• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1987년도 한국자동제어학술회의논문집; 한국과학기술대학, 충남; 16-17 Oct. 1987
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• pp.643-646
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• 1987

A criterion is developed for the, selection of the best pairing of the control and manipulated variables and for the interaction analysis of decentralized multi-input multi-output control systems. This criterion is based on the difficulty caused by the interaction terms in finding the in-verse of the block steady gain matrix. A quantitative measure of the best pairing is obtained from the resemblance of a set of independent block multi-loop systems. Several examples show the validity of the pairing criterion.

• Advances in aircraft and spacecraft science
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• 제6권5호
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• pp.371-389
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• 2019

The implementation of a robust $H_{\infty}$ Control, which is numerically efficient for uncertain nonlinear dynamics, on longitudinal and lateral autopilots is realised for a quarter scale Piper J3-Cub model accepted as an unmanned aerial vehicle (UAV) under the condition of sensor noise and disturbance effects. The stability and control coefficients of the UAV are evaluated through XFLR5 software, which utilises a vortex lattice method at a predefined flight condition. After that, the longitudinal trim point is computed, and the linearization process is performed at this trim point. The "${\mu}$-Synthesis"-based robust $H_{\infty}$ control algorithm for roll, pitch and yaw displacement autopilots are developed for both longitudinal and lateral linearised nonlinear dynamics. Controller performances, closed-loop frequency responses, nominal and perturbed system responses are obtained under the conditions of disturbance and sensor noise. The simulation results indicate that the proposed control scheme achieves robust performance and guarantees stability under exogenous disturbance and measurement noise effects and model uncertainty.

• Journal of Power Electronics
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• 제7권1호
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• pp.1-12
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• 2007

Novel nonlinear backstepping control with integrated adaptive control function is developed for high-performance positioning control systems. The proposed schemes are synthesized by a systematic approach and implemented based on a modern low-cost DSP controller, TMS320C32. A baseline backstepping control scheme is derived first, and is then extended to include a nonlinear adaptive control against the system parameter changes and load variations. The backstepping control utilizes Lyapunov function to guarantee the convergence of the position tracking error. The final control algorithm is a convenient in the implementation of a practical 32-bit DSP controller. The new control system can achieve superior performance over the conventional nested PI controllers, with improved position tracking, control bandwidth, and robustness against external disturbances, which is demonstrated by experimental results.

• Journal of Advanced Marine Engineering and Technology
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• 제33권8호
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• pp.1212-1219
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• 2009

본 연구에서는 실용설계의 새로운 도구로써 제어계의 강인성, 성능, 안정성 등의 설계지침을 정량화하기 쉽고 해가 효율적으로 구해져 주목받는 선형행렬부등식을 이용하여 강인한 LMI 제어기를 설계한다. 우선 다층상 구조물의 진동제어를 위해 수학적 모델링을 행하고 적분형 서보계를 적용한 LMI 제어 기법으로 상태 피드백 제어칙을 설계한다. 다음으로 설계한 제어칙으로 시스템 불확실성의 변동에 대해 시간영역의 설계사양을 고려한 경우와 고려하지 않은 경우에 대하여 시뮬레이션을 행하고 실제 적용 가능성을 검토한다.

• 한국정보통신학회논문지
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• 제22권8호
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• pp.1099-1106
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• 2018

본 논문은 장거리 다기능레이더용 주파수합성기 개발에 관한 것으로 다기능레이더 체계의 기능 및 성능을 보장하기 위해 필요한 주파수합성기 성능지표를 도출하고 분석하였다. 다기능레이더는 위상배열 전자 스캔 방식을 적용한 레이더체계이고, 주파수합성기는 STALO를 포함하여 다기능레이더에 필요한 다양한 주파수신호를 합성하는 역할을 수행한다. 다기능레이더 요구사항 분석을 통해 최적의 주파수합성 방식을 선택하고, 회로크기를 포함한 성능 및 기능을 최적화하였다. 도출된 MFR용 주파수합성기 개발규격을 만족하기 위해 DDS-driven Offset-PLL(Phase Locked Loop) 방식을 사용하여 낮은 위상 잡음과 빠른 주파수 고정 시간, 우수한 불요파 특성을 갖는 주파수 합성기를 설계 및 제작하였다. 제작된 다기능 레이더용 주파수합성기는 위상잡음 -131dBc/Hz@100kHz 이하, 주파수 고정시간 $4.1{\mu}s$ 이하의 성능을 측정하였다.

• Journal of Advanced Marine Engineering and Technology
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• 제34권1호
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• pp.92-101
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• 2010

본 연구에서는 회전체를 지지하는 자기 베어링에 관하여, 2장에서는 적분형 서보계를 이용하여 횡축형 자기베어링 시스템(Horizontal-shaft Magnetic Bearing System: HMBS)에 대한 불확실성을 고려하면서 과도상태 응답개선에 대한 이론적인 고찰과 제어기설계 수식을 유도한다. 그리고 HMBS에 대해 물리 퍼래미터 변동에 대한 강인성과 외란의 영향을 저감하고 기준위치 변경에 따른 추종성을 갖도록 상태 피드백 제어기를 LMI 기법을 이용하여 설계한다. 3장에서는 설계한 제어칙을 가지고 시스템 불확실성의 변동에 대해 시간영역의 설계사양을 고려한 경우와 고려하지 않은 경우에 대하여 시뮬레이션을 행하고 실제 적용 가능성을 검토한다.

• International Journal of Aeronautical and Space Sciences
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• 제8권1호
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• pp.10-20
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• 2007

For spacecraft attitude control, reaction wheel (RW) steering laws with more than three wheels for three-axis attitude control can be derived by using a control allocation (CA) approach.1-2 The CA technique deals with a problem of distributing a given control demand to available sets of actuators.3-4 There are many references for CA with applications to aerospace systems. For spacecraft, the control torque command for three body-fixed reference frames can be constructed by a combination of multiple wheels, usually four-wheel pyramid sets. Multi-wheel configurations can be exploited to satisfy a body-axis control torque requirement while satisfying objectives such as minimum control energy.1-2 In general, the reaction wheel steering laws determine required torque command for each wheel in the form of matrix pseudo-inverse. In general, the attitude control command is generated in the form of a feedback control. The spacecraft body angular rate measured by gyros is used to estimate angular displacement also.⁵ Combination of the body angular rate and attitude parameters such as quaternion and MRPs(Modified Rodrigues Parameters) is typically used in synthesizing the control command which should be produced by RWs.¹ The attitude sensor signals are usually corrupted by noise; gyros tend to contain errors such as drift and random noise. The attitude determination system can estimate such errors, and provide best true signals for feedback control.⁶ Even if the attitude determination system, for instance, sophisticated algorithm such as the EKF(Extended Kalman Filter) algorithm⁶, can eliminate the errors efficiently, it is quite probable that the control command still contains noise sources. The noise and/or other high frequency components in the control command would cause the wheel speed to change in an undesirable manner. The closed-loop system, governed by the feedback control law, is also directly affected by the noise due to imperfect sensor characteristics. The noise components in the sensor signal should be mitigated so that the control command is isolated from the noise effect. This can be done by adding a filter to the sensor output or preventing rapid change in the control command. Dynamic control allocation(DCA), recently studied by Härkegård, is to distribute the control command in the sense of dynamics⁴: the allocation is made over a certain time interval, not a fixed time instant. The dynamic behavior of the control command is taken into account in the course of distributing the control command. Not only the control command requirement, but also variation of the control command over a sampling interval is included in the performance criterion to be optimized. The result is a control command in the form of a finite difference equation over the given time interval.⁴ It results in a filter dynamics by taking the previous control command into account for the synthesis of current control command. Stability of the proposed dynamic control allocation (CA) approach was proved to ensure the control command is bounded at the steady-state. In this study, we extended the results presented in Ref. 4 by adding a two-step dynamic CA term in deriving the control allocation law. Also, the strict equality constraint, between the virtual and actual control inputs, is relaxed in order to construct control command with a smooth profile. The proposed DCA technique is applied to a spacecraft attitude control problem. The sensor noise and/or irregular signals, which are existent in most of spacecraft attitude sensors, can be handled effectively by the proposed approach.