showed that when rowing exercise, elliptical track exercise had higher muscular activity in trapezius, deltoid, erector spinae, rectus femoris, biceps femoris, gastronemius than linear track exercise on more many muscle of upper and lower limbs. Also elbow joint torque and lumbar joint torque was more higher too. but linear exercise also had higher muscular activity in multifidus, tibilalis anterior than elliptical track exercise. According to this experiment, we found out that elliptical track was more efficient than linear track.

• Bulletin of the Korean Space Science Society
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• 2010.04a
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• pp.29.2-29.2
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• 2010

항법분야에 있어서 위성항법시스템의 다양한 오차를 제거한 정밀한 위치 정보를 이용하여 이동체에 활용하는 연구가 진행되고 있다. 실제 환경에서 이동체를 이용한 항법실험을 수행하기 전 실제 환경과 유사한 가상의 실시간 테스트베드를 구축하여 알고리즘 테스트 및 검증 실험을 수행하려 한다. 이를 위해 이동체의 운동을 시뮬레이션하는 운동궤적제어시스템과 실제의 항법신호를 시뮬레이션하는 GNSS 시뮬레이터 사이의 시각동기화는 실시간 시뮬레이션을 구현하기 위해 필수적으로 요구된다. 동기화 되지 않은 시각정보는 이동체 운동궤적제어시스템에 의해 생성된 실제의 궤적과 GNSS 시물레이터로부터 생성된 궤적사이의 오차를 유발하여 항법수신기의 부정확한 항법신호를 유발한다. 이 연구는 GNSS 시뮬레이터를 이용한 실시간 테스트베드의 구축에 있어 필요한 이동체 운동궤적의 시각동기화 기술 개발을 목표로 한다. GNSS 시뮬레이터는 Spirent 사의 GPS 시뮬레이터가 사용되었다. 이동체의 위치, 속도, 가속도와 같은 움직임을 나타내는 운동에 관한 명령은 적용되어야 하는 정확한 시각이 함께 전송되므로, 이는 그 시각 이전에 GPS 시뮬레이터에 도달해야 한다. 따라서 1초(1 Hz) 또는 0.1초(10 Hz) 사이에 원격제어시스템과 GPS 시뮬레이터사이의 시각 동기화를 구현하였다. 시뮬레이터와의 시각정보 동기화를 위해 Amplicon사의 PCI-215 타이머카드를 이용하였고, 그 결과, 이동체 운동궤적제어시스템과 시뮬레이터의 시각정보를 $10^{-3}$ 내의 위치오차를 가지는 정밀도로 동기화됨을 확인할 수 있었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.3
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• pp.6-13
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• 2006

Aerodynamic characteristics for two-dimensional cyclic motion profile of flapping airfoil in low Reynolds number flows are investigated. Plunging motion and lead-lag motion in the two dimensional space with different plunging and lead-lag amplitudes are combined to cyclic motion profile and the flow around the airfoil is simulated. Present result shows that the improved aerodynamic efficiencies for a given flapping airfoil by adding periodic lead-lag motion of airfoil rather than the pure plunging case. The thrust coefficient and lift coefficient are compared with each cycle during the flapping period and aerodynamic characteristics are obtained on upstroke motion and downstroke motion.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.5
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• pp.46-55
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• 2006

In general, 3-dimensional point-mass equation has been widely used for the trajectory optimization of the fixed-wing aircraft and reentry vehicle. But it should be modified and represent target vehicle's own characteristics. For a lighter-than-air vehicle such as an airship, there exists different and peculiar flight characteristics compared with the aircraft. The first part of this paper is to derive the dynamic equation of motion for the mid-altitude unmanned airship and the second part is to obtain the optimal trajectories under the minimal time flight given constraints. The trajectory optimization problem is converted into the nonlinear programming problem using Sequential Quadratic Programming approach. Finally numerical solutions are presented in the last part of the paper.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.9
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• pp.875-881
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• 2010

During the lunar mission, spacecraft are subject to various unexpected disturbance sources such as third body attraction, solar pressure and operating impulsive maneuver error. Therefore, efficient trajectory correction maneuver (TCM) strategy must be required to follow the designed mission trajectory. In the early days of space exploration, the mission trajectory has been designed by using patched conic approach based on two-body dynamics for the lunar mission. Thus the TCM based on two-body dynamics has been usually adopted. However, with the advanced in computing power, the mission trajectory based on three-body dynamics is attempted recently. Thus, these approaches based on two-body dynamics are essentially different from real environment and large amount of energy for the TCM is required. In this work, we study the trajectory correction maneuver based on three-body dynamics.

• 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.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.3
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• pp.213-220
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• 2014

A program that predicts trajectories of projectiles influenced by the interference flow field of helicopters is developed. The interference flow field are computed using a compressible inviscid solver in conjunction with an actuator disc model. The trajectories are predicted using 6-DOF (Degree of Freedom) equations as well as an alternative form of modified point mass equations of motion. The method for the interference flow field prediction method are validated with ROBIN(ROtor Body INteraction) model. A Sierra international bullet and a 105mm projectile are used to validate the trajectory method. Trajectories of a Sierra International bullet and a HYDRA 70 rocket firing from a helicopter are predicted.

• Journal of Korean Society of Coastal and Ocean Engineers
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• v.4 no.4
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• pp.187-200
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• 1992

A general scheme is developed to determine the Langrangian motions of water particles by the Eulerian velocity at their mean positions by using Taylor's theorem. Utilizing the Stokes finite-amplitude wave theory, the orbital motions and the mass transport velocity including the effects of higher-order wave components are determined. The fifth-order approximation of orbital motion gives very good predictions of actual water particle motion in Stokes fifth-order wave theory except near the free-surface. The fifth-order theory predicts the mass transport velocity less than that given by the existing second-order theory over the whole water depth.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.21 no.10
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• pp.1879-1885
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• 2017

This paper discusses the trajectory tracking system of unmanned ground vehicles based on predictive control. Because the unmanned ground vehicles can not satisfactorily complete the path tracking task, highly efficient and stable trajectory control system is necessary for unmanned ground vehicle to be realized intelligent and practical. According to the characteristics of unmanned vehicle, this paper built the kinematics tracking models firstly. Then studied algorithm solution with the tools of the optimal stability analysis method and proposed a tracking control method based on the model predictive control. The controller used a kinematics-based prediction model to calculate the predictive error. This controller helps the unmanned vehicle drive along the target trajectory quickly and accurately. The designed control strategy has the true robustness, simplicity as well as generality for kinematics model of the unmanned vehicle. Furthermore, the computer Simulink/Carsim results verified the validity of the proposed control method.

• Proceedings of the Korean Society for Agricultural Machinery Conference
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• 2017.04a
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• pp.66-66
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• 2017

국내 농촌의 인구고령화, 여성화 증가로 인한 농촌노동력 감소 문제를 해결하기 위해 농업기계자동화에 관한 연구가 활발히 진행되고 있다. 본 연구는 자동화농업기계 중 자동 이식기의 성능평가 기술을 개발하기 위해 수행되었으며 이를 위해 자동 정식기의 핵심부품인 이식호퍼의 결주율, 이식율, 주간간격, 운동궤적 등을 측정할 수 있는 원형토조 실험장치를 개발하였다. 원형토조 실험장치는 원형토조, 이식호퍼 구동장치, 컨트롤러로 구성되어 있으며 이식호퍼의 회전속도(rpm)를 조절하여 주간간격을 조절할 수 있고 초고속 카메라를 이용하여 이식호퍼의 운동궤적을 측정할 수 있다. 이식작물로 고추, 양배추, 브로콜리의 3종류의 육묘를 이용하여 이식호퍼의 회전속도를 20~60 rpm 구간에서 10 rpm 단위로 속도조건변화를 주고 결주율과 이식율을 측정하였다. 이식호퍼 rpm 속도에 따른 주간거리는 190~560 mm로 나타났다. 각 rpm 단수, 작물별 평균 이식율은 고추육묘가 약 97%, 양배추육묘가 약 94%, 브로콜리육묘가 약 95%로 나타났다. 또한 초고속 카메라를 이용하여 측정한 이식호퍼의 운동궤적을 통해 선진사 제품과 대비하여 차이를 보인 것을 확인하였다. 향후 원형토조 실험장치를 이용해 다양한 작물 및 토양조건에서의 실험 및 토양저항 측정장치 개발을 통해 이식작업 진행중에 호퍼에 걸리는 부하에 대한 성능평가시험을 할 계획이다.