• Proceedings of the KIEE Conference
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• summer
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• pp.1510-1512
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• 2004

본 연구는 농형 유도 발전기와 양방향 PWM 인버터를 가진 WECS (Wind Energy Conversion System)시스템을 모델링하고 이 모델에 기초하여 제어 법칙을 제안하였다. 제어 법칙은 풍속 따라 작용하는 최적 팁 속도비에 의해 효율이 최대가 되도록 제어하는 것이다. WECS은 바람의 변동이 있어도 최적치에 팁 속도비를 유지하기 위해 터빈의 회전 속도 제어하여 행한다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.11
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• pp.1104-1111
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• 2009

In the low altitude, mission of the aircraft is restricted by a variety of threats such as anti-air missiles and terrain obstacles. Especially, aircraft have always a risk of ground collision near terrain. In this study, to effectively solve this problem, we developed the flight path generation algorithm that is considered the terrain avoidance. In this flight path generation algorithm, waypoints that should be passed by the UAV are selected first. The waypoints are located in the middle of the terrain obstacles. Then, physically meaningful waypoints sets are classified by Dijkstra algorithm. The optimal waypoint guidance law based on the optimal control theory is applied to produce trajectory candidates. And finally the minimum control energy trajectory is determined.

• 한국항공운항학회:학술대회논문집
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• 2015.11a
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• pp.247-251
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• 2015

본 논문에서는 항공기의 3자유도 질점 모델과 Dubins 곡선을 이용한 3차원 경로생성 알고리즘 및 비선형 경로추종 유도기법을 통합하여 항공기의 경로계획을 위해 적용한 경로생성 알고리즘을 검증하고, 경로추종 성능과 항공교통관리를 위한 시뮬레이션에 3자유도 질점 항공기 모델 사용의 타당성을 확인하였다. 최적경로 생성을 위해 사용된 Dubins 곡선의 경우 계산속도가 빠르고 경로계획에 바로 적용이 가능하다는 장점이 있다. 하지만 주로 2차원 상의 경로문제를 다루기 때문에 이를 3차원 비행경로로 확장시킨 알고리즘을 사용하였다. 경로추종을 위한 유도제어법칙은 Specific Acceleration 명령을 통해 자세를 제어하는 비선형 경로추종 유도법칙을 활용하였으며, 이에 대한 결과를 확인하였다.

• Journal of the Korea Institute of Military Science and Technology
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• v.11 no.3
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• pp.5-12
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• 2008

This paper presents the features of an impact angle constrained open-loop optimal trajectory which is given by a function of initial conditions and optimal guidance gains. Using missile motion described by linearized kinematic equations and a proper form of performance index, an inverse optimal problem is suggested to investigate the gains related to the performance index. The flight trajectory and time-to-go can be shaped in terms of the optimal guidance gains. The results are evaluated by 3-DOF simulation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.10-10
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• 1999

선형 및 비선형 GPA 기법을 이용한 가스터빈 엔진의 성능예측 및 진단을 연구하고 전형적 산업용 가스터빈 엔진인 TB5000에 적용하여 최적의 계측변수를 정의하였다. 선형 GPA는 가스가 지나가는 구성품의 계측가능한 온도, 압력, 연료유량, 로터 회전수 등과 같은 종속변수와 효율, 유량과 같은 측정불가능한 독립변수의 관계 방정식을 열역학 법칙, 연속방정식, 질량 및 에너지 보존법칙, 구성품 성능곡선 등으로부터 유도하는 것이며 비선형 GPA는 독립변수와 종속변수의 비선형 관계를 충분히 고려하기 위해 선형 GPA를 반복적으로 적용하는 방법이다. 본 연구에서 반복기법은 Newton-Raphson 반복기법을 사용하였다.

• 제어로봇시스템학회:학술대회논문집
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• 1992.10a
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• pp.572-577
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• 1992

In this paper, the optimal homing guidance problem is investigated for the general missile/target models described in the state-space. The closed-form solution of the optimal guidance law derived, and its asymptotic properties are studied as the time-to-go goes to infinity or zero. Futhermore, several approximate solutions of the optimal guidance law are suggested for real-time applications.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.8
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• pp.627-636
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• 2021

This paper deals with a study for the guidance control of reusable launch vehicle. For this purpose, modeling of the equation of motion of a reusable launch vehicle with 6 degrees of freedom was performed. With this model, an optimal re-entry path was created and a path-following guidance control simulation was performed to follow the optimal re-entry path. For the design of the path-following guidance controller, the attitude controller applying a time-delay technique that is resistant to modeling uncertainty, disturbance and failure. And the nonlinear path-following guidance law were used. Guidance control simulation using a classical PD controller was performed and compared with the guidance control simulation of a reusable launch vehicle applying a time delay technique.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.33 no.2C
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• pp.192-199
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• 2008

In ultra-wideband (UWB) systems, conventionally, the synchronization is to align time phases of a locally generated template and any of multipath components to within an allowable range. However, the synchronization with a low-power multipath component could incur significant performance degradation in receiver operation (e.g., detection) after the synchronization. On the other hand, the synchronization with a high-power multipath component can improve the performance in receiver operation after the synchronization. Generally, the first one among multipath components has the largest power. Thus, the synchronization with the first path component can make better performance than that with low-power component in receiver operation after the synchronization, Based on which, we first propose an optimal decision rule based on a maximum likelihood (ML) approach, and then, develope a simpler suboptimal decision rule for selecting the first path component. Simulation results show that the system has good demodulation performance, which uses new synchronization definition and the proposed decision rules have better performance than that of the conventional decision rule in UWB multipath channels. Between macroblocks in the previous and the current frame. On video samples with high motion and scene change cases, experimental results show that (1) the proposed algorithm adapts the encoded bitstream to limited channel capacity, while existing algorithms abruptly excess the limit bit rate; (2) the proposed algorithm improves picture quality with $0.4{\sim}0.9$dB in average.

• Proceedings of the Korean Institute of Intelligent Systems Conference
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• 2000.05a
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• pp.150-153
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• 2000

본 논문에서는 퍼지규칙의 수가 적고, 결론부가 선형식으로 표현되는 TSK 퍼지시스템을 이용한다. 본 논문에서 제안되는 적응제어 방법은 규범모델 적응제어 기법을 응용한 것으로 Lyapunov함수를 이용하여 안정성문제를 해결하면서 동시에 최적의 적응법칙을 유도 할 수 있도록 설계되었다. 그리고 역진자 시스템에 대해서 시뮬레이션을 통해 제안된 적응 퍼지제어기의 설계 방법이 유효함을 보인다.

• Journal of the Korea Institute of Military Science and Technology
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• v.11 no.4
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• pp.29-35
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• 2008

In this paper, a new guidance law to reduce sensitivity to the initial heading errors is proposed. In order for shaping the input weights over the flight, we introduce the distribution functions expressed in terms of time-to-go and its inverse term. By applying the optimal control theory with the synthesized weights, the homing guidance law is derived. Also the characteristics of the proposed law are examined. Various computer simulations show the good performance of the proposed guidance.