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안정성증강 작동기와 트림 작동기를 이용한 헬리콥터 자세명령반응타입 제어시스템 설계
김응태,최인호,현정욱,Kim, Eung Tai,Choi, Inho,Hyun, JeongWook 한국항공운항학회 2013 한국항공운항학회지 Vol.21 No.4
Attitude command response type required for enhanced handling qualities of helicopter can be implemented by mechanical automatic flight control system with SAS actuators which have limited authorities. However, the early saturation of SAS actuator hinders the helicopter from following the attitude command for large stick command. Auto-trim controller can delay SAS actuator's saturation by utilizing trim actuators and allows the attitude command response type for larger stick command. This paper describes the control law for limited authority system of helicopter with auto-trim. Limited authority system is applied to BO-105 linear dynamic model and simulation is performed along with handling quality analysis.
안정성증강 작동기를 이용한 Fly-By-Wire 헬리콥터 제어법칙 설계에 대한 연구
김응태,최인호,Kim, Eung-Tai,Choi, In-Ho 한국항공운항학회 2015 한국항공운항학회지 Vol.23 No.1
The previous limited authority system capable of implementing attitude command response type and translational command response type by operating SAS actuator has the problem of early saturation of SAS actuator since SAS actuator should compensate the mechanical linkage displacement caused by control sick movement. In this paper, a limited authority system where flight control computer receives the command from the control stick which is not connected to the mechanical linkage is described. In this system the compensation by the SAS actuator is not necessary and SAS actuator saturate later. SAS actuator saturation problem can be further relaxed by using the trim actuator. This new limited authority system is applied to BO-105 model, simulation is performed for the doublet input and pirouette maneuver is also simulated and analyzed.
민간항공기 디지털 Fly-By-Wire 시스템 기술 개발 동향
김응태(Kim Eung-Tai),장재원(Chang Jae-Won),최형식(Choi Hyoung-Sik),이석천(Lee Sugchon) 한국항공우주연구원 2009 항공우주산업기술동향 Vol.7 No.2
전투기에 처음 적용되었던 Fly-By-Wire (전자식 비행제어) 시스템은 여러 가지 장점으로 인해 까다로운 인증과정을 거쳐 민간 항공기에까지 적용되었고, 최근에는 소형제트기까지 적용 범위가 확장되고 있으며 미래에는 대부분 Fly-By-Wire 항공기가 주를 이룰 것으로 전망된다. 본 논문에서는 대형여객에서 소형제트기까지 민간 항공기에 적용되는 Fly-By-Wire 시스템의 구성 및 특성등에 대하여 기술 하였다. 특히 비행조종컴퓨터 다중화 방안과 데이터 통신 버스, 조종면 작동기, Fly-By-Wire 시스템을 통하여 적용되는 제어 법칙 등에 대한 기술 개발 동향에 대해 고찰하였다. The Fly-By-Wire system was first applied to the fighter and its inherent advantages lead to the advent of the Fly-By-Wire civil aircraft. Recently even the small jet aircraft shows the trend of adopting the Fly-By-Wire system. In the future, most of the aircraft are expected to be the Fly-By-Wire type. In this paper, the structure and the characteristics of the Fly-By-Wire system applied to the civil aircraft was described. The development trend of the redundant method of the flight control system, data communication system, control surface actuation system and the control laws implemented by the Fly-By-Wire system of the civil aircraft are discussed.
김응태 ( Eung Tai Kim ),성기정 ( Kie Jeong Seong ),( Matthias Cremer ),( Damian Hischier ) 한국항공운항학회 2010 한국항공운항학회지 Vol.18 No.4
The main purpose of this study is to obtain linear models for the design of automatic flight controller in order to operate the Light Sport Aircraft as unmanned air vehicle. Flight test equipments installed on the aircraft to acquire flight test data are described and maneuvers for practical speed calibration are introduced. Parameters for the linear models of lateral and longitudinal motion are estimated by the Output error method as well as trim data analysis using the flight test data. Simulated data using the estimated parameters is shown to agree well with the measurement data. Estimated parameters obtained for several flight conditions can be used to improve the aerodynamic database of the simulation program.