• 한국군사과학기술학회지
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• 제8권3호
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• pp.92-100
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• 2005

The objective of this paper is to design a sliding mode controller of an electro-mechanical fin actuation system using extended reducer-observer(ERO) which is used in order to estimate the velocity. The employed observer enables proper estimation of the plant state variables, even in the case of the constant or slow varying load torque disturbances. The effectiveness of this control scheme is verified by comparison with a PID control through a series of simulation studies. The simulation results show that the sliding mode control designed with the ERO gives good control performances.

• 한국군사과학기술학회지
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• 제10권3호
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• pp.181-188
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• 2007

This paper presents a torque control method of a hydraulic actuation system for measuring the dynamic stiffness of missile fin actuators. We propose a new control technique called Dual Dynamic Torque Feedback Control(DDTFC), which improves the stability of the torque control system and enables fast tracking of torque command. The developed control scheme is derived from the physical understanding based on mathematical modelling and analysis. The dynamics of hydraulic torque control servo-system is unravelled via physics-based modelling and nonparametric system identification. In order to verify the effectiveness of the method, the experiment is carried out with a test equipment for measuring the dynamic stiffness. The experiment and simulation results show that DDTFC gives stability improvement.

• 전기학회논문지
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• 제59권1호
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• pp.70-75
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• 2010

The objective of this paper is to propose a new velocity measurement method for an electro-mechanical fin actuator. The model of the electro-mechanical fin actuator includes uncertainties such as unknown disturbances and parameter variations in flight condition. So, an electro-mechanical fin actuator system needs robust control algorithm which requires not only position information but also velocity information. Usually, analog tachometers have been used for velocity feedback in an electro-mechanical fin actuator. However, using these types of sensors have problems such as the cost, space, and malfunction. These problems lead to propose a new velocity measurement method using linear type Hall-effect sensor. In order to verify the proposed method, several experiments are performed using Model Following Sliding Mode Controller(MFSMC). It is shown that the MFSMC with a new velocity measurement method using linear type Hall-effect sensor can satisfy the requirements without using of velocity sensor.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1991년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 22-24 Oct. 1991
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• pp.1104-1109
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• 1991

Recently, Pneumatic Actuation System (PAS) has been used increasingly as a high performance fin-control servo actuation systems because of the special advantages of pneumatic units: primarily their low cost, small size, light weight, and tolerance to broad temperature extremes. In this study, a nonlinear model of PAS is derived through the detailed analysis of the major components in the typical system. The model includes nonlinear flow-pressure relationships of the flow through the solenoid valve openings and orifices, PWM algorithm for driving two solenoid valves as a closed-center 3-way valve for minimum gas consumption, solenoid valve dynamics, saturation, and friction. Simulation results are compared with the experimental ones for square and sinusoidal inputs to see the validity of the model. Independent of the shape and magnitude of the input signals, both results are in good agreements with minor difference.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.537-541
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• 2003

In order to control the missiles by aerodynamics, control surfaces sometime called fins are used. Deflection angles of these fins are the right control variables of the aerodynamics, but aerodynamicists prefer to use analytic variables called aileron, elevator and rudder instead of these physical variables, because these three analytic variables dominantly influence on the roll, pitch and yaw channels of the missile maneuver, respectively, and each can be assumed a linear combination of four fin deflection angles. On that basis, roll, pitch and yaw autopilots for controlling the attitudes or lateral acceleration of the missile are designed, and as a consequence outputs of each autopilot are aileron, elevator and rudder commands, respectively. In the existing fin control scheme for the typical tail-fin controlled cruciform missiles, firstly these outputs are distributed to four fin defection commands, and after that four fins are actuated by fin controllers so that their deflections follow the commands. This paper shows that performance of such control schemes can be degraded significantly when fin actuators have certain physical constraints such as slew rate, voltage or current limit, uncertainty of actuator dynamics, and so on, and propose a new control scheme which alleviates such problems. This scheme can be widely applied to various fin actuation systems. But in this paper, for convenience, tail-fin controlled cruciform missile is taken as an example, and it is shown that a proposed control scheme gives better performance than the existing one.

• 항공우주기술
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• 제1권1호
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• pp.141-146
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• 2002

로켓 추진에 의한 동력 비행 중 비행체의 자세제어를 위해, 대기권내 비행에 있어서는 공력비행 조정익으로 조종할 수 있으나 공기가 희박한 높은 고도나 대기권 밖에서의 비행은 추력벡터제어에 의존할 수밖에 없다. 추력벡터제어 방법으로 현재 여러 가지 장치가 개발되어 사용되고 있는데 본 연구는 로켓이 비행하는 동안 김발에 의해 연결된 로켓엔진 전체를 움직여 엔진에서 발생한 추력의 방향을 조종하여 로켓의 자세를 제어하는 김발엔진구동 추력벡터제어방식에 대한 내용을 다루었다. 로켓에 적용 가능한 김발엔진 구동장치로는 전기유압식, 전기기계식, 공압식 장치 등이 있으나 큰 동력이 요구되는 시스템에서는 대부분 출력 대 무게비가 높은 전기유압식 구동장치가 사용된다. 본 연구에서는 KSR-III의 추력벡터제어를 위해 사용되는 전기유압식 김발엔진 서보구동시스템을 상세모델링하였고 이에 기초하여 시뮬레이션을 수행하였다. 그리고 시뮬레이션 결과와 실제 시스템을 대상으로 시험한 결과를 비교하여 모델을 검증하였다.

• 대한기계학회논문집A
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• 제33권11호
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• pp.1300-1305
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• 2009

The various electromagnetic based actuation(EMA) methods have been proposed for actuating microrobot. The advantage of EMA is that it can provide wireless driving to microrobot. In this reason a lot of researchers have been focusing on the EMA driven microrobot. This paper proposed a swimming microrobot driven by external alternating magnet field which is generated by two pairs of Helmholtz coils. The microrobot has a fish-like shape and consists of a buoyant robot body, a permanent magnet, and a fin. The fin is directly linked to the permanent magnet and the magnet is swung by the alternating magnet field, which makes the propulsion and steering power of the robot. In this paper, firstly, we designed the locomotive mechanism of the microrobot boy EMA. Secondly, we set up the control system. Finally, we demonstrated the swimming robot and evaluated the performance of the microrobot by the experiments.

• 한국군사과학기술학회지
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• 제22권3호
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• pp.392-400
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• 2019

This paper provides a fin actuation system of missile based on electromagnetic-spring mechanism to miniaturize the system and lower the cost. Compared with proportional electro-mechanical actuators, the output of Electromagnetic-Spring Actuators(EMSA) has two or three discrete states, but the mechanical configuration of EMSA is simple since it does not need power trains like gears. The simple mechanism of EMSA makes it easy to build small size, low cost, and relatively high torque actuators. However, fast response time is required to improve the dynamic performance and accuracy of missiles since bang-off-bang operation of EMSA affects the flight performance of missile. In this paper the development of EMSA including parameter optimization and mathematical modeling is described. The simulation results using Simulink and experimental test results of prototype EMSAs are presented.

• Composites Research
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• 제27권2호
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• pp.47-51
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• 2014

본 논문은 기존의 유/공압 및 전기식 모터를 대체할 수 있는 경량, 고성능 지능소자 구동기를 설계/제작하고 이를 소형 무인비행체의 조종익 시스템에 적용 가능성을 연구한 것이다. 또한 압전 복합재료 작동기에 대한 성능평가를 수행하였으며, 유니모프 및 바이모프 형태의 작동기를 제작하여 각각의 작동 특성을 확인하였다. 이와 같은 성능시험 평과 결과를 통해 바이모프 형태의 작동기가 하중 유무와 무관하게 선형적인 받음각 변화를 가짐을 알 수 있었다. 이러한 지능소자 구동 시스템은 소형 로봇, 유도무기 및 MAV, UAV의 조종익 제어 시스템으로 사용될 수 있는 가능성을 확인하였다.