• 제어로봇시스템학회논문지
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• 제14권5호
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• pp.502-510
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• 2008

UAVs(Unmanned Aerial Vehicles) have many applications in military and commercial areas. The flight control system of UAVs is more important than manned aircraft's because the mission of UAVs must be operated without a human pilot. But very heavy and expensive navigation system makes it difficult to develop UAV flight control system. In this research, GPS/IMU integrated navigation filter was developed for light weight/low cost flight control system of small UAVs. With this navigation filter, full flight control system which has real time operating capability has been developed. The performance of the flight control system is basically checked by HILSIM (Hardware In the Loop SIMulation). Finally, the flight control system is verified by showing performance test result under real flight environment.

• 한국항공우주학회지
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• 제33권11호
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• pp.80-87
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• 2005

T-50 훈련기에 탑재되어 있는 전기식 비행제어계통 (Digital fly-by-wire flight control system)은 통합 다기능 감지기(IMFP : Integrated Multi-Function Probe)를 이용하여 항공기의 고도/속도/받음각 정보를 획득한다. T-50에는 3개의 IMFP가 장착되어 있으며, 이는 제어법칙에 3중의 소스를 제공한다. IMFP로부터 제공된 3개의 공기 정보는 중간 값을 채택하여 보다 신뢰성 있는 정보를 제어법칙에 제공한다. 고고도 초음속 비행시험 결과, 초음속 영역에서 발생하는 항공기 충격파(Shock wave)의 영향으로 인해 IMFP에서 측정되는 공기정보에 일시적으로 오차가 발생하였다. 이러한 오차정보는 항공기의 안정성에 영향을 미칠 수 있으며, 특히 저고도영역에서 이러한 오차정보가 제어법칙에 제공되어 질 경우, 항공기의 안전성에 영향을 미칠 수 있다. 본 논문에서는 저고도 초음속 영역에서, IMFP 오차정보로 인하여 발생할 수 있는 비행안정성 및 조종성(Controllability)을 해석하기 위해 민감도해석(Sensitivity analysis) 및 HQS(Handling Quality Simulator) 조종사 평가를 수행하였다.

• 제어로봇시스템학회논문지
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• 제5권2호
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• pp.237-247
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• 1999

Flight parameters of a light aircraft in normal category named ChangGong-91 we identified from flight tests. Modified Maximum Likelihood Estimation (MMLE) is used to produce aerodynamic coefficients, stability and control derivatives. A Flight Training Device (FTD) has been developed based on the identified flight parameters. Flat earth, rigid body, and standard atmosphere are assumed in the FTD model. Euler angles are adapted for rotational state variables to reduce computational load. Variations in flight Mach number and Reynolds number are assumed to be negligible. Body, stability and inertial axes allow 6 second-order linear differential equations for translational and rotational motions. The equations of motion are integrated with respect to time, resulting in good agreements with flight tests.

• Transactions on Control, Automation and Systems Engineering
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• 제4권2호
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• pp.114-123
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• 2002

Called VISTA (Variable-stability In-flight Simulator Test Aircraft), the one-of-a-kind NF-l6D has a simulation system that can mimic several aircraft. Though housed in an F-l6 Fighting Falcon airframe, VISTA can also act like the F-15 Eagle or the Navy's F-14 Tomcat. More importantly, such flexibility allows for improved training and consolidation of some sorties. Consequently USAF Test Pilot School students will have an opportunity to learn how to test future integrated cockpits. In this paper we will use the multiple model adaptive estimation (MMAE) and the multiple model adaptive controller (MMAC) techniques to model the aircraft's flight control system containing the longitudinal and lateral-directional axes. Single and dual actuator and sensor failures will also be included in the simulation. White Gaussian noise will be included to simulate the effects of atmospheric disturbances.

• 한국군사과학기술학회지
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• 제17권4호
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• pp.430-435
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• 2014

This paper presents the case study of the airworthiness certification for the flight control system of tactical UAV. Airworthiness regulations for flight characteristics and design and construction based on the STANAG 4671 are selected, and safety assessment is performed. Stall protection on wing level and turning flight criteria, and flap interconnection system failures were analyzed and applied to the flight control system design. The Hardware-in-the-loop simulation including math model, integrated system verification and validation test and failure mode and effects test were also performed and they are used to validate the means of compliance of the proposed airworthiness.

• 한국항공우주학회지
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• 제36권11호
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• pp.1104-1111
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• 2008

고등훈련기급에 탑재되어 있는 전기식 비행제어계통 (digital fly-by-wire flight control system)은 통합 다기능 감지기(IMFP : Integrated Multi-Function Probe)를 이용하여 항공기의 고도/속도/받음각 정보를 획득한다. 고등훈련기에는 3개의 IMFP가 장착되어 있으며, 이는 비행제어법칙에 3중의 공기정보를 제공한다. IMFP로부터 제공된 3개의 공기 정보는 중간 값을 채택하여 보다 신뢰성 있는 정보를 비행제어법칙에 제공한다. 초음속 비행시험 결과, 초음속 영역에서 발생하는 잡음이 포함된 IMFP로 인하여 고도유지모드 자동조종장치를 작동시켰을 때, 세로축으로 진동현상이 발생하였다. 이러한 현상은 자동조종장치를 이용하여 비행을 할 경우, 항공기 안정성 및 조종성을 저해할 수 있다. 본 논문에서는 초음속 영역에서 발생하는 IMFP 잡음정보가 자동조종장치에 영향을 미치지 않도록 비행제어법칙을 설계하였으며, 제어법칙설계 및 귀환이득을 조율하여 선회비행 시에 피치자세각 유지모드를 개선하였다. 설계된 비행제어법칙은 비실시간 시뮬레이션 및 비행시험을 통하여 검증하였다.

• International Journal of Aeronautical and Space Sciences
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• 제18권3호
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• pp.574-578
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• 2017

In order to achieve iterative design in early R&D period, a Distributed and Real-time Integrated Simulation System for avionics based on a Model-Based Systems Engineering (MBSE) method is proposed. The proposed simulation system includes driver, simulation model, monitor, flight visual model and aircraft external model.The effect of this simulation system in iterative design and system verification is testified by several use cases. The result shows that the simulation system, which can play an important role in iterative design and system verification, can reduce project costs and shorten the entire R&D period.

• 항공우주기술
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• 제8권1호
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• pp.172-178
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• 2009

최근에 개발된 소형제트기는 조종사의 피로경감과 더불어 비행안전성 제고를 위하여 자동비행시스템이 필수적인 요소로 인식되고 있다. 또한, 소형항공기의 항공전자시스템은 집중화된 다중프로세서(centralized multi-processor)와 다중연산 계산구조(multi-process computing architectures)로서 B-777의 Integrated Modular Avionics와 유사한 시스템을 장착하는 추세이다. 이러한 소형항공기 시스템 변화는 고전적 비행방식인 조종사 중심의 비행방식에서 자동비행제어시스템(AFCS) 중심의 비행방식으로의 변화를 야기하였으며 자동 비행제어시스템의 비중은 보다 더 증가하고 있다. 이에 본 논문에서는 상용 소형항공기용 자동비행장치(Autopilot)에 대한 HILS를 구성하여 성능을 검증하였다. 또한, 현재 개발하고 있는 FBW용 FCC(Flight Control Computer)에 탑재될 자동비행 알고리듬에 대한 성능을 PILS를 통하여 확인하였고, 상용 Autopilot에 대한 HILS 결과와 같은 조건에서 비교하여 그 성능을 검증하였다.

• 한국항공운항학회지
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• 제27권2호
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• pp.54-69
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• 2019

The primary objective of this paper is to introduce the application of Human-Machine Interface (HMI) and Augmented Reality (AR) technologies in flight operations. These include: self-check-in, baggage handling, airport security and surveillance, airport operations monitoring, In-Flight Entertainment and Connectivity (IFEC), cockpit design, and cabin crew support. This paper investigates the application status and development trends of HMI and AR technologies for airports and aircraft. These technologies can provide more efficient in-flight passenger service and experience by using AR devices. This paper also discusses the developments such as; the Integrated Control Application (ICA) for the IFEC interface, AR flight simulation training program using the fixed-based simulator, and the AR aircraft cabin interior concept test program. These applications present how HMI and AR techniques can be utilized in actual flight operations. The developed programs in this paper can be applied to their purpose within aircraft interiors and services to enhance efficiency, comfort, and experience.

• 제어로봇시스템학회논문지
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• 제5권6호
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• pp.683-690
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• 1999

This paper deals with a fault-tolerant control method for robust control of RPV(Remotely Piloted Vehicle). To design the flight control system, the 6-DOF simulation program has been developed based on the dynamic model of RPV. A robust fault detection and diagnosis method proposed by Kwon et al. [8]-[10] is adopted to detect the actuator fault of RPV and to make the controller reconfiguration. The Hoo control method is applied to the flight control system. An integrated simulation for performance evaluation of the fault-tolerat\nt control system designed is performed via 6 DOF simulation and shows that the control system works even under the actuator fault.