• Defense and Technology
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• no.8 s.174
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• pp.36-43
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• 1993

신예 항공기들은 고가의 무기와 첨단전자장비들을 갖추고 있기 때문에 가격 또한 엄청나게 비쌉니다. 따라서 전투시에 상대의 후방까지 깊숙하게 침투시에 상대의 후방까지 깊숙하게 침투하여 목표물을 공격하되, 아군 항공기의 손실은 최소로 줄이는 것이 승패를 좌우하는 매우 중요한 요소입니다 따라서 항공기의 생존성을 제고하기 위해서는 상대의 레이다에 포착되지 않는 은폐기술 즉, 스텔스(stealth)성능이 필수적입니다

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.42-49
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• 2005

Technical performance measurement (TPM) has been in widespread use for many years and is recognized as a highly useful method that can identify deficiencies in meeting aircraft system requirements, provide early warning of program problems, and be used to monitor technical risks. This paper presents the overview of technical performance measurement method and its application in aircraft system development for KHP, KTX etc.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.4
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• pp.65-70
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• 2010

A small unmanned aerial vehicle(UAV), which uses a propulsion system consisting of electric motor and battery, weighs less than 8 kg, capable of hand launch. Because it is easy to operate and able to transmit image information in real time, the use of small UAV has been increasing. However, very few analysis methods or analysis results on flight performance of the small UAV have been known so far. In this paper, the performance analysis methods of a small UAV, which is manufactured to study an electric powered UAV, are suggested and their results are achieved. Aerodynamic data of the vehicle are obtained by making use of gliding performance from actual flight test, and required thrust and required power by flight speed are predicted. In addition, the methods to predict range and endurance in case of using battery as power source are suggested and their results are achieved.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.27 no.1
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• pp.62-68
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• 2023

An aerial relay system utilizing an unmanned aerial vehicle(UAV) or drone is addressed for event-driven operations such as temporary communication services for disaster affected area, military and first responder support. UAV relay system (URS) targets to provide a reliable communication service to a remote user equipment or an operator, therefore, a fast UAV placement to guarantee a minimum quality of service(QoS) is important when an operation is requested. Researches on UAV utilization in communication systems mostly target to derive the optimal position of UAV to maximize the performance, however, fast deployment of UAV is much more important than optimal placement under emergency situations. To this end, this paper derives the feasible area for UAV placement, investigates the effect of performance requirements on that area, and suggests UAV placement to certainly guarantee the performance requirements. Simulation results demonstrate that the feasible area derived in this paper matches that obtained by an exhaustive search.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2004.05a
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• pp.66-66
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• 2004

중량은 항공기의 성능을 좌우하는 주요 변수로써, 최소의 중량 달성이 100여 년 전 라이트 형제가 최초의 비행을 성공한 후, 항공기 개발자들의 주요 관심사였다. 일반 구조물의 최적화를 통한 설계는 구조물의 강도를 유지하면서 중량절감, 비용절감을 위해 널리 사용되고 있다. 하지만, 현재 항공기 구조물에 대해서는 아직 최적화론 통한 설계가 널리 적용되지 않고 있다. 그래서, 항공기에서는 중량절감을 위해 가벼우면서 강도를 큰 알루미늄이 주재료로 사용되고 있다.(중략)

• Defense and Technology
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• no.5 s.267
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• pp.52-59
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• 2001

본딩은 전기/전자 시스템뿐만 아니라 연료, 엔진, 비행제어, 유/공압계통 등에서도 안전한 전기적인 운용을 하기 위해서 필요하다. 항공기 개발에서 본딩은 설계시부터 요구조건을 두어 엄격히 관리해야 하며, 제작시에도 제시된 요구조건에 맞게 본딩을 해야 한다. 항공기의 전기/전자계통 설계시 요구성능과 항공기 및 운용자의 안전성 확보를 본딩 계통의 설계목표로 설정하고, 세부적인 본딩 요구조건과 유사기종의 설계개념을 보완하여 현실적으로 적용가능한 적용분야별 본딩 설치 및 설계 요구조건을 정립하는 것이 매우 필수적이라고 판단된다. 이 글에서는 항공기 설계시 고려해야 되는 본딩 일반요구조건에 대하여 기술해 보고자 한다.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.24 no.10
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• pp.951-957
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• 2013

In this paper, we propose a performance evaluation process of aircraft blade antennas. The process consists of various sub-processes that should be considered for a stable communication link with the base station. The process begins with the settlement of the ground shape and size to evaluate the impedance matching characteristics of a stand-alone antenna. Next, the main communications area of the antenna is determined by considering a flight scenario, and then the minimum gain requirements of the antenna are derived in the operating frequency band. Finally, the proposed evaluation process is applied for a commercial aircraft blade antenna. The results demonstrate that the proposed process is suitable to be adopted for the evaluation of aircraft blade antennas.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.6
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• pp.83-91
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• 2006

An advanced method of Relaxed Static Stability (RSS) is utilized for improving the aerodynamic performance of modern version supersonic jet fighter aircraft. The flight control system utilizes RSS criteria in longitudinal axis to achieve performance enhancements and improve stability. The flight control law of T-50 advanced trainer employs RSS concept in order to improve the aerodynamic performance and guarantee aircraft stability. The longitudinal center of gravity(X-c.g) varies as a function of external stores, fuel state and gear position. Shifts in X-c.g relate directly to longitudinal static margin in aircraft stability. This paper deals the maximum aft X-c.g for critical aircraft loadings and checks static margin limits using sensitivity such as damping, natural frequency, gain and phase margin. And nonlinear analysis was conducted for such as short period input. And also, this paper shows the T-50 aircraft stability based on the result of high angle of attack flight such as upright and inverted departure.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.05a
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• pp.226-230
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• 2010

In this paper, the performance of an electric powered small Unmanned Aerial Vehicle which has a battery and electric motor is analysed. Aerodynamic data is obtained through flight test and flight performance is predicted. As a result, we present the optimum flight speed for the maximum endurance and predict endurance and range according to the variation of flight speed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.10
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• pp.899-904
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• 2007

During the conceptual design phase of fighter class aircraft, the high speed wind tunnel test with 1/20 scale wing-body-tail model has been conducted to investigate the effects of leading edge flap deflection on the supersonic cruise performance of the aircraft. To select the proper leading edge flap deflection for the wind tunnel test, the aerodynamic characteristics due to various leading edge flap deflections have been analyzed by using corrected supersonic panel method. Based on the results obtained from the experimental and numerical approaches, the effects of leading edge flap deflection have shown to be useful to enhance the supersonic cruise performance of fighter class aircraft.