• Proceedings of the Korean Society of Computer Information Conference
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• 2017.07a
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• pp.11-12
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• 2017

본 논문에서는 항공기 비행 자세를 직관적으로 이해하고 동작의 원리를 시각화 할 수 있는 비행 자세 시뮬레이터를 구현하였다. 항적 정보의 변화에 따라 6축 모션 플랫폼을 동작시키고, 자이로 센서로 부터 전달 받은 비행 자세를 시뮬레이터에 전달하여 시스템을 구성한다. 항공기의 자세를 분석하기 위하여 자이로 센서와 가속도 센서를 같이 사용하는데 자이로 센서는 적분과정의 누적오차가 발생하고 가속도 센서는 짧은 순간의 진동에 따른 노이즈가 심하여 상보 필터를 이용한 보정작업을 하였다. 산출된 센서 정보를 이용하여 6축 모터에 전달할 각도를 계산하여 모션 플랫폼을 동작시키게 되며 시각화 결과는 OpenGL을 이용하여 구현하였다. 본 연구의 결과는 향후, 항공관련 학생들의 교육 기자재로 활용될 수 있을 것으로 사료된다.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.30 no.4
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• pp.215-221
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• 2022

본 연구는 민간항공 조종사 훈련 및 평가에 중요하게 고려되고 있는 8가지 핵심 역량 향상을 위한 기초자료 마련을 위해 수행되었으며, 그 중 가장 중요하다고 판단되는 상황인식(situation awareness) 및 작업부하 관리에 대해 분석하였다. 예비 조종사를 대상으로 항공기 접근 및 착륙 단계를 진행하는 동안 PM(pilot monitoring) 역할을 수행하며 인식하는 항공기 상황과 작업부하량에 대해 평가하였다. 평가 시나리오는 기본비행훈련장치(basic aviation training device)를 사용하여 지형적 상황인식, 공간/시간적 상황인식, 시스템 상황인식, 환경적 상황인식을 평가할 수 있는 요소로 구성하였으며, 모니터링 도중 의도적인 주의분산 상황을 추가하였다. 연구 결과, 전체 비행 단계에 대한 상황인식은 32.3%이고, 지형적 상황인식(60.3%)이 가장 높고, 시스템 상황인식(18%)이 가장 낮은 것으로 나타났다. NASA-TLX 평가방법으로 측정한 작업부하량은 10.8점(20점 만점)으로 나타났다. 또한, 기초공중항법학을 수강한 예비 조종사들이 대체로 높은 상황인식을 하였고, 작업부하 결과는 지형적 상황인식과 밀접한 상관관계를 가지고 있었다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.17 no.1
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• pp.159-164
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• 2016

This paper reports the load factor logic design for a fly-by-wire helicopter flight envelope protection. As a helicopter is very complex system with a rotor, fuselage, engine, etc., there are many constraints on the flight region. Because of these constraints, pilots should consider them carefully and have a heavy workload, which causes controllability degradation. In this respect, automatic logic is needed to free the pilot from these considerations. As one of these logics, the flight envelope protection logic for the load factor of a FBW helicopter was designed. The flight to exceed the load factor is caused by an abrupt pitch cyclic stick change. In this scheme, the load factor limit logic was added between the pilot stick command block and pitch attitude command block. From the current load value, the available attitude range was calculated dynamically and simulated on the helicopter simulator model to verify the performance. A comparison of the simulation results at the hovering and forward speed region with and without applying the load limiting logic showed that the load factor limit was exceeded more than 20% when the logic was not applied, whereas with the load factor limit logic the load factor was within the limit. In conclusion, a dynamically allocated limitation logic to helicopter FBW controller was verified by simulation.

• Fire Science and Engineering
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• v.21 no.3
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• pp.104-112
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• 2007

Simulators were introduced in education as a tool to make advanced training standardized, less expensive, and without danger to those involved. In 1922 in the Unites States, Edward Link presented his homemade flight simulator, which became common place in both military and civilian aviation, known as the "Link Trainer". The development of mannequin simulators used for medical simulation education, training, and research is reviewed, tracing the motivations, evolution to commercial availability, and efforts toward assessment of efficacy of those for teaching cardiopulmonary resuscitation(CPR) for medical personnel and emergency medical technicians(EMT), cardiology skills, anaesthesia clinical skills, and crisis management. This study will provide a brief overview of simulators and trainers in several domains.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.222-231
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• 2004

LCS(Launch Control System) in Space Center performs the ground and flight tests of launch vehicle. Those tests require data monitoring and control functions to the external systems such as launch vehicle, launch pad, and propellant supply system, etc. The LCS is composed of real time control system, simulation system, data server, external network, etc. The purpose of the simulation system is to simulate launch vehicle, and it is used for evaluation test of the LCS. This paper described the simulation system overview, the concept design, and the real time data processing evaluation tests of the simulator, gateway, data distribution server which are constituents of the simulation system.

• Journal of Advanced Navigation Technology
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• v.16 no.6
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• pp.1092-1100
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• 2012

In this paper, it has designed and developed the integrated aural cueing system(ACS) system of the reconfigurable tactical Flight Training System(RTT) for the 6 rotorcraft such as UH-1H, UH-60, AH-1H, 500MD, BO-100, and CH-47. RTT is an evolving alternative instructional training system to provide the ability to rehearsal and collectively train, through networked simulators in a unit-collective and combined arms simulated battlefield environment. ACS handles the volume, pitch and repetition of the digitally stored sounds based on commands it receives from the Host server. This paper explained and implemented the conceptual and detail design the ACS system. In order to evaluating the performance of the ACS system, we made the monitoring system for interworking the virtual Host and the ACS system. As the result, it was confirmed the good performance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.124-133
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• 2003

We propose an application of the Object-Oriented design methodology to develop operational flight program(OFP) for stores management computer(SMC) which manages and controls stores inventory, stores activation, launch for missiles, and release of the conventional weapons. For the development of SMC, a military version of PowerPC 603e is used as a central processing unit board and VxWorks real-time operating system is used. The Tornado software development environment(SDE) and the programming language Ada95 are used for OFP development. We design three layerd in the OFP for the independency of the software modules. An avionics system computer(ASC) simulator and a test bench are developed for the SMC integration test and verification test. And the tests are rigorously and successfully conducted.

• Journal of Convergence for Information Technology
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• v.7 no.5
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• pp.75-82
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• 2017

Recently, as the roles and utilization fields of UAV become more diverse, demand for high - level mission has been increasing. To solve this issue, researches on the operation of multiple small UAVs and related systems have been actively carried out. The multiple small UAVs based application system has a problem that the task complexity of control personnel increases because the control personnel must continuously control and manage several small UAVs. Hence, it is necessary to develop a software platform that can perform efficient control in order to employ a multiple small UAVs based application system successfully. In this paper, we propose an effective ground control software platform for application systems using multiple small UAVs. We first analyze the requirements for the software platform, and design and implement software based on the analysis. Simulation using the X-plane flight simulator shows that multiple flight data are effectively displayed and that the image data transmitted from many small UAVs are simultaneously displayed in real time.

• Journal of Aerospace System Engineering
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• v.17 no.1
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• pp.59-67
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• 2023

Recently, interest in flight simulators based on HMD and mixed reality is increasing. However, they have limitations in providing various interactions and a sense of presence to pilot wearing HMD. To overcome these limitations, a mixed reality image corresponding to the interaction under the actual cockpit environment must be generated in real time and provided to the pilot. For this purpose, we proposed a mixed reality image generation method, in which the cockpit area including the pilot's body could be extracted from real image obtained from the camera attached to the HMD and then composed with virtual image to generate a high-resolution mixed reality image. Simulation results showed that the proposed method could provide mixed reality images to HMD at 30 Hz frame rate with 99% image composition accuracy.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.28 no.3
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• pp.225-236
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• 2017

In this paper, a simulation test bed is presented which operates to provide full-scale simulation of airborne multi-function phased array radars. This simulation test bed provides a capability to evaluate the target tracking performance. To realize aircraft operation scenario, we developed 6DOF aircraft dynamics model which can generate trajectories and attitude of an aircraft. This procedure includes steady state flight trim search, autopilot design, and aircraft guidance command design. Also, the radar-environment integrated simulator includes target detection/measurement model and tracking filter. Developed simulator is validated by creating an air-to-air scenario.