• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.6
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• pp.448-457
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• 2013

This paper presents the design of an active flutter suppression system for flexible wing using sliding mode control method. The aerodynamic force generated by the motion of a flexible wing control surface is utilized as control force. For this purpose, aeroservoelastic model is formulated by blending aeroelastic model, control surface actuator model, and gust model. A sliding mode controller is designed for active flutter suppression on the aeroservoelastic model in conjunction with Kalman filter that estimates the system states based on the measured output. The performance of the designed controller is demonstrated via numerical simulation for the representative flexible wing model.

• Journal of Navigation and Port Research
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• v.26 no.2
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• pp.193-197
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• 2002

This paper suggests a method to design TSK(Takagi-Sugeno-Kang) fuzzy nonlinear control system for automatic steering system which contains the nonlinear component of ship's maneuvering equation. A TSk fuzzy model can be identified using input-output data and represent a nonlinear system very well. A TSK fuzzy controller can be designed systematically from a TSK fuzzy model because the consequent part of TSK fuzzy rule is a linear input-output equation having a constant term. Therefore, this paper suggests the method identifying the TSK fuzzy model and designing the TSK fuzzy controller based on the TSK fuzzy model for ship steering.

• Journal of Korea Game Society
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• v.11 no.1
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• pp.111-120
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• 2011

It is important to realistically simulate group behaviors of the multi-agents in virtual worlds. While most researchers have focused on their group behaviors in an open space, this paper studies their group behaviors by using steering force in an enclosed space. Agents have a common target and should move towards it in an enclosed space while avoiding collision with other agents. Under those environments, three possible models of agents are proposed and the six steering forces needed in each model are also proposed. In order to show the correctness of the proposed models, they were simulated. Our simulation results showed that the proposed models only using steering forces operate well in the enclosed space although it requires a different period of time for each agent to arrive at its target depending on the walls and doors.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.14 no.4
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• pp.1561-1567
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• 2013

This paper is regarding the helicopter flight control law design for the handling quality performance. MIL-F-83300 and ADS-33E specification is used of the helicopter flight handling quality and to meet these requirements, ACAH type controller is required. This paper described the ACAH type controller design and performance evaluations. Helicopter dynamics first developed as nonlinear dynamics including rotor dynamics and then linear model was extracted from hovering to forward flight mode using trim condition. Control law used the model following to meet the handling qualities, the simple inverse model as feed forward gain, decoupling logic and phase model to decouple the axes, and linear model to calculate the coefficients. Handling quality evaluation used the matlab based Conduit tool and verified that Level 1 requirement is satisfied.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2021.11a
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• pp.187-188
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• 2021

한국해양대학교 실습선 한나라호와 시뮬레이터 모델 선박의 제원에 따른 선회권을 비교하여 선박 제원에 따른 선회권을 분석하고, 시뮬레이터의 모델 선박을 사용하여 실제 선박의 선회 성능 및 조종 성능 평가 시 두 선박의 제원 확인에 대한 중요성을 제시한다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2011.06a
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• pp.359-361
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• 2011

예선이 부선을 선미예인하고 있는 상황에서의 예부선 조종특성을 확인하기 위하여, 예부선 통합 실선시운전 시험을 수행하였다. 부선을 예인하는 상황에서의 저항시험, 가감속시험, 좌현/우현 10도 선회시험, 좌현/우현 20도 선회시험, 부선 선수동요각을 기준으로 하는 10도 지그재그시험, 20도 지그재그 시험을 통하여 다양한 상황에서의 예선과 부선의 운항 특성을 확인하였다. 본시험 결과는 향후 예부선의 자유항주 모형시험 결과와 함께, 예부선의 통합운항을 모사하는 수학모델 검증에 사용될 예정이다.

• Proceedings of the Korean Information Science Society Conference
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• 2005.07b
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• pp.553-555
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• 2005

본 논문은 모든 항전장비 가운데서도 조종사의 신속한 상황인식과 수많은 정보의 처리를 위하여 지속적으로 발전이 이루어지고 있는 조종석 디스플레이 시스템의 개량형 설계를 제안한다. 현재 항공기 조종석 시스템은 아날로그식 계기판과 함께 다수의 2-D 컬러 디스플레이를 배열한 모델을 사용하고 있다. 본 논문에서 차세대 조종석을 위해 제안하는 시스템은 미공군에서 개발 중인 방식을 도입하여 3-D와 2-D를 흔용한 소수의 대형 디스플레이로 디지털 신호만을 사용한 시스템에 OLED(Organic Light Emitting Diodes) 소자를 적용한 것이다. 이 시스템은 상용칩을 수용한 고성능의 컴퓨터 시스템을 이용하여 초당 50,000개의 3-D triangle을 최신화하여 밝은 지형과 어두운 지형 투명도, 지형특성, 비가시적 지형을 시현한다. 본 설계의 구현을 통하여 고성능의 신호 집약적 시스템 설계의 우수성과 차세대 소자로 각광받는 OLED 디스플레이 채택을 통한 디스플레이 시스템 상의 가시도 향상 및 중량감소 등의 효과가 있어 조종석 디스플레이 시스템의 실용도가 개선들 수 있음을 제안하였다.

• Proceedings of the Computational Structural Engineering Institute Conference
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• 2010.04a
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• pp.488-491
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• 2010

본 논문에서는 돌풍응답경감제어 효과 검증을 위한 풍동시험에 사용될 유연날개에 대해 공탄성 모델, 조종면 작동기 모델, 돌풍 모델 등으로 구성되는 서보공탄성 모델링을 수행하였으며, 이에 대한 연속돌풍 응답해석을 수행하여 상용 Solver를 이용한 해석결과와 비교하여 구성된 서보공탄성 모델을 검증하였다. 또한, 유연날개의 돌풍응답을 경감하는 조종면 제어기를 설계하고, 이에 대한 수치 시뮬레이션을 수행하여 돌풍응답 경감효과를 검증하였다.

• Aerospace Engineering and Technology
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• v.5 no.2
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• pp.240-247
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• 2006

Tilt rotor aircraft is a multi-configuration airplane which has three independent flight modes; helicopter, conversion, and aiplane. The control surface mixer resign is reqctired to generate and distribute efficient control forces and moments in each flight mode. In the conversion mode, the thrust vector is changed from helicopter mode to airplane, therefore the thrust vector makes undesired forces and moments which affect on pitch, roll and yaw dynamics. This paper describes the design results of control surface mixer design which minimize the undesired forces and moments due to nacelles tilting angle change for 4O% scaled model.

• Journal of the Korean Institute of Navigation
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• v.15 no.4
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• pp.27-39
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• 1991

One practical method has already been proposed for predicting the characteristics of ship manoeuvring motions at relatively high advance speed [19]. Howeverf, this method can hardly be applied to motions of ships in starting, stopping, backing and slow steaming conditions, even though such extensive motions are of vital importance from a safety point of view particularly in harbour areas. The method presented here aims at predicting the characteristics of ship manoeuvring at low advance speed, which covers starting, stopping, backing and slow steaming conditions. The force mathematical models at large angles of incidence to the hull as well as under the wide range of propeller operations are formulated. Simulations of various manoeuvres at low advance speed are carried out for two types of merchant ship, I.e. a LNGC and a VLCC. Comparisons between simulations and corresponding full-scale measurements [10], [15] or free-running model tests [6],[10] provide a first verification of the proposed mathematical models.