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- 저자 : 김종섭(Byung-soo Kim) (검색결과 2 건)
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고기동 전투기 세로축 제어법칙 설계 및 비행성 파라미터 최적화에 관한 연구
김종섭(Byung-soo Kim),양인석(Inseok Yang),고기옥(Gi-oak Koh),김병수(Byung-soo Kim) 제어로봇시스템학회 2018 제어·로봇·시스템학회 논문지 Vol.24 No.8
Flight control law design aims to determine the optimal flying qualities and ensure the stability of aircraft for all mission task elements (MTE) over the entire flight envelope. Numerous control law design criteria offer guidance in the control law development process, and representative aircraft design criteria are presented in MIL-STD-1797 and MIL-DTL-9490E. This paper describes three design methods to optimize flying quality parameters in INDI (Incremental Nonlinear Dynamic Inversion) control based on the T-50 Advanced Supersonic Trainer aircraft model. In the first method, flying quality parameters are optimized to meet the flying-quality as a design goal. In the second method, flying quality parameters are optimized to have flying quality and stability margin, such as the gains and phase margins, as a design goal. In the last method, a lead-compensation filter is added at the feedback stage of the angular acceleration to improve the stability margin and then, flying quality parameter is re-optimized with the above second optimization method. The results of the design and evaluation show that the second and third optimization methods are better than the first, achieving level 1 flying quality and guaranteeing the aircraft’s stability.
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고기동 전투기에 적합한 모델/센서기반 비선형 동적 모델역변환 제어 기법 개발
김종섭(Chong-sup Kim),양인석(Inseok Yang),고기옥(Gi-oak Koh),김병수(Byung-soo Kim) 제어로봇시스템학회 2018 제어·로봇·시스템학회 논문지 Vol.24 No.7
This paper evaluates the flying qualities and stability of the nonlinear dynamic inversion (NDI) control law, in which angular acceleration is analyzed by a mathematical model or measured by an angular acceleration sensor based on the T-50 Advanced Supersonic Trainer model. The NDI has been considered the suitable nonlinear control technique for fighter aircrafts in aerospace industries, since it replaces nonlinear characteristics with the user-defined desired dynamics by inverting the original plant dynamics. To obtain the angular acceleration of the aircraft, two approaches are considered in this paper: estimating from the analytic model (model-based) or measuring from the angular acceleration sensor (sensor-based). To evaluate the robustness of the model-based or sensor-based NDI, the sensitivity analyses with model uncertainties and wide Center-of-Gravity (CG) travel situations are considered. The evaluation results of flying qualities and stability show that the sensor-based NDI considerably degrades the stability margin and pitch equivalent time delay compared with model-based NDI. However, it has the advantages of decreasing the inter-axes coupling effects and improving the robustness throughout the overall flight envelope.
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