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마찰 구동형 압전 작동기를 이용한 카메라 손떨림 진동보상 기법 연구
조명신,황재혁,Cho, Myungsin,Hwang, Jaihyuk 항공우주시스템공학회 2015 항공우주시스템공학회지 Vol.9 No.4
The focal plane image stabilization for a camera is one of the most effective method that can increases the digital camera's image quality by compensating the vibration disturbance. The optical image stabilization can be implemented by making the focal plane to trace the path of incident light. To control the position of focal plane motion compensating stage precisely, a nonlinear control algorithm has been applied by considering coulomb friction which is nonlinear behavior of the compensator system. In our study, we have analyzed the hand shaking vibration using the gyro sensor, and made a mathematical model of compensating stage containing optical sensor and piezo-actuator. Then the nonlinear control algorithm has been designed and its performance has been verified by experiment. In this study, a friction driven peizo-electric actuator with $1{\mu}m$ resolution and 10mm/s speed has been used for stage movement.
소형 위성 카메라의 영상안정화를 위한 초점면부 보정장치의 제어
강명수,황재혁,배재성,Kang, Myoungsoo,Hwang, Jaihyuk,Bae, Jaesung 항공우주시스템공학회 2016 항공우주시스템공학회지 Vol.10 No.1
In this paper, position control of focal plane compensation device using piezoelectric actuator is conducted. The forcal plane compensation device installed on earth observation satellite camera compensates micro-vibration from reaction wheels. In this study, four experimental models of the open-loop compensation device are derived using MATLAB system identification toolbox in the input range of 0~50Hz. Subsequently, the PID controller for each model is designed and the performance test of each controller is conducted through MATLAB/Simulink. According to frequency response analysis of the closed-loop compensation device system, the PID controller designed for 38~50Hz input range has enough tracking performance for the whole 0~50Hz input range. The maximum output error is about $1{\mu}m$ for the input range. The simulation results has been verified by the experimental method.
중소형 무인기 브레이크 시스템용 복합형 지능재료펌프 설계
이종훈,황재혁,양지연,주용휘,배재성,권준용,Lee, Jonghoon,Hwang, Jaihyuk,Yang, Jiyoun,Joo, Yonghwi,Bae, Jaesung,Kwon, Junyong 항공우주시스템공학회 2015 항공우주시스템공학회지 Vol.9 No.3
In this study, the design of compound smart materials hydraulic pump that can be applied to a small-medium size UAV having a limited space envelope and weight has been conducted. Compound Smart Material Pump(CSMP) proposed in this paper is composed of a pressurize pump and a flow pump for supplying the high pressure and fluid displacement to overcome the disadvantages of the piezoelectric actuator which has a small strain. Though this compound smart material pump has been designed as small size and lightweight as possible, it can sequentially supply the sufficient large flow rate and pressure required for the brake operation. For the design of CSMP, about 2,700 kg (6,000 lb) class fixed wing manned aircraft was selected. Based on the established requirements, the design of the CSMP have been done by strength, vibration, and fluid flow analysis.
황재업(Jaeup Hwang),배재성(Jaesung Bae),황재혁(Jaihyuk Hwang),김정인(Jungin Kim),이수연(Suyeon Lee) 대한기계학회 2016 대한기계학회 춘추학술대회 Vol.2016 No.12
This paper is concerned with the semi-active magneto-rheological(MR) damper. A dynamic model of the MR damper is formulated by incorporating magnetic field-dependent properties of the MR fluid. The damping characteristics of MR damper by changing the intensity of the magnetic field are investigated and the dynamic responses of the landing gear with MR damper are simulated using ADAMS. The landing gear is simulated by implementing its performance as evaluated comparing with the experiment.
박정삼,배재성,황재혁,강국정,Park, Jungsam,Bae, Jaesung,Hwang, Jaihyuk,Kang, Kukjeong 항공우주시스템공학회 2008 항공우주시스템공학회지 Vol.2 No.3
Eddy current are induced when a nonmagnetic, conductive material is moving as the result of being subjected to the magnetic field, or if it is placed in a time-varying magnetic field. These currents circulate in the conductive material and are dissipated, causing a repulsive force between the magnet and conductor. Using this concept, eddy current damping can be used as a form of viscous damping. This paper investigated analytically and experimentally the characteristics of an eddy current damping when a permanent magnet is placed in a conductive tube. The theoretical model of the eddy current damping is developed from electromagnetics and is verified from Maxwell program and experiments. From these comparisons, although predictability is not accurate at high excitation frequencies, the present model can be used to predict damping force at low excitation frequencies. In order to improve the prediction of the characteristics of an eddy current damping, the induced magnetic flux densities have to be considered in following researches.
황재업,배재성,황재혁,홍예선,박상준,정태경,Hwang, Jaeup,Bae, Jaesung,Hwang, Jaihyuk,Hong, Yehsun,Park, Sangjoon,Chung, Taekyong 항공우주시스템공학회 2014 항공우주시스템공학회지 Vol.8 No.1
This thesis is simulated a aircraft nose landing gear drop-test. flow rate-to-pressure difference characteristics of damping orifices for a nose landing gear is investigated by CFD analyses. Orifice is kind of poppet valve type. it is simulated pressure drop with variable orifice area. it is simulated landing gear model by using ADAMS with CFD result. It's performance evaluated landing gear drop-test and analyzed the results.