• Journal of Biosystems Engineering
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• 제36권6호
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• pp.476-483
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• 2011

The aerial application using an unmanned helicopter has been already utilized and an attitude controller would be developed to enhance the operational convenience and safety of the operator. For a preliminary study of designing flight controller, a state space model for an RC helicopter would be identified. Frequency sweep flight tests were performed and time history data were acquired in the previous study. In this study, frequency response of the flight test data of a small unmanned helicopter was analyzed by using the CIFER software. The time history flight data consisted of three replications each for collective pitch, aileron, elevator and rudder sweep inputs. A total of 36 frequency responses were obtained for the four control stick inputs and nine outputs including linear velocities and accelerations and angular velocities in 3-axis. The results showed coherence values higher than 0.6 for every primary control inputs and corresponding on-axis outputs for the frequency range from 0.07 to 4 Hz. Also the analysis of conditioned frequency response showed its effectiveness in evaluating cross coupling effects. Based on the results, the dynamic characteristics of the model helicopter can further be analyzed in terms of transfer functions and the undamped natural frequency and damping ratio of each critical mode.

• 대한전자공학회논문지TE
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• 제42권4호
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• pp.47-52
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• 2005

본 논문에서는 다변수 제어시스템 설계시 효과적인 제어를 어렵게 만드는 요인 중의 하나인 입력과 출력의 결합문제를 해결하기 위해서 각 채널의 출력변수는 대응되는 입력 신호에 의해서만 독립적으로 조정되도록 하는 비결합 제어기를 설계하였다. 설계된 제어기는 비결합 조건뿐만 아니라 제어계의 강인성을 동시에 고려할 수 있는 특성을 2자유도 구조에 적용하였다. 또한 제어기를 구하는 경우 계산을 용이하게 하기 위해서 플랜트를 표준모델로 확장시킨 후 전달행렬을 이용하여 상태공간계수로 표현하였다. 이 경우 비결합제어기의 자유매개변수를 구하는데 있어서 지능형탐색방법의 일종인 유전알고리즘을 적용하였다. 일반적으로 유전알고리즘을 특정한 문제에 적용할 경우 그 문제가 가지고 있는 최적화 특징을 잘 파악하여 이것을 이용하는 것이 유전알고리즘 적용시 성공여부를 결정하는 중요한 요인이 된다. 따라서 본 논문에서는 유전알고리즘을 이용하여 고정 차수의 정방 비결합제어기의 $H_{\infty}$설계시 효율적인 방법을 제시하였다.

• Industrial Engineering and Management Systems
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• 제1권1호
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• pp.1-9
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• 2002

Among the state-space description of discrete vent systems, the max-plus algebra is known as one of the effective approach. This paper proposes a model predictive control (MPC) design method based on the max-plus algebra. Several studies related to these topics have been done so far under the constraints that system parameters are constant. However, in practical systems such as production systems, it is common and sometimes inevitable that system parameters vary by each event. Therefore, it is of worth to design a new MPC controller taking account of adjustable system parameters. In this paper, we formulate system parameters as adjustable ones, and they are solved by a linear programing method. Since MPC determines optimal control input considering future reference signals, the controller can be more robust and the operation cost can be reduced. Finally, the proposed method is applied to a production system with three machines, and the effectiveness of the proposed method is verified through a numerical simulation.

• 한국지능시스템학회:학술대회논문집
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• 한국퍼지및지능시스템학회 2005년도 추계학술대회 학술발표 논문집 제15권 제2호
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• pp.95-98
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• 2005

This paper presents intelligent digital redesign method of global approach for hybrid state space fuzzy-model-based controllers. For effectiveness and stabilization of continuous-time uncertain nonlinear systems under discrete-time controller, Takagi-Sugeno(TS) fuzzy model is used to represent the complex system. And global approach design problems viewed as a convex optimization problem that we minimize the error of the norm bounds between nonlinearly interpolated linear operators to be matched. Also by using the power series, we analyzed nonlinear system's uncertain parts more precisely. When a sampling period is sufficiently small, the conversion of a continuous-time structured uncertain nonlinear system to an equivalent discrete -time system have proper reason. Sufficiently conditions for the global state -matching of the digitally controlled system are formulated in terms of linear matrix inequalities (LMls). Finally, we prove the effectiveness and stabilization of the proposed intelligent digital redesign method by applying the chaotic Lorentz system.

• Transactions on Electrical and Electronic Materials
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• 제15권6호
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• pp.297-304
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• 2014

Due to the nonlinearity and complexity of the three-phase photovoltaic inverter, we propose an intelligent control based on fuzzy logic and the classical proportional-integral-derivative. The feedback linearization method is applied to cancel the nonlinearities, and transform the dynamic system into a simple and linear subsystem. The system is transformed from abc frame to dq0 synchronous frame, to simplify the state feedback linearization law, and make the close-loop dynamics in the equivalent linear model. The controls improve the dynamic response, efficiency and stability of the three-phase photovoltaic grid system, under variable temperature, solar intensity, and load. The intelligent control of the nonlinear characteristic of the photovoltaic automatically varies the coefficients $K_p$, $K_i$, and $K_d$ under variable temperature and irradiation, and eliminates the oscillation. The simulation results show the advantages of the proposed intelligent control in terms of the correctness, stability, and maintenance of its response, which from many aspects is better than that of the PID controller.

• 전자공학회논문지
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• 제50권1호
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• pp.246-253
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• 2013

본 논문에서는 유동의 안정된 흐름 제어를 위한 유동제어에 대해 다룬다. 전산유체역학 해석을 통해 제공된 대용량의 유동 데이터를 POD 방법을 통하여 축약하고, 제어측면에서 시간 및 주파수 영역에서의 분석에 근거하여 적절한 수준의 저차 모델링한다. 한편, 유동장 표면에 부착된 압력센서로부터 공간상의 유동상태 추정을 위해 신경망 구조를 갖는 유동추정기를 구성하고, 되먹임 유동제어기를 설계함으로써 유동제어루프를 구성한다.

• 대한기계학회논문집
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• 제13권2호
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• pp.213-220
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• 1989

본 연구에서는 고정도의 위치제어계를 실현하기 위하여 가변구조제어이론을 전기-유압서보계에 적용하였다.실험은 유압구동부의 공급압력을 변화시켜 유압계의 매개변수를 변화시켜줄 때와 관성하중을 가감하여 부하를 변화시켜 가며 행하였다. 가변구조계에서는 계의 매개변수변동과 부하변동에도 영향을 받지 않음을 종래의 고정구조계와 구조계와 비교, 검토하였다.

• 한국정밀공학회지
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• 제14권1호
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• pp.174-184
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• 1997

This paper presents a robust force tracking control of a smart flexible gripper featured by a piezoceramic actuator characterizing its durability and quick response time. A mathematical governing equation for the proposed gripper structure is derived by employing Hamilton's principle and a state space control model is subsequently obtained through model analysis. Uncertain system parameters such as frequency variation are included in the control model. A sliding mode control theory which has inherent robustness to the sys- tem uncertainties is adopted to design a force tracking controller for the piezoceramic actuator. Using out- put information from the tip force sensor, a full-order observer is constructed to estimate state variables of the system. Force tracking performances for desired trajectories represented by sinusoidal and step func- tions are evaluated by undertaking both simulation and experimental works. In addition, in order to illustrate practical feasibility of the proposed method, a two-fingered gripper is constructed and its performance is demonstrated by showing a capability of holding an object.

• Journal of Astronomy and Space Sciences
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• 제11권2호
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• pp.281-295
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• 1994

본 논문에서는 운동량 바이어스 안정화된 인공위성의 능동 미동 제동율 위한 자동 제어기의 설계에 새로운 연속의 스위칭 방정식율 도입한 가변구조 시스댐 이론을 사용하였다. 일반적으로 미동 제동을 갖고 있는 션형화된 다변수 시스템에 가변구조 이론을 적용할 때, 스위칭 이득을 어떻게 결정해야 하는지, 진동 현상과 입력과 상태 궤적에 도달기간을 어떻게 줄여야 하는지 등의 단점을 갖고 있다. 이러한 문제를 해결하기 위해서 본 논문에셔는 슬라이딩 모드를 얻기 위한 불연속의 스위칭 로직 대신에 연속의 스위칭 방정식을 제시하였다. 이 새로운 접근방법은 기존의 가변구조 이론에 의한 방법보다 훨씬 간단하고, 구해진 제어입력이 연속이므로 진동현상이 없으며, 동시에 설계인자를 적절하게 선정하므로써 도달기간을 줄일 수 있게 된다.

• International Journal of Aeronautical and Space Sciences
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• 제9권1호
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• pp.162-168
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• 2008

A design objective for variable stability flight control system is to develop a controller of in-flight simulation capability that forces the aircraft being flown to follow the dynamics of other aircraft. This paper presents a model-following variable stability control system (VSS) for in-flight simulation which consists of feedforward and feedback control laws, the aircraft dynamic model to be simulated, and switching and fader logics to reduce the transient effect between two aircraft dynamics. The separate design techniques for feedforward and feedback control law proposals are based on model matching and augmented linear quadratic (LQ) techniques. The system allows pilots to select and engage VSS mode, and when deselected, the aircraft reverts to the baseline flight control system. Both the baseline flight control laws and VSS control laws are computed continuously during flight. Initialization of the state values are necessary to prevent instability, since VSS control laws have integrators and filters in longitudinal, and lateral/directional axes. This paper demonstrates and validates the effectiveness and quality of VSS with F-16 models embedded in T-50 in-flight simulation aircraft.