• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.6
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• pp.540-547
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• 2015

This paper describes development contents and flight tests of an ACMI simulator based on LVC integrating architecture. ACMI is the system that provides air combat training and ground bombing training for improving fighting efficiency, that is the live simulation involving real people to operate real systems. ACMI simulator was developed for technic acquisition of LVC interoperability by using data link communication. ACMI simulator simulated maneuvering of a fighter by operating an UAV, a fighter can be distinguished from an UAV by maneuvering characteristics. This study proposes maneuvering simulation method by using flight data of the UAV, and performed its flight test for verifying similarity of fighter maneuvering.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.10
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• pp.871-876
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• 2016

Abnormal odor similar with burning smell often appears at the cockpit in the beginning of ultra-sonic aircraft without air filter due to the heating of production materials remained at the bleed air duct. Sources of the odor should be removed by burn-in test before test flight in order to prevent pilot confuses order with emergency such as fire of engine. However, the present method cannot prevent abnormal odor completely at the high altitude flight because maximum temperature of flight is higher than it of burn-in-test. This paper suggests burn-in test improved based on the analysis of thermal conditions of high altitude flight. It is verified that the existing burn-in test cannot cover thermal conditions of high altitude flight due to the discontinuous flow control, high change rate of temperature per unit time and difference between limit temperature of condenser and turbine. In order to overcome the limitations of current methods, the new burn-in test with continuous flow control are suggested. The continuous flow control are achieved by ram air inlet control. The effect of suggested method are verified by ground tests and flight tests. The results show the bleed air temperature can cover the temperature of high altitude flight and prevent abnormal odor at the flight test.

• KEPCO Journal on Electric Power and Energy
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• v.4 no.2
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• pp.115-123
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• 2018

Various types of robots running on power transmission lines have been developed for the purpose of line patrol monitoring. They usually have complex mechanism to run and avoid obstacles on the power line, but nevertheless did not show satisfactory performance for going over the obstacles. Moreover, they were so heavy that they could not be easily installed on the lines. To compensate these problems, flying robots have been developed and recently, multi-copter drones with flight stability have been used in the electric power industry. The drones could be remotely controlled by human operators to monitor power distribution lines. In the case of transmission line patrol, however, transmission towers are huge and their spans are very long, and thus, it is very difficult for the pilot to control the patrol drones with the naked eye from a long distance away. This means that the risk of a drone crash onto electric power facilities always resides. In addition, there exists another danger of electromagnetic interference with the drones on autopilot waypoint tracking under ultra-high voltage environments. This paper presents a patrol monitoring plan of autopilot drones for power transmission lines and its field tests. First, the magnetic field effect on an autopilot patrol drone is investigated. Then, how to build the flight path to avoid the magnetic interference is proposed and our autopilot drone system is introduced. Finally, the effectiveness of the proposed patrol plan is confirmed through its field test results in the 154 kV, 345 kV and 765 kV transmission lines in Chungcheongnam-do.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.59-59
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• 2002

램제트 추진기관은 압축과정을 별도의 부품 없이 형상에 의해서 감속하여 연소 압력비를 얻는다. 따라서 구동 마하수와 형상에 의해 흡입과정의 압축 효율이 결정된다. 설계점은 충분한 유량을 확보 할 수 있는 유량과 충격파 각을 조절하여 전압력 손실을 줄이도록 고려되어야 한다. 또한 연소가 일어나면 연소실 압력이 배압으로 작용하고 비행시에 받음각은 변하므로 이에 따른 성능 분석도 고려 되어야 할 사항이다. 본 연구는 국내에서 실험한 형상에 대해 수치계산을 수행하여 코드의 검증과 아울러 램제트 유동장의 수치적 시뮬레이션도 설계단계에서 하나의 도구로 이용할 수 있음을 보여준다. 실험에서는 배압 조건을 얻기 위해 유동 블록키지를 유로 내에 두어 상응하는 배압을 얻었지만 본 계산에서는 압력 경계조건을 직접 사용하였다. 유동이 비정상 특성을 가지므로 시간 정확도를 이차로 가지도록 이중시간 전진법을 사용하였다. 사용한 압력비는 충격파가 카울 끝에 닿는 임계상태에 가까운 12, 13, 14에 대해 계산을 수행하였고 부스터모드로 흡입구 끝이 막혀 있다가 램제트 모드로 바뀌어 연소실 압력이 위의 압력비라고 가정할 때의 비정상 천이 과정을 계산해 보았다. 본 계산은 흡입구 부분만을 떼어놓고 적절한 가정 하에 수행되었지만 연소실 내부도 비정상 특성을 가지므로 흡입구와 연소실을 동시에 같이 계산해야한다. 추후에 전체적인 계산을 진행하기 위한 전 단계로 흡입구 계산만을 수행하여 실험과 잘 일치하는 계산 결과를 얻었고 전체 계산을 위한 연구는 진행 중에 있다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.289-292
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• 2007

Performance of a dual mode ramjet engine based on the sensitivity analysis of design parameters (the gap between cowl and inlet spike and combustor length) was analyzed from the view points of aerodynamics and thermodynamics. A dual mode engine performing from supersonic to hypersonic (Mach no. 2 to 6) was designed in a proposed flight envelop. The design method and result were comparable to the results of the previous study, Hyperion RLV, and the CFD calculation.

• Proceedings of the Korea Information Processing Society Conference
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• 2021.05a
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• pp.198-201
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• 2021

무인 항공기(UAV, Unmanned Aerial Vehicles)는 높은 기동성을 가지며 설치 비용이 저렴하다는 이점이 있어 홍수, 지진 등의 재난 재해 감시 시스템에 이용되고 있다. 재난 재해 감시 시스템에서 UAV는 지상에 위치한 사물인터넷(IoT, Internet of Things) 기기로부터 데이터를 수집하는 임무를 수행하기 위해 계획된 항로를 따라 비행한다. 이때 UAV가 정상 경로로 비행하기 위해서는 실시간으로 GPS 위치 확인이 가능해야 한다. 만일 UAV가 계산한 현재 위치의 GPS 정보가 잘못될 경우 비행경로에 대한 통제권을 상실하여 임무 수행을 완료하지 못하는 결과가 초래될 수 있다는 취약점이 존재한다. 이러한 취약점으로 인해 UAV는 공격자가 악의적으로 거짓 GPS 위치 신호를 전송하는GPS 스푸핑(Spoofing) 공격에 쉽게 노출된다. 본 논문에서는 신뢰할 수 있는 시스템을 구축하기 위해 지상에 위치한 기기가 송신하는 신호의 세기와 GPS 정보를 이용하여 UAV에 GPS 스푸핑 공격 여부를 탐지하고 공격당한 UAV가 경로를 이탈하지 않도록 대응하기 위해 연합학습(Federated Learning)을 이용하는 방안을 제안한다.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.26 no.2
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• pp.83-90
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• 2018

This paper describes a case study on the design factor analysis of vertical wind tunnel for skydiver's training or experiencing of paradropping exercise in the air. The case study of vertical wind tunnel design is to provide the knowledges on effects of parameter's variation when it is applied to overall or partial duct of tunnel circuit. The analysis of design parameters based on pressure loss are produced one by one through the tunnel components from the flight chamber because the wind tunnel must satisfy the requirement of flight chamber such as flow speed, quality and quantity. Results shows the various effects of parameter variation with pressure loss in the wind tunnel circuit. Pressure loss should be based on the determination of fan and power system which can be selected from market or new design.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.31-34
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• 2003

To trace the working point of pressure-fed rocket propulsion system, direct analogy model was suggested, by which propellant mass flow rate and combustion chamber pressure were calculated from propellant tank pressures, levels and flight acceleration. In this paper, the analysis of KSR-III flight test results was taken by example, and it can be described that working point transition tendency of pressure-fed rocket propulsion system can be calculated by this direct analogy model.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.1
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• pp.37-66
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• 1993

항공기 운항과 관련한 환경의 변화는 다른 분야의 환경 변화보다 그속도가 빠르고 변화의 폭이 크다고 할 수 있다. 약 1세기 동안에 항공기 개발기술은 실로 놀라운변화를 거듭해 왔으며 전자시스템의 도입으로 수 십년 전에는 상상조차 할 수 없었던 일들이 현실로 나타나게 되었다. 본 논문은 이러한 환경변화 가운데 비행안전이라는 목표를 실현하기 위해 우선적으로 항공기 운항과 관련한 환경변화 요인들에 내포되어 있는 문제점들을 분석하고자 하였으며 장비개발 및 Human Factor, 항공교통 관제 및 항공기 운항 그리고 조종사 관리 및 조종 환경으로 분야를 나누어 요인 분석을 함으로써 현재와 미래를 통해 예상되는 문제점들을 도출하였다. 또한 항공기 사고사례를 분석하여 공통되는 요인을 도출, 이를 문제점으로 제시하였다. 이러한 문제점들에 대한 대책에 관한 연구는 항공기 운항 분야의 발전과 비행안전을 위해 계속해서 이루어질 것으로 기대한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.47-53
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• 2017

One of the most common causes of failure of space launch vehicles is combustion instability. Combustion instability is a phenomenon that the pressure perturbation inside the combustion chamber is greatly amplified due to the interaction of the pressure perturbation inside the combustion chamber and the heat release perturbation. When this phenomenon becomes worse, an engine failure or launch vehicle crash occurs. In order to predict and avoid such combustion instability, understanding of the phenomenon is indispensable, and numerical, theoretical, and experimental approaches to combustion instability have been carried out worldwidely.