• 제어로봇시스템학회논문지
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• 제14권9호
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• pp.916-924
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• 2008

In this paper dynamic modeling parameters were estimated using a frequency domain estimation method. A systematic flight test method was employed using preprogrammed multistep excitation of the swashplate control input. In addition when one axis is excited, the autopilot is engaged in the other axis, thereby obtaining high-quality flight data. A dynamic model was derived for a small scale unmanned helicopter (CNUHELI-020, developed by Chungnam National University) equipped with a Bell-Hiller stabilizer bar. Six degree of freedom equations of motion were derived using the total forces and moments acting on the small scale helicopter. The dynamics of the main rotor is simplified by the first order tip-path plane, and the aerodynamic effects of fuselage, tail rotor, engine, and horizontal/vertical stabilizer were considered. Trim analysis and linearized model were used as a basic model for the parameter estimation. Doublet and multistep inputs are used to excite dynamic motions of the helicopter. The system and input matrices were estimated in the frequency domain using the equation error method in order to match the data of flight test with those of the dynamic modeling. The dynamic modeling and the flight test show similar time responses, which validates the consequence of analytic modeling and the procedures of parameter estimation.

• Journal of Mechanical Science and Technology
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• 제17권5호
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• pp.654-667
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• 2003

This paper presents a consequence of the systematic approach to identify the aerodynamic parameters of an unmanned aerial vehicle (UAV) 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 high-quality 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.

• 한국건설관리학회:학술대회논문집
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• 한국건설관리학회 2007년도 정기학술발표대회 논문집
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• pp.977-982
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• 2007

건설자동화 장비의 개발에 있어서 주변 사물을 인식하고 효과적으로 모델링하기 위한 노력은 지속적으로 이루어져 왔다. 이 연구는 지능형 굴삭 로봇 개발의 요소기술로서, 3D 레이저 스캐너를 이용하여 토공 작업환경을 3차원으로 모델링하고, 객체화된 모델링 정보를 이용하여 지능적인 작업 계획을 수립하기 위한 기반 연구이다. 이 연구에서는 먼저 3D 레이저 스캐너의 시장 동향을 분석하였고 토공 작업환경을 대상으로 3D 레이저 스캐너의 성능을 비교 분석하여 토공 현장에서 적합한 3D 레이저 스캐너를 선정하였다. 그리고 3D 모델링 시스템의 하드웨어 구서을 제시하였고 전체 소프트웨어의 컨셉을 설계하였다. 다음으로 소프트웨어 상세 기능 설계 및 사용자 인터페이스 설계를 통해 향후 photogrammetry 및 객체인식 기술의 적용을 위한 프레임워크를 구축하였다. 이 연구에서는 실제 토공현장을 대상으로 개발된 소프트웨어와 토탈 스테이션을 이용하여 타겟간의 상대거리를 측정하고 3D 모델링 시스템의 정확성을 측정하였다.