• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.4
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• pp.76-83
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• 2004

A Propulsion System of the CRW(Canard Rotor Wing) type UAV(Unmanned Aerial Vehicle) was composed of the turbojet engine to generate the propulsive exhaust gas, and the duct system including main and rotary ducts, the nozzle subsystem including main and tip jet nozzle for three flight modes such as lift/landing mode, low speed transition flight mode and high speed forward flight mode. Transient simulation performance utilized the ICV (Inter-component volume) method and simulated using the SIMULINK. Transient performance analysis was performed on 3 cases. Fuel flow schedules to accelerate from Idle to maximum rotational speed were divided into the step increase of the most severe case and ramp increase cases to avoid the overshoot of turbine inlet temperature, and variations of thrust and the turbine inlet temperature were investigated in some transient analysis cases.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.163-166
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• 2008

The helicopter flies at low level flight mode in its own operational range comparing to other aircraft categories. The low level flight means that the engine operates at variable atmospheric condition such as hot and cold temperature, snow, heavy rain, etc. Furthermore it may increase the entering possibility of engine foreign object damage particles like sand, dust, etc., i.e. this operating condition gives rise to damages of engine gas path components. An on-line condition monitoring program was developed by using SIMULINK, where measurement signals were simulated as an input module. The reliability and capability of the developed on-line condition monitoring were confirmed through application to a real helicopter engine health monitoring.

• Journal of the Korean Society of Industry Convergence
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• v.26 no.4_2
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• pp.639-648
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• 2023

In modern society, UAM (Urban Air Mobility) transportation system is being developed as an alternative to urban traffic congestion and environmental problems, and electric vertical take-off and landing (eVTOL) is a combination of vertical take-off and landing function and electric power. It is attracting attention as an innovative next-generation transportation method as an eco-friendly alternative that reduces noise and air pollution by providing efficient mobility within the city. Since eVTOL development requires designing and implementing airframes suitable for various mission purposes, the power system needs to be developed as a platform concept before airframe development. In this study, we empirically proposed a test bench concept equipped with a stable power supply and an efficient control system, essential in developing a power platform with a combined function in the form of a fuselage and module type specialized for various mission purposes. The proposed drivetrain platform test bench consists of a system verifying the stable take-off and landing software and a power platform adjusting the motor's thrust. It will serve as a verification system that can be developed.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.31 no.1
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• pp.11-17
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• 2023

In this study, the correlation analysis between total system error and environmental factor variables was performed to confirm the effect on the performance of the integrated navigation system by various environmental factors. To collect flight data of hybrid vertical take-off and landing UAVs, scenarios including various turning sections and straight sections such as left turn, right turn, turning rate, and path change angle were selected, and environmental data of wind direction, wind speed, temperature, air pressure, and humidity were collected in real time through weather station. As a result of the correlation analysis between the collected flight data and environmental data, it was concluded that the performance of the integrated navigation system by environmental factors within the collected data was not significant affected and was robust.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.9
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• pp.599-608
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• 2022

Urban air mobility (UAM) equipped with rotor system is subject to ground effect at vertiport during takeoff and landing. The aerodynamic performance of the aircraft in ground effect should be analyzed for the safe operation. In this study, The ground effects on the aerodynamic performance and wake structure of the quadcopter electric vertical takeoff and landing (eVTOL) configuration equipped with coaxial counter-rotating propellers were investigated by using the lattice Boltzmann method (LBM). The influence of the ground effect was observed differently in the upper and lower propellers of the coaxial counter-rotating propeller system. There was no significant change in the aerodynamic performance of the upper propeller even if the propeller height above the ground was changed, whereas the averaged thrust and torque of the lower propeller increased significantly as propeller height decreased. In addition, the amplitude of the thrust fluctuation tended to increase as the propeller height decreased. The propeller wake was not sufficiently propagated downstream and was diffused along the ground due to the outwash flow developed by the ground effect. The impingement of the rotor wakes on the ground and a fountain vortex structure were observed.

• Review of KIISC
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• v.22 no.8
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• pp.36-40
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• 2012

북한은 사이버공간을 해방구로 보고 지난 2003년도에 인터넷 대란 공격을 실시한 이래 사이버 공격을 지속적이고 강력하게 감행하고 있다.1) 지난해에는 농협전산망을 공격하였으며 최근에는 서해상에서 GPS교란 공격을 실시하여 인천 국제공항에 이착륙하는 항공기에 심각한 위협을 초래하기도 하였다. 이처럼 북한을 포함한 전 세계적인 사이버 공격이 이제는 국가안보상의 심대한 위협이 되고 있어 각국은 사이버전 대비에 심혈을 기울이고 있다. 이제 우리나라는 사이버공격을 가장 많이 받는 국가 중의 하나가 되고 있다. 국가적인 사이버위협이 지속되는 상황하에서 국방차원에서의 사이버대응 실태를 살펴보고 발전책을 제시하고자 한다.

• Proceedings of the KIEE Conference
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• 2004.11c
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• pp.59-61
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• 2004

For automatic landing of small VTOL UAV, it is necessary to calculate the distance from the UAV and the ground. The distance can be generally measured by a ultra-sonic sensor, but the ultra-sonic sensor has errors according to velocity of a sensor board. To compensate these errors, we proposed a sensor fusion method using a Kalman filter.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.3 no.1
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• pp.97-105
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• 1995

본 연구는 창공-91 항공기의 비행 시험의 일환으로 수행된 것으로, 항공기의 이 착륙 성능 측정을 위한 비행 시험의 절차와 사용된 방법, 자료 처리 절차 그리고 비행 시험 결과에 대해 기술하였다. 본 비행 시험은 FAR 부속서인 Advisory Circular 23-8A 의 비행 시험 절차에 따라 수행되었으며, 측정된 자료를 분석한 결과 설계시에 결정된 창공-91의 성능 자료를 만족함을 보였다.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.22 no.1
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• pp.44-50
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• 2014

In this study, we surveyed the operating status of the LSA Airpark in Metropolitan Area of Korea, and compared the Airfield Facilities Manual for the Air Leisure. We analyzed the problems of the closure and the currently used of the LSA Airpark, through site visits. We presented the re-usability for the closure LSA Airpark, the improvements for the currently used of the LSA Airpark.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.1
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• pp.81-93
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• 1993

창공-91의 비행 시험의 목적은 성능 측정과 비행 특성의 확인이며 교통부의 기준은 주로 비행기의 운항에 따르는 안정성에 주안점을 두고 있다. 비행 시험으로 실속 속도와 이착륙 성능 그리고 상승 성능을 측정하여 비행 교범에 수록하였고, 안정성과 조종성의 적절함을 판단하였다. 창공-91 A2기의 비행 시험에 소요된 비행 시간은 81. 5 시간이다. (창공-91 $A_1$기 : 52.8시간)