• International Journal of Aeronautical and Space Sciences
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• 제11권2호
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• pp.131-135
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• 2010

We report on the design of a three-axis missile autopilot using multi-objective control synthesis via linear matrix inequality techniques. This autopilot design guarantees $H_2/H_{\infty}$ performance criteria for a set of finite linear models. These models are linearized at different aerodynamic roll angle conditions over the flight envelope to capture uncertainties that occur in the high-angle-of-attack regime. Simulation results are presented for different aerodynamic roll angle variations and show that the performance of the controller is very satisfactory.

• 한국정보디스플레이학회:학술대회논문집
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• 한국정보디스플레이학회 2006년도 6th International Meeting on Information Display
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• pp.1291-1294
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• 2006

The technique presented in this paper maximizes LCD color performance by way of advanced gamma control technology. First, two gamma curves corresponding to two sub-pixels are mixed to minimize gamma distortion off-axis, then RGB gamma curve control is used to establish accurate on-axis color. Independent RGB curve control for each sub-pixel improves the LCD's performance both on- and off-axis.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.30-30
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• 2000

In the three axis control of satellite by using reaction wheel and gyro, a Gyro carries out measuring of the attitude angie and the attitude angular velocity. The Gyro is operated by the electronic part and the mechanic actuator. The digital part of the electronic part is consisted of the FPGA (Field Programmable Gate Array), which is one of the methods for designing VLSI (Very Large Scale Integrated Circuit), and the mechanic actuator processes the input/output data by the dynamic model. In the research of the mixed mode of Gyro, the simulation is accomplished by SABER of the mixed mode simulator and the results for the practical implementation of the satellite ACS (Attitude Control System) interfaced with the data processing are proposed.

• 제어로봇시스템학회논문지
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• 제8권1호
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• pp.54-59
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• 2002

In the three-axis control of satellites by using on-board actuators, gyros are usually used to measure the attitude angles and angular rates. The gyros are operated by electronic parts and mechanical actuators. The digital components of the electronic parts consist of largely FPGA (Field Programmable Gate Array) as one of the methods for VLSI(Very Large Scale Integrated) circuit design, while the mechanical parts provide output signal directly by mechanical actuation of a spinning rotor. In this research, a mixed mode of gyro is implemented in FGA. In addition to the hardware implementation, the simulation study was conducted by using the SABER for the mixed mode simulator. Results for the practical implementation of the satellite ACS (Attitude Control System) interfaced with the data processing are also presented to validate the FPGA implementation.

• 대한기계학회논문집A
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• 제38권9호
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• pp.925-932
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• 2014

회전체의 자이로스코픽 모멘트가 크거나 회전속도가 고속인 경우 회전속도에 따라 회전체의 동역학적 특성이 변화하는 정도가 커지게 되며, 자기베어링을 이용하여 회전축을 지지하는 경우 자기베어링의 제어기는 회전속도의 영향을 고려하여야 한다. 각 축의 부상력이 해당 축의 센서 출력에 의해서만 결정되는 독립축 제어기는 회전속도에 따른 변화에 대응하기 어려운 구조이나, 혼합축 제어기는 센서출력을 변환하여 진동 모드와 일치하도록 하고 각각의 진동 모드에 대해 독립적으로 제어기가 작동하는 구조로서, 진동 모드에 직접적으로 대응할 수 있는 장점이 있다. 본 논문에서는 회전체의 유연 모드를 포함하는 자기베어링 시스템의 수학적 모델을 기반으로 혼합축 제어기를 설계하고 제어기의 성능을 ISO 민감도 기준 및 불평형질량 응답 측면에서 평가하였다. 제어기 성능 평가 시 회전속도에 따른 시스템의 동특성 변화를 고려하여, 운전 속도 범위에서 성능 지표를 만족함을 확인하였다.

• 한국정밀공학회지
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• 제14권3호
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• pp.98-106
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• 1997

In this paper, a new method of position synchronizing control is proposed for multi-axes driving system. The proposed position synchronizing control system is constituted with speed and synchronizing controller. The speed controller is aimed at the following to speed reference. Furthermore, it is designed to guarantee low sensitivity under some disturbance as well as robustness against model uncertainties using $H_{\infty}$technique. The synchronizing controller is designed to keep minimizing the position error using PID control law which is considered to reduce the dimension of transfer function in the control system. Especially, the proposed method can be easily conducted by controlling only slave axis speed, because it, has variable structure which is decided to master and slave axis by the sign of synchronizing error. Therfore, the master axis which is smaller influenced than another axes by disturbance can be controlled without reducing or increasing its speed for precise position synchronization. The effectiveness of the proposed method is sucessfully confirmed through many experiments.s.

• 한국통신학회논문지
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• 제39C권1호
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• pp.82-89
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• 2014

최근 M2M/IoT에 대한 관심이 높아지면서 디바이스의 위치와 자세 등을 인식할 수 있는 동작 인식 센서의 필요성이 대두되고 있다. 본 논문에서는 소형의 디바이스에 적합하도록 저잡음, 저전력, 초소형 6축 관성센서 IC를 구현하였다. 본 논문에서 구현된 IC는 3축의 압전형 자이로 센서와 3축의 압저항형 가속도 센서를 사용하며, 3축의 자이로스코프 감지 회로, 자이로스코프 센서 구동 회로, 3축의 가속도 감지 회로, 16bit sigma-delta ADC, 디지털 필터와 제어 회로로 구성되어 있다. 본 IC은 TSMC $0.18{\mu}m$ mixed signal CMOS공정으로 개발되었으며, STM사의 6축 관성 센서인 LSM330의 소비전류 6.1mA보다는 약 27% 낮은 4.5mA의 소비 전류로 동작한다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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• pp.455-460
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• 1994

This paper presents a simple methodology for reducing the order of H$_{\infty}$ controllers in the mixed sensitivity control problems. The key point of this methodology is to transform the generalized plant expression to new one, where the control object and the weighting functions for the sensitivity function may have some poles on the imaginary axis. So that, this methodology makes it possible to use the standard method to solve the general H$_{\infty}$ design problems about the mixed sensitivity problems, even for a servo system or a oscillatory system. We derive that the order of H$_{\infty}$ controllers designed by this methodology may be reduced to n$_{p}$ where n$_{p}$ is the order of the denominator of the control object. It is clear that n$_{p}$ is lower than n$_{p}$ + n$_{s}$, which is the order of H$_{\infty}$ controllers obtained by the ordinary H$_{\infty}$ design method up to now, where n$_{s}$ is the order of the denominator of the weighting function for sensitivity. Finally, a numerical example is given to illustrate the results..lts.ts..lts.lts.

• 대한소아치과학회지
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• 제24권4호
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• pp.758-762
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• 1997

There are various types of localized tooth malpositions in the mixed dentition, such as abnormal tooth axis, anterior crossbite of some incisors, impaction, midline diastema, ectopic eruption, and so forth. We, Pediatric Dentists, have usually used removable appliances for these instances. But, removable orthodontic appliances, as is known, have marked limitations in some situations, for example, severe rotation, intrusion and extrusion, root torque, closure of large diastema, traction of impacted tooth, etc. In such cases, Whip spring, combined with fixed or removable appliance, can increase utilities of removable orthodontic appliances. The authors have applied whip springs to some cases showing localized positional and arrangement problems, and have witnessed the results as follows; 1. The refined and elaborate control of direction and magnitude of force by the operator, and accurate compliance of the patients were requisite for the treatment with it. 2. It showed special effectiveness for de rotation of incisors. Although it yields some benefit for root movement, the special consideration for incomplete roots in this age bracket was required. 3. In the localized malalignment cases in mixed dentition, uncurable with traditional removable appliances but practically unrealistic with fixed appliance therapy, the whip spring was thought to be a good alternative.

• 항공우주기술
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• 제13권1호
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• pp.44-54
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• 2014

본 논문에서는 3구 추력기 2모듈 형태의 추력기시스템 기준으로 발사체 상단 자세제어용 추력기시스템 명령생성방식 2가지를 제시한다. 하나는 혼합오차함수를 이용하는 방식이고, 다른 하나는 명령혼합함수를 이용하는 방식이다. 시뮬레이션을 통해 두 방식을 비교 분석한 결과, 제어축 간의 상호 간섭, 각축 제어기의 독립적인 설계와 분석 용이성, 비행성능 예측 가능성 등의 관점에서 명령혼합 알고리듬이 상대적으로 유리함을 보인다.