• Proceedings of the Korean Institute of Intelligent Systems Conference
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• 2002.12a
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• pp.80-83
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• 2002

정밀한 서보기술에 바탕을 두고 있는 산업용 로봇 팔은 기계적인 강성도와 서보기구들로 인하여 정확한 제어가 가능하다 그러나 로봇팔은 동작중비 관성모멘트의 변화와 기하학적인 구조로 인하여 비선형적인 시스템이다. 특히 관성모멘트의 변화는 로봇팔의 회전속도와 로봇팔이 이동시키는 대상물의 무게 등에 따라 관성모멘트는 변할 수 있다. 이로 인하여 관성모멘트의 변화에 따라 로봇팔의 정확한 위치제어가 힘들어진다. 따라서 본 논문에서는 관성모멘트의 변화에도 불구하고 강인한 응답특성을 나타내는 제어기의 설계가 요구된다. 일반적으로 PID .제어기는 설계의 용이성으로 산업현장에서 널리 사용된다. 그러나 PIB 제어기의 각 계수값을 설정하는데 많은 어려움이 발생한다. 따라서 본 논문에서는 PID 제어기의 각 계수 값을 퍼지알고리즘을 이용하여 자동으로 설계할 수 있는 자기동조 PID 제어기를 설계한다.

• Journal of Korean Society of Steel Construction
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• v.14 no.6
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• pp.701-710
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• 2002

An analysis program using orthotropic plate elements was developed to simplify the analysis of plates stiffened with open ribs and the orthotropic behavior of stiffened plates and the application of this program were evaluated using the sensitivity analysis and the parametric study. The inertial moment ratio, i.e., the ratio of the inertial moment of the rib to that of the plate was defined and the orthotropic behavior of stiffened plates corresponding to the inertial moment ratio was proved by the sensitivity analysis. To evaluate the application of this program, the parametric study for various types of stiffened plates was performed and then the maximum displacement of this study was compared to that of ABAQUS using isoparametric plate elements. The Results of this study agreed well with that of ABAQUS at the particular inertial moment ratio, that is proposed to the limit ratio of the orthotropic plate analysis and the correlative function between the error ratio and the inertial moment ratio was obtained. Therefore, the orthotropic plate analysis of stiffened plates with open ribs could have safe results over the limit ratio and also have good results simply by using the correlative function of this study.

• Proceedings of the KIEE Conference
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• 2006.07b
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• pp.976-977
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• 2006

선형전동기와 같은 선형운동을 하는 기기에서 원형운동을 하는 경우 속도가 0 이되는 부분에서 비선형적인 마찰력이 작용하며 이로 인한 운동괘적의 외곡 현상이 발생한다. 본 연구에서는 이러한 마찰력을 비롯한 모든 외란을 하나의 비선형적인 외란으로 간주하여 실용적으로 사용할 수 있는 간단한 형태의 외란 관측기를 제시한다. 또한 모든 외란 관측기에서 피할수 없는 문제의 하나인 전동기 관성(모멘트)의 변동 문제를 해결하기 위하여 제한적이지만 매우 효과적으로 관성을 추정해낼 수 있는 새로운 방법을 제안한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.5
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• pp.385-392
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• 2018

This paper suggests a new method to estimate the roll and pitch damping moment coefficients of a flying disc through sensor data from the onboard IMU module. This method can be easily performed than wind tunnel or computational fluid dynamics methods because it estimates aerodynamic coefficients simply after accumulating the inertial data through several repeated flight experiments. Estimated coefficients are applied to a simulator which is based on the flight dynamics of a flying disc. Finally, the predicted flight trajectory is compared with the true position provided by GPS, which demonstrated the validity of the proposed estimation method.

• Proceedings of the KIEE Conference
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• 2011.07a
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• pp.35-36
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• 2011

본 논문은 불안정한 비선형시스템의 대표적인 플랜트인 도립진자를 이용하여, 비선형시스템의 선형화된 모델링에서 PID제어기와 상태궤환제어기의 제어역할을 연구한다. 우선 선형화시스템에서의 제어기를 구성한 후 회전형 도립진자를 모델링한다. 회전형 도립진자의 모델링은 실린더의 관성모멘트와 진자의 회전중심에 대한 모멘트의 관계를 토크를 기준으로 비선형 동적방정식 형태로 정리한다. 정리된 방정식을 선형화하여 컴퓨터 시뮬레이션을 통해 PID제어기와 상태궤환제어기의 제어특징과 성능을 비교 및 연구한다. 테스트용 회전형 도립진자를 이용하여 위에서 구성된 제어기로 제어가능한지 실험한다. 테스트용 회전형도립진자는 RealSYS사의 리얼시스 DSP Inverted Pendulum 2005년 생산품으로 실험한다.

• Proceedings of the Korean Nuclear Society Conference
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• 1998.05b
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• pp.903-908
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• 1998

KALIMER 원자로 건물에 대하여 3차원 쉘요소 모델과 단순 빔모델을 작성하고 고유진동수 해석을 수행하였다. 두 모델의 1차 수평방향 고유진동수는 대체로 일치하였다. 단순 빔모델에 대해 원자로건물의 회전 관성모멘트를 해석에 반영한 경우 3차원 모델에는 없는 회전모드가 발생되었다. 지진응답해석은 1940 EL Centro와 인공지진에 대하여 수행하였으며, 두 결과는 면진구조물의 경우 비면진구조물과 비교하여 응답가속도가 크게 줄고, 상대변위가 증가하는 경향을 보였다.

• Journal of the Korean Society of Marine Environment & Safety
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• v.21 no.5
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• pp.538-542
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• 2015

The transverse moment of inertia is an indispensable factor in analyzing the roll motion characteristics of ships and the calculating method needs to be based on the more reasonable theories when deciding the value as the results and reliability of analysis could be much affected by the correctness. However, the mass distribution and shape of hulls are quite complicated and give much difficulties in case of calculating the value directly from the ship design data, furthermore even acquiring the detailed design data for calculation is almost impossible. Therefore some simpler ways are practically adopted in the assumption that the gyradius of roll moment can be decided by a given ratio and hull width. It is well known that the responses of the free roll decay are varied according to the value of roll moment in view of roll period and amplitude decay ratio, so that the general formula to get the moment value can be derived also from the observation of roll decay responses. This study presents how the roll period and decay ratio are interrelated each other from the roll motion characteristics with suggesting a general formula to be able to calculate roll moment from it. Finally, the obtained general formula has been applied to a ship data to check the resultant characteristics through analyzing graphs and showed that the roll moment becomes more accurate when rolling period and decay ratio are considered together in calculation.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.2
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• pp.111-118
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• 2022

An electro-mechanical actuator (EMA) is an actuator that combines an electric motor with a mechanical power transmission elements, and it is suitable for urban air mobility (UAM) in terms of design freedom and maintenance. In this paper, the author presents the research results of the EMA that controls the rotor blade pitch angle of UAM. The actuator is based on an inverted roller screw and controls the blade pitch angle through a two-bar linkage. The dynamic equations for the actuator alone and the blade pitching motion with actuator were derived. For the latter, the equivalent moment of inertia is variable depending on the link angle due to the two-bar linkage. The variations of the equivalent moments of inertia are analyzed and compared in terms of the nut motion and the blade pitch motion. For an example model, the variation of the equivalent moment of inertia of the former is smaller than the latter, so it is judged that the dynamic equations derived from the point of view of the nut motion is suitable for the controller design.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.11
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• pp.1-8
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• 2006

A steady prediction method is presented to compute dynamic damping coefficients for axisymmetric projectiles. Viscous flow analysis is essential to the steady method using a zero-spin coning motion in the inertial coordinate frame. The present method is applied to compute the pitching moment and the pitch-damping moment coefficients for the Army-Navy Spinning Rocket. The results are in good agreement with the parabolized Navier-Stokes data, range data, and unsteady prediction data. Predictions for Secant-Ogive-Cylinder configurations are performed to investigate effects of afterbody geometries. To investigate the geometrical effect and flow physics, the longitudinal developments of the coefficients are examined in detail.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.2
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• pp.137-143
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• 2011

The pitch motion of a gravity-gradient satellite can be chaotic, depending on the ratio of mass moments of inertia and the eccentricity of the satellite orbit. For a precise prediction of motion, chaotic pitch motion has to be changed to non-chaotic motion. Feedback control can be used to obtain nonchaotic pitch motion. For chaos control and stabilization of the pitch motion of a gravity-gradient satellite, a feedback control system is designed, based on the linear nonautonomous system obtained by linearizing the nonlinear pitch motion. The control law obtained has two parameters and is applied to chaotic nonlinear pitch motion. The nonlinear control system satisfies the proposed control objectives in the range of the nonchaotic parameter space.