• 대한의용생체공학회:학술대회논문집
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• 대한의용생체공학회 1996년도 춘계학술대회
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• pp.266-270
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• 1996

External linkage type spine motion analyzer was developed for measuring relative trunk motion respect to the pelvis. A special program for calculation of the relative angular motion and graphical display were also developed. The developed device assured its accuracy and conveniency after application to 15 normal volunteers and 18 patients after fixation and decompression surgery. Compare to the normal subjects, patients shows different angular motion especially in the angular acceleration.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 2005년도 춘계학술대회 논문집
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• pp.1579-1582
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• 2005

Polishing is cutting process that polished workpiece by relative motion of abrasive grain between polishing tool and workpiece. According to relative motion forms(polishing patterns) of abrasive grain, the surface quality is different. Then, polishing patterns are important essential in polishing process. In work field, polishing patterns are determined by an expert of experience. Therefore, to work effective polishing, it is necessary that evaluate polishing characteristics for polishing patterns. And, polishing machine is made with cartesian coordinate robots, we estimate polishing characteristics by measurement of surface roughness.

• 한국항해학회지
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• 제13권2호
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• pp.37-55
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• 1989

When a ship is sailing on the sea, she has the six-degrees of freedom of motion. It means that she meets a lot of dangerous situations. Especially, when the VLCC is travelling in irregular sea, the slamming, the deck-wetness and the propeller racing are occured with the sea state she is on. These are the representative steps that a heave-to and a scudding are used for a ship building , but for a predominance in both. The author intends to clarify this problem theoretically. The methods of statistical calculation are based with the ITTC spectral formulation and with the assumption that the wave height histogram follows the Rayleigh distribution. In this study, the author gives an attention on the relative bow motion to a wave in the irregular sea. It is verified that the relative diplacement at the bow to sea level in the following sea is less than that in the head sea. It is confirmed that, therefore, one have to sail with scudding when he is threatened to heave-to at a rough sea. But he must bear the propeller racing in mind in the cases.

• 국제초고층학회논문집
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• 제10권2호
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• pp.99-107
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• 2021

This research investigates the potential of Adaptive TMDs for tall building damping. The Adaptive TMD under consideration is based on real-time controlled hydraulic dampers generating purely dissipative control forces. The control approach is designed to enhance the Adaptive TMD efficiency for moderate wind loads with return periods below 50 years. The resulting enhanced TMD efficiency is used to reduce the pendulum mass by 15% compared to the passive TMD while still guaranteeing the acceleration limits of the one and ten year return period winds. Furthermore, the adaptive control approach is designed to disproportionally increase the controlled damping force at wind loads with return periods of 50 years and more in order to reduce the maximum relative motion of the Adaptive TMD with only 85% pendulum mass. Compared to the passive TMD with 100% pendulum mass the maximum relative motion is reduced by 20%. Both the pendulum mass reduction and the maximum relative motion reduction significantly reduce the foot print of the Adaptive TMD which is highly desirable from the economic point of view.

• 한국정밀공학회지
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• 제17권2호
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• pp.185-192
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• 2000

Cam mechanism is one of the common devices used in many automatic machinery. Since the motion of the cam mechanism depends on the shape of the cam and the type of the follower, the shape design procedure must be well defined in order to determine the accurate shape of the cam corresponding to the prescribed motion of the follower. This paper proposes a new approach for designing the shape of disk cams. The proposed relative velocity method uses the relative velocity at center of the follower roller or at contact point between the cam and the follower for 4 different types of the disk cam systems. Also, the relative velocity method for determining the cam profile uses the geometric relationships of the cam and the follower.

• 한국철도학회논문집
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• 제9권3호
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• pp.277-281
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• 2006

The center pivot in the power car of KTX carries the traction force of the motor bogie to the carbody. The damage to the center pivot due to failure of swivel joint causes a serious hazard of the train. To prevent the hazard, information on the relative motion between bogie and carbody is necessary. In this paper, a method to measure the relative rotation of the center pivot is proposed and an actual test to verify the method and safety is conducted. The test results show that the rotation of the center pivot is within the allowable limit and the damage due to the relative motion doesn't take place.

• Journal of Mechanical Science and Technology
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• 제20권2호
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• pp.177-184
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• 2006

An orbital design method of the formation initialization based on the relative orbital element method is presented. It firstly constructed the relative motion equation of the satellite formation flying in terms of the leader and followers' orbital elements. Then the equation was simplified when the orbit eccentricity of the leader satellite was small. And according to the satellites' mission, a general design method for the relative trajectory was proposed. The advantage of this method is that one can get a very simple analytical formula of each follower satellite's orbital elements when the orbital eccentricity of the leader satellite is zero. The simulation results show that the method is effective.

• Journal of Astronomy and Space Sciences
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• 제26권3호
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• pp.317-328
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• 2009

위성의 상대운동 모델은 두 위성 사이의 상대적인 운동을 기술하며, 위성편대비행 연구의 기본이 된다. 이 연구에서는 선형 및 비선형 상대운동 모델들의 정확도를 산출하고 이를 비교 분석하였다. 우선 모델의 정확도를 나타내는 '모델링 오차 지수(Modeling Error Index)'를 정의하였다. 다양한 주위성 궤도의 이심률과 두 위성 사이의 거리에 대해 모델링 오차 지수를 계산하여, 여러 궤도환경에 따른 기존의 여러 가지 상대운동 모델들의 정확도를 산출하였다. 여러 가지 상대운동 방정식들의 모델링 오차 지수는 주위성의 이심률의 크기, J2 섭동 고려 여부, 위성들의 상대 거리의 크기에 따라 달라진다. 이 연구에서 사용한 상대운동 모델의 정확도는 편대비행 동역학모델의 오차를 나타내므로, 이 연구 결과를 이용해서 주어진 편대비행 임무에 알맞은 모델을 선택하는 것이 가능하다.

• 한국공작기계학회논문집
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• 제12권2호
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• pp.71-78
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• 2003

This research proposes an implementation method of linearized equations of motion for multibody systems with closed loops. The null space of the constraint Jacobian is first pre-multiplied to the equations of motion to eliminate the Lagrange multiplier and the equations of motion are reduced down to a minimum set of ordinary differential equations. The resulting differential equations are functions of all relative coordinates, velocities, and accelerations. Since the variables are tightly coupled by the position, velocity, and acceleration level coordinates, direct substitution of the relationships among these variables yields very complicated equations to be implemented. As a consequence, the reduced equations of motion are perturbed with respect to the variations of all variables, which are coupled by the constraints. The position velocity and acceleration level constraints are also perturbed to obtain the relationships between the variations of all relative coordinates, velocities, and accelerations and variations of the independent ones. The Perturbed constraint equations are then simultaneously solved for variations of all variables only in terms of the variations of the independent variables. Finally, the relationships between the variations of all variables and these of the independent ones are substituted into the variational equations of motion to obtain the linearized equations of motion only in terms of the independent variables variations.

• International Journal of Aeronautical and Space Sciences
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• 제4권2호
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• pp.1-8
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• 2003

Satellite formation flying is the placing micro-satellites with the same mission into nearby orbits to form a cluster. Clohessy-Wiltshire equations are used to describe the relative motion and control strategies between satellites within a cluster, which are known as Hill's equations. Even though Hill's equations are powerful in determining initial conditions for the satellite formation flying, they can not accurately express the relative motion under J2 perturbation. Some methods have been developed for the determination of initial conditions to avoid limits of Hill's equation. This paper gives a new method of determining initial conditions using mean elements. For this research mean elements were transformed to osculating elements using Brouwer's theory and the orbit was propaeated with the consideration of J2-J8 to get a relative position. The results show that satellites within a cluster are maintained in the desired boundary for long period and the method is effective on a fuel saving for satellite formation flying.