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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.
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.
김종섭(Chong-Sup Kim),고기옥(Gi-Oak Koh),지창호(Chang-Ho Ji),조인제(In-Je Cho),이동규(Dong-Kyu Lee) 한국항공우주학회 2015 韓國航空宇宙學會誌 Vol.43 No.8
전투기는 공대지 및 공대공 전투임무를 위한 다양한 외부 무장형상으로 운용된다. 무장발사로 인한 비대칭 무장형상에서는 조종사가 롤트림 입력을 인가하여 수평비행을 유지한다. 그러나 외란이 있는 실제 비행 중에는 수평비행을 위해 정확한 롤트림 입력을 인가할 수 없다. 이러한 상태에서 자동비행시스템 인가 시에는 부정확한 롤트림 명령의 영향으로 롤자세각 오차가 발생하여 롤축 자동비행시스템의 성능을 저하시킨다. 본 논문에서는 이러한 문제를 해결하기 위해 롤축 자동비행시스템 명령 단에 적분기를 설계하여 롤자세각의 정상상태 오차를 제거하였다. 또한, 롤자세각 오차량을 제한하는 제한기를 비행영역에 따라 스케줄링하여 초기 과도응답을 개선하였다. 시뮬레이션 평가한 결과, 설계된 비행제어법칙은 부정확한 롤트림 상태에서 자동비행시스템을 운용 시에 롤자세각 추종 성능을 개선함을 확인할 수 있었다. The fighter aircraft uses several different loading configurations for air-to-surface and air-to-air combat missions. To maintain wings-level flight with an asymmetric weapon configuration, a pilot controls a roll trim system. However, it is difficult to apply an accurate roll trim input for wings-level flight in the actual flight under disturbance. The inaccurate roll trim input degrades the performance of the roll autopilot system. In this paper, to solve this problem, an integrator was additionally designed in the command part of the roll autopilot system. The initial transient response was improved by scheduling the limiter to restrict the roll attitude error. As a result of the evaluation of the simulation for the designed flight control law, the roll attitude following performance was found to be improved in the autopilot system operation under the inaccurate roll trim condition.
김종섭(Chong Sup Kim),배명환(Myung-whan Bae),황병문(Byung Moon Hwang),고기옥(Gi-oak Koh),강철(Cheul Kang),성덕용(Duck Yong Sung) 대한기계학회 2004 대한기계학회 춘추학술대회 Vol.2004 No.11
An advanced method of Relaxed Static Stability (RSS) is utilized for improving the aerodynamic performance of modern version supersonic jet fighter aircraft. The laws of flight control system utilize RSS criteria in both longitudinal and lateral-directional axes to achieve performance enhancements. Particularly, the design of longitudinal control laws for utilizing RSS methods greatly affects the performance of the aircraft in Air-to-Air Tracking and Air-to-Ground modes, which improves weapon delivery. In the area of Airto-Air Tracking, the development of longitudinal control laws aids in the fine tracking and gross acquisition of other aircraft. This paper proposes that Air-to-Air fine tracking can be improved via RSS control law design methods without effecting Air-to-Air gross acquisition.
상호작용 다중모델-무향 칼만필터 기반 공대공 기관포 정밀 타격 성능 향상 기법에 관한 연구
한승우(Seung-woo Han),김종섭(Chong-sup Kim),고기옥(Gi-oak Koh),고상호(Sang-ho Ko) 한국항공우주학회 2023 韓國航空宇宙學會誌 Vol.51 No.3
본 논문에서는 공대공 근접 교전 상황에서 기관포의 정밀 타격 성능 향상을 위한 신호처리 기법에 관한 연구를 수행한다. 목표 항공기의 상태 추정 시 단일모델을 사용한 경우와 다중모델을 병렬로 사용한 경우 발생하는 추정 오차를 비교하고 분석한다. 결과적으로 상호작용 다중모델 기법과 무향 칼만필터를 활용하여 기동하는 목표 항공기의 상태를 추정한다. 또한 목표 항공기의 정밀 타격을 위한 가상추적점 생성 기법을 제안한다. 가상추적점을 추종하기 위한 비행제어시스템을 구현하고 기관포를 활용한 목표 항공기 정밀 타격 시뮬레이션을 수행하여 임무 수행 능력과 생존성 향상을 확인한다. This paper describes a signal processing technique to improve the precision aiming performance in close range air-to-air combat. We compare and analyze the state estimation error that occurs when a single model is used or multiple models are used parallel. As a result, the state of the target aircraft is estimated using Interactive Multiple Model method and Unscented Kalman Filter. Also a method to generate virtual pursuit point (VPP) for precision aiming is proposed. Finally, the flight control system is designed to pursuit VPP and close range air-to-air pursuit simulation is performed to evaluate the mission performance and viability.