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Jinyoung Suk,Youngsaeng Lee,Seungjoo Kim 대한기계학회 2003 JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY Vol.17 No.5
This paper presents a consequence of the systematic approach to identify the aerodynamic parameters of an unmanned aerial vehicle (UA V) equipped with the automatic flight control system. A 3-2-1-1 excitation is applied for the longitudinal mode while a multi-step input is applied for lateral/directional excitation. Optimal time step for excitation is sought to provide the broad input bandwidth. A fully automated programmed flight test method provides highquality flight data for system identification using the flight control computer with longitudinal and lateral/directional autopilots, which enable the separation of each motion during the flight test. The accuracy of the longitudinal system identification is improved by an additional use of the closed-loop flight test data. A constrained optimization scheme is applied to estimate the aerodynamic coefficients that best describe the time response of the vehicle. An appropriate weighting function is introduced to balance the flight modes. As a result, concurrent system models are obtained for a wide envelope of both longitudinal and lateral/directional flight maneuvers while maintaining the physical meanings of each parameter.
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Ground Test and Evaluation of a Flight Control System for Unmanned Aerial Vehicles
Jinyoung Suk,Jinhyung Kim 한국항공우주학회 2004 International Journal of Aeronautical and Space Sc Vol.5 No.1
UAV(Unmanned Aerial Vehicle) has become one of the most popular military/commercial aerial robots in the new millennium. In spite of all the advantages that UAVs inherently have, it is not an easy job to develop a UAV because it requires very systematic and complete approaches in full development envelop. The ground test and evaluation phase has the utmost importance in the sense that a well-developed system can be best verified on the ground. In addition, many of the aircraft crashes in the flight tests were resulted from the incomplete development procedure. In this research, a verification procedure of the whole airborne integrated system was conducted including the flight management system. An airborne flight control computer(FCC) senses the external environment from the peripheral devices and sends the control signal to the actuating system using the assigned control logic and flight test strategy. A ground test station controls the mission during the test while the downlink data are transferred from the flight management computer using the serial communication interface. The pilot control box also applies additional manual actuating commands. The whole system was tested/verified on the wind-tunnel system, which gave a good pitch control performance with a pre-specified flight test procedure. The ground test system guarantees the performance of fundamental functions of airborne electronic system for the future flight tests.
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Longitudinal System Identification of an Avian-Type UAV Considering Characteristics of Actuator
Hakseong Gim,ByoungJu Lee,Jaeyeon Huh,Seungkeun Kim,JinyoungSuk 한국항공우주학회 2018 International Journal of Aeronautical and Space Sc Vol.19 No.4
To develop autonomous flapping aircraft, basic mathematical modeling is essential to solve the problem of “uncertainty models” in biomimetic flight dynamics. This study identified the longitudinal linear model of an ornithopter via automated flight tests and sensors onboard the ornithopter to measure angular rates, Euler angles, and total velocity. For accurate flight tests, automated signal input was designed for elevator deflection: doublet and multistep 3211 maneuver. Furthermore, because the flapping motion of the ornithopter’s main wings generates oscillations during cruise flight, fast Fourier transform is used to analyze flight data in the frequency domain, and a Butterworth filter is used to filter out the flapping motion from the data. The characteristics of the actuator are then analyzed using a motion capture camera and applied to the system identification. The structure of the ornithopter linear model is found to be similar to that of a fixed-wing aircraft, which has a periodic oscillation. The results from the flight tests and analysis manifest that an ornithopter has unstable characteristics due to a single right-half plane real pole.
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