• 제어로봇시스템학회논문지
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• 제6권11호
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• pp.995-1002
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• 2000

In this paper, fuzzy logic controllers(FLC) are designed for control of flight. For tuning FLC, we used adaptive evolutionary algorithms(AEA) which uses a genetic algorithm(GA) and an evolution strategy (ES) in an adaptive manner in order to take merits of two different evolutionary computations. We used AEA to search for optimal settings of the membership functions shape and gains of the inputs and outputs of FLC. Finally, the proposed controller is applied to the high-angle-of-attack flight system for a supermaneuverable version of the f-18 aircraft and compares with other methods.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.519-524
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• 2003

In this report, a longitudinal adaptive flight control law is presented for the automatic landing system of a Japanese automatic landing flight experiment vehicle (ALFLEX). The longitudinal adaptive flight control law is designed to track an output of the vehicle to a guidance signal from the guidance portion of the automatic landing system. The proposed adaptive control law in the attitude control portion adjusts the controller gains continuously online as flight conditions change, in spite of the existence of unmodeled dynamics. The number of the controller gains to be adjusted is decreased to 1/2 from the previous studies. Computer simulation involving six-degree-of-freedom (DOF) nonlinear flight dynamics is performed to examine the effectiveness of the proposed adaptive control law. In order to verify the influence of the dispersion of the initial conditions, the Monte Carlo simulation is also applied. The initial conditions are more widely dispersed than the previous studies. As a result, except under the unsuitable initial conditions, the ALFLEX successfully landed on the runway.

• 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.

• 제어로봇시스템학회논문지
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• 제9권4호
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• pp.329-339
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• 2003

A neural network based adaptive controller design method is proposed for reconfigurable flight control systems in the presence of variations in aerodynamic coefficients or control effectiveness decrease caused by control surface damage. The neural network based adaptive nonlinear controller is developed by making use of the backstepping technique for command following of the angle of attack, sideslip angle, and bank angle. On-line teaming neural networks are implemented to guarantee reconfigurability and robustness to the uncertainties caused by aerodynamic coefficients variations. The main feature of the proposed controller is that the adaptive controller is designed with assumption that not any of the nonlinear functions of the system is known accurately, whereas most of the previous works assume that only some of the nonlinear functions are unknown. Neural networks loam through the weight update rules that are derived from the Lyapunov control theory. The closed-loop stability of the error states is also investigated according to the Lyapunov theory. A nonlinear dynamic model of an F-16 aircraft is used to demonstrate the effectiveness of the proposed control law.

• 한국항공우주학회지
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• 제34권7호
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• pp.45-54
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• 2006

일반적인 항공 촬영용 무인비행선은 GIS 데이터를 획득하기 위하여 기체 조종사와 영상 장치 조종사가 필요하며, 좋은 영상을 위해서는 이들의 호흡과 정확한 위치로의 이동이 중요하다. 본 논문에서는 이런 인력의 소요를 줄이고 정확한 위치/고도의 사전 계획된 비행경로를 자동비행하는 11m급 무인비행선의 고전제어 기반의 자동비행 제어법칙을 소개한다. 또한 이를 검증하기위해 실시한 비행시험의 각 단계별 절차와 유의사항, 외란에 의한 추종 오차를 줄이는 LOS 가이던스 알고리즘을 제시하고 비행시험 결과를 통한 게인 튜닝절차를 소개한다.

• International Journal of Control, Automation, and Systems
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• 제3권2호
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• pp.217-224
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• 2005

Generally, the underwater flight vehicle (UFV) depth control system operates with the following problems: it is a multi-input multi-output (MIMO) system because the UFV contains both pitch and depth angle variables as well as multiple control planes, it requires robustness because of the possibility that it may encounter uncertainties such as parameter variations and disturbances, it requires a continuous control input because the system that has reduced power consumption and acoustic noise is more practical, and further, it has the speed dependency of controller parameters because the control forces of control planes depend on the operating speed. To solve these problems, an adaptive fuzzy sliding mode controller (AFSMC), which is based on the decomposition method using expert knowledge in the UFV depth control and utilizes a fuzzy basis function expansion (FBFE) and a proportional integral augmented sliding signal, is proposed. To verify the performance of the AFSMC, UFV depth control is performed. Simulation results show that the AFSMC solves all problems experienced in the UFV depth control system online.

• International Journal of Aeronautical and Space Sciences
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• 제10권2호
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• pp.12-22
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• 2009

This paper deals with the State-Dependent Riccati Equation (SDRE) Technique for the design of rotorcraft waypoint guidance. To generate the flight trajectory through multiple waypoints, we use the trigonometric spline. The controller design and its validation is based upon a level 2 simulation rotorcraft model and the designed SDRE controller is applied to the trajectory tracking problems. To verify the designed guidance law, the simulation environment of high fidelity rotorcraft model is developed using three independent PCs. This paper focuses on the validation of rotorcraft waypoint guidance law which is designed by using SDRE Controller.

• 한국항공우주학회지
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• 제42권10호
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• pp.851-857
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• 2014

본 논문에서는 무인기의 다양한 비행모드 중 자동선회 모드의 확장을 위해 자동 장주비행 모드 (auto race-track mode)와 8자 비행모드 (Figure 8 mode)를 구현하기 위한 알고리즘과 비행로직을 제안하고, 이에 대한 시뮬레이션 평가를 수행하여 제안된 비행모드의 검증을 수행하였다. 일반적으로 자동선회 모드는 지정된 선회반경을 유지하는 원선회 비행 (circle flight)을 지칭하게 되는데, 자동 장주비행 모드와 8자 비행 모드를 구현하게 되면 이착륙 안정성 증대와 수행 임무영역을 확장할 수 있게 된다. 이러한 자동 장주비행 모드와 8자 비행모드의 구현을 위한 알고리즘과 비행체의 위치 및 선회방향에 관계없이 비행모드를 구성할 수 있는 비행로직 구현을 정리하였으며, 제안된 알고리즘과 비행로직의 검증을 위해 중형급 무인기를 대상으로 시뮬레이션을 수행하였다.

• 한국항행학회논문지
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• 제11권2호
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• pp.137-145
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• 2007

본 논문에서의 ADS-B 비행시험은 CDTI상에 목적고도가 제공될 경우 항공교통관제사 및 조종사에게 운영상 어떠한 효과가 있는지를 실증하고자 시행되었다. 또한 이 비행시험은 현 항공교통관제업무 환경에서 ADS-B 운영시험을 하는 최초의 연구이자 향후 우리나라에 ADS-B의 배치를 고려하기 전에 운영상의 실질적인 정보를 제공하기 위한 연구이다. 비행시험을 위해 ADS-B 장비가 탑재된 H 대학교의 항공기 2대가 이용되었고, 충남 태안소재 태안비행장에 지상국이 구축되어, 기 설정된 비행절차에 따라 비행시험이 수행되었다. ADS-B 비행시험 결과 통신주파수 사용횟수 및 주파수 점유시간이 기존의 시스템에 비해 현저하게 줄어듦을 확인하였고, 따라서 항공교통관제사의 업무량(workload) 뿐만 아니라 조종사의 상황인식도 뚜렷하게 개선되어짐을 확인할 수 있었다.

• 제어로봇시스템학회논문지
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• 제10권2호
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• pp.125-130
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• 2004

This paper describes an approach for synthesizing a Fuzzy Logic Controller(FLC) that combines the benefits of fuzzy logic control and fuzzy logic gain scheduling for the F/A-18 aircraft. Specially, fuzzy rules are utilized on-line to determine the denoralization factor(Κ) of a feedback fuzzy controller based on the dynamic pressure(Q) indicateing the region of the flight envelop the aircraft is operating in. Simulation results demonstrate that the proposed FLC provides excellent compensation for time-varying and/or nonlinear characteristics of the aircraft, and that it also exhibits satisfactory robustness with noisy air data sensors.