• 소음진동
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• 제7권4호
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• pp.605-612
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• 1997

A state feedback controller and an observer have been developed and analyzed for an aircraft's safe landing in the windshear called microburst. The observer estimates the ambient wind field as well as the full-order longitudinal state vector. The controller uses the wind and state estimates for guiding the control inputs for safe landing. For the observer and controller gains, the design methodologies of linear quadratic estimation and linear quadratic regulation have been exploited. Analysis shows that some of the microburst-induced aircraft accidents in the past might have been avoided with the designed autopilot.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2003년도 학술회의 논문집 정보 및 제어부문 A
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• pp.115-118
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• 2003

In recent years, a receding horizon guidance law based on receding horizon control and optimal control is proposed. A receding horizon guidance law considering autopilot lag and constraints is proposed. The performance of receding horizon guidance law in the presence of target maneuvers is confirmed by simulation results. Through many simulation, a suitable selection of weighting matrix can minimize effect of disturbance, target acceleration. which is meaning of this paper.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1993년도 한국자동제어학술회의논문집(국내학술편); Seoul National University, Seoul; 20-22 Oct. 1993
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• pp.619-623
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• 1993

In this paper, a neural network is appled to design a lateral autopilot for airplanes. Linearized lateral dynamics is used in training the neural network controller and verifying the performance as well. To train the neural network, back propagation algorithm is used. In this training, no information about the dynamics to be controlled except sign and rough magnitude of control derivatives is needed. It is shown by computer simulations that the performance and stability margin are satisfactory.

• 한국항공우주학회지
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• 제30권7호
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• pp.81-89
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• 2002

현재까지 개발된 다양한 형태의 유도법칙은, 유도개념에 따라 추적방식, 미사일과 표적에 의해 정의되는 방위각을 일정하게 유지시키는 유도법칙, 그리고 표적의 기동 예측에 기반한 유도법칙 등으로 분류할 수 있다. 본 논문에서는 이러한 개념적인 유도목적을 일반화한 유도법칙을 제안하였다. 제안한 유도법칙은 충돌삼각형 상에서 정의된 목표각을 사용하는데, 목표각은 매개변수의 설정에 따라 다양한 형태가 될 수 있다. 르야프노프 이론을 사용하여, 제안한 유도법칙은 목표각 오차의 반응이 1차 시스템과 동일함을 증명하였다. 그리고 자동조종장치의 동역학이 느릴 경우는, 목표각 오차 반응을 2차 시스템으로 모사할 수 있는 유도법칙도 제안하였다. 제안한 유도법칙의 유용성을 보이기 위하여 측정잡음을 포함한 시뮬레이션을 수행하고 결과를 제시하였다.

• 대한조선학회논문집
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• 제34권3호
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• pp.19-26
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• 1997

본 논문에서는 신경망을 이용한 선박자동조타장치의 개발에 관한 연구결과를 소개한다. 앞의 논문에서 소개된 Back-Propagation 알고리즘을 이용하여 선박의 자동운항을 위한 자동제어방법을 개발하였으며 그 결과 기준모델추구신경망제어기와 순간최적제어기를 설계하였다. 기준모델추구신경망제어기는 선수각과 선수각속도가 주어진 기준모델을 추구하도록 타각을 제어하도록 하였으며, 순간최적제어기는 현 상태에서 다음상태로의 천이를 최적화하도록 하였다. 신경망에 근거한 이들 제어기법을 간단한 선박조종수치모델에 적용한 결과 그 효용성을 확인할 수 있었다.

• 대한전기학회:학술대회논문집
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• 대한전기학회 1999년도 하계학술대회 논문집 B
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• pp.569-572
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• 1999

This paper presents a method for designing an autopilot of the BTT missile using 2DOF Wiener-Hopf control technique to improve tracking performance. Linear controllers are designed based on the linearized models which are obtained from the nonlinear missile dynamic equations at various operating points. The gain scheduling technique is used to implement the final autopilot. A simulation on the flight of missiles is carried out through the use of 6DOF equation program including exact nonlinear equations of the missile and the variations of aerodynamic variables in order to check applicability of the suggested method in real situation.

• 한국군사과학기술학회지
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• 제6권3호
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• pp.122-130
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• 2003

This paper is concerned with a control allocation strategy using the dynamic inversion and the pseudo inverse control which generates the nominal control input trajectories, and autopilot design using time-varying control technique which is time-varying version of pole placement of linear time-invariant system for an agile missile with aerodynamic fin and thrust vectoring control. Control allocation of this paper is capable of extracting the maximum performance from each control effector, aerodynamic fin and thrust vectoring control, by combining the action of them. Time-varying control technique for autopilot design enhance the robustness of the tracking performance for a reference command. The main results are validated through the nonlinear simulation.

• 제어로봇시스템학회논문지
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• 제7권12호
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• pp.1031-1035
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• 2001

In this paper, a robust recursive control approach for nonlinear system, which is based on Lyapunov stability, is proposed. The proposed method can apply to extended systems including cascaded systems and the stability is guaranteed in the sense of Lyapunov. The recursive design procedure so called “robust recursive control approach” is used to find a stabilizing robust controller and simultaneously estimate the uncertainty parameters. First, a nonlinear model with uncertainties whose bounds are unknown is derived. Then, unknown bounds of uncertainties are estimated. By using these estimates, the stabilizing robust controller is updated at each step. This approach is applied to the pitch autopilot design of a nonlinear missile system and simulation results indicate good performance.

• 제어로봇시스템학회논문지
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• 제4권4호
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• pp.458-463
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• 1998

This paper presents an autopilot design method for STT missiles using the intelligent control technique and multiple controllers. The mixed $H_2/H_{\infty}$ control technique is applied for each controller design and the control gains are implemented by using the genetic searching algorithm. To facilitate automatic switching of multiple controllers under different operating conditions, an error based switching scheme is also combined with the multiple controllers at a higher level, which constitutes a hierarchical intelligent control system. It is shown via computer simulation that the proposed autopilot outperforms the conventional one.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.1304-1307
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• 1996

In this paper, we present a robust Two Degree of Freedom (TDF) $H_{\infty}$ controllers for a missile system. The feedback controller is designed to meet robust stability and disturbance rejection specifications while the prefilter is used to improve the robust model matching properties of the closed loop system. As the perturbed model, we use the normalized coprim factor perturbations. These controllers are designed using $H_{\infty}$ optimization procedures, and applied to a missile model via simulation.