• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.162-170
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• 2005

In KSLV-I, actuation system for thrust vector control of kick motor was configured as electro-hydraulic servo actuation system and consisted of actuators, hydraulic power supply system, hydraulic power distribution system and control system. In case of hydraulic power supply system, we use EMDP(Electric Motor Driven Pump) to supply hydraulic power. Generally, we use brushed DC motor for EMDP but it is not easy to operate EMDP using brushed DC motor at a high altitude. Hence, we are developing EMDP using brushless DC motor to use at a high altitude. In this study, we will explain control system for BLDC motor to drive hydraulic pump.

• Proceedings of the KOSOMBE Conference
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• v.1995 no.05
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• pp.78-81
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• 1995

본 연구에서는 슬라이딩 모드를 전기유압식 심실보조기의 직류모터제어기의 속도와 위치제어에 적용하였다. 슬라이딩 모드 컨트롤은 가변구조시스템(varaiable sturucture system)의 일종으로 적절한 내부스위칭 논리를 갖는 연속적인 부시스템(subsystem)의 모임으로 구성된다는 접에서 고정된 제어구조를 갖는 일반적인 제어시스템과 다르다. 이 시스템은 불연속적인 동적시스템이나 시변적인 요소를 갖는 시스템등에서 사용되고 있다. 이 논문에서는 슬라이딩 모드 제어를 적용하여 좌심실보조기를 제어하는 경우에 넓은 작동범위에서도 시스템이 안정적이며 혈류역학적인 외란에 대해서도 기준입력에 대한 속도의 추종이 잘 이루어지는지의 여부를 실제의 구현에 앞서 컴퓨터모델을 통해 검증하고 문제점들을 조사하였다.

• Journal of the Korean Society for Precision Engineering
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• v.14 no.9
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• pp.139-145
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• 1997

This study is concerned with the optimizing method of control parameters for a hydraulic speed control system by using genetic algorithms which are general purpose search algorithms based on natural evolution and genetics. It is shown that the genetic altorithms satisfactorily oiptimized control gains of the PI speed control system of an electrohydraulic servomotor and that optimization of control para- meters can be achived without much experience and knowledge for tuning. It is also shown that optimal gains may be determined from fitness distribution curves plotted in given gain spaces.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.10
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• pp.738-746
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• 2019

Instead of hydraulic actuation systems, an electromechanical actuation system is more efficient in terms of weight, cost, and test evaluation in the thrust vector control of the 7-ton gimbal engine used in the Korea Space Launch Vehicle-II(KSLV-II) $3^{rd}$ stage. The electromechanical actuator is a kind of servo actuator with position feedback and uses a BLDC motor that can operate at high vacuum. In the case of the gimballed rocket engine, a synthetic resonance phenomenon may occur due to a combination of a vibration mode of the actuator itself, a bending mode of the launcher structure, and an inertial load of the gimbals engine. When the synthetic resonance occurs, the control of the rocket attitude becomes unstable. Therefore, the requirements for the stiffness have been applied in consideration of the gimbal engine characteristics, the support structure, and the actuating system. For the 7-ton gimbal engine of the KSLV-II $3^{rd}$ stage, the stiffness requirement of the actuation system is $3.94{\times}10^7N/m$, and the direct drive type electromechanical actuator is designed to satisfy this requirement. In this paper, an equivalent stiffness analysis model of a direct drive electromechanical actuator designed based on the stiffness requirements is proposed and verified by experimental results.