• 항공우주시스템공학회지
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• 제15권4호
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• pp.75-84
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• 2021

A novel robot-operating-system-based flight and mission state communication node for X-Plane 11 flight control simulation environments and its simulation results were discussed. Although the proposed communication method requires considerable implementation steps compared with the conventional MATLAB/Simulink-based User Datagram Protocol (UDP) block utilization method, the proposed method enables a direct comparison of cockpit-view images captured during flight with the flight data. This comparison is useful for data acquisition under virtual environments and for the development of flight control systems. The fixed/rotary-wing and ground terrain elements simulated in virtual environments exhibited excellent visualization outputs, which can overcome time and space constraints on flight experiments and validation of missionary algorithms with complex logic.

• 한국항공우주학회지
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• 제35권9호
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• pp.783-791
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• 2007

FAA AC 120-63 등급 C 또는 FTD 등급 5에 규정된 헬리콥터 모의 비행 훈련장치에 사용될 단일 로터 회전익기의 수학적 모델에 대해 고찰하였다. 선정된 비행 운동 모델의 비행 운동 성능 평가를 통해서 그 유용성을 파악하였다. 이로부터 훈련은 물론 조종 성능시험이 가능한 비행 훈련장치 개발을 통해서 헬리콥터 비행성 평가를 위한 모의 비행 시험환경을 구현하였다.

• International Journal of Aeronautical and Space Sciences
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• 제9권1호
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• pp.162-168
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• 2008

A design objective for variable stability flight control system is to develop a controller of in-flight simulation capability that forces the aircraft being flown to follow the dynamics of other aircraft. This paper presents a model-following variable stability control system (VSS) for in-flight simulation which consists of feedforward and feedback control laws, the aircraft dynamic model to be simulated, and switching and fader logics to reduce the transient effect between two aircraft dynamics. The separate design techniques for feedforward and feedback control law proposals are based on model matching and augmented linear quadratic (LQ) techniques. The system allows pilots to select and engage VSS mode, and when deselected, the aircraft reverts to the baseline flight control system. Both the baseline flight control laws and VSS control laws are computed continuously during flight. Initialization of the state values are necessary to prevent instability, since VSS control laws have integrators and filters in longitudinal, and lateral/directional axes. This paper demonstrates and validates the effectiveness and quality of VSS with F-16 models embedded in T-50 in-flight simulation aircraft.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.513-520
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• 2004

A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.

• 한국시뮬레이션학회:학술대회논문집
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• 한국시뮬레이션학회 2001년도 The Seoul International Simulation Conference
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• pp.147-151
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• 2001

Based on flight software modeling experiences on satellite simulator developments so far, three different approaches for modeling the flight software within the satellite simulator such as utilization of a processor emulator executing the actual flight software image, re-compilation of the flight software sources within the simulator infrastructure, and development of a set of abstract models representing the required flight software functionality are presented.

• 한국시뮬레이션학회논문지
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• 제10권4호
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• pp.31-40
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• 2001

The flight simulator should be made like a actual flight. For the scene of sight, instrument should show the condition of flight and the pilot should catch the altitude, speed, pose and rate of lift of the airplane. This paper describes visual training program of driving airplane in practice. It is for beginners using joystick in PC, implements airplane physical equations. Flight simulator in it implements airplane panel parts in order to make simple modeling, And it uses rendering technology to implement vision parts of panel. It uses double buffering In make it faster and more efficient..

• 한국항행학회논문지
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• 제22권1호
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• pp.13-19
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• 2018

본 논문에서는 저고도 무인기 교통관리 체계에서 운용될 무인기의 사용 용도별로 비행패턴을 분석하였고, 시뮬레이션 모형을 개발하였다. 무인기 비행패턴은 감시형, 선회형, 배송형 패턴으로 분류하였으며, 무인기 사용 용도별로는 농업, 시설 점검, 공공안전 및 보안, 물품 배송으로 총 네 가지 경우를 고려하였다. 또한 저고도 무인기 교통관리 체계에 적용할 공역 운용방식을 검증하기 위한 도구로써 시뮬레이션 모형을 개발하였다. 개발된 시뮬레이션 모형을 감시형 비행패턴에 적용해 보았으며, 그 결과 정해진 입력을 받아 주어진 비행패턴을 그리며 비행하는 것을 확인 및 검증하였다. 본 시뮬레이션 모형은 향후 무인기가 다양한 비행패턴을 그리며 해당 용도에 맞게 안전하고 효율적으로 운항할 수 있는지 검증하는데 사용될 예정이다.

• 한국항공우주학회지
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• 제37권6호
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• pp.602-608
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• 2009

IEEE(Institute of Electrical and Electronics Engineers)1516 에 규정된 HLA(High Level Architecture) 기반 기술은 상이한 목적으로 개발된 다수의 개별 시뮬레이션들이 결합된 복합 시뮬레이션 네트워크 시스템을 구성하는데 있어서 필수적 요소이다. 본 논문에서는 상용 비행 시뮬레이션을 HLA를 기반으로 구현하는 과정과 구현된 시스템의 동작 과정을 보여줌으로써 확장성 및 상호 운용성을 갖춘 비행 시뮬레이션 모델 구조를 제시하였다. 또한 HLA를 기반으로 구현된 실시간 시뮬레이션 시스템과 상용 비행 시뮬레이션을 비교하여 얻어진 비행 정보 데이터 분석을 통해 완벽한 실시간성을 보장할 수 있는 지에 대한 여부를 판단하였다.

• 항공우주시스템공학회지
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• 제9권4호
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• pp.49-54
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• 2015

Accurate aerodynamic data is required for the flight simulation or control logic design of aircraft. The aerodynamic look-up table has been used widely to provide aerodynamic forces and moments for given flight conditions. In this paper, we replace the aerodynamic look-up table with real-time aerodynamic model which calculates aerodynamic forces and moments of quasi-steady flow directly for given flight conditions and control surface deflections. Flight simulations are conducted for the low-speed small UAV using real-time aerodynamic model, and responses of the UAV are predicted successfully for inputs of control surfaces.

• 대한기계학회논문집A
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• 제26권8호
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• pp.1487-1494
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• 2002

In this study, to propose the prediction method of the crack growth under flight-simulation loading, crack growth tests are conducted on 2124-7851 aluminum alloy specimens. The prediction of crack growth under flight-simulation loading is performed by the stochastic crack growth model which was developed in previous study. First of all, to reduce the complex load history into a number of constant amplitude events, rainflow counting is applied to the flight-simulation loading wave. The crack growth, then, is predicted by the stochastic crack growth model that can describe the load interaction effect as well as the variability in crack growth process. The material constants required in this model are obtained from crack growth tests under constant amplitude loading and single tensile overload. The curves predicted by the proposed model well describe the crack growth behavior under flight-simulation loading and agree with experimental data. In addition, this model well predicts the variability of fatigue lives.