• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.8
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• pp.26-33
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• 2005

Smart UAV, which adopting tiltrotor aircraft concept, requires vertical take-off and landing, long endurance and high speed capability. These contradictable flight performances are hard to meet unless the operation of flap system which should reveal optimal performance for each flight mode. In order to design SUAV flaperon satisfying the three performance requirements, various configurations are generated and their aerodynamic performances are analyzed using numerical flow computations around flap systems. Considering aerodynamic performance and structural simplicity, a final flap configuration is selected and the performance is validated through the wind tunnel testing for 40% scale model.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.67-70
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• 2007

It is well known that the aircraft engine inlet should be safely designed against the bird strike at the aircraft development stage. The aircraft accident is increasing for FOD(Foreign Object Damage), especially bird of runway circumference. The aircraft accident due to bird strike brings about economic loss and which is connected with the life of passengers. In this study, MSC/DYTRAN has been utilized to analyze the aircraft engine inlet against the bird strike. In order to validate the proposed method for the bird strike analysis, this study was performed with comparison of precedence study results.

• Journal of Aerospace System Engineering
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• v.8 no.3
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• pp.14-19
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• 2014

When a helicopter lands on a ship deck in high sea states, one of main difficulties is the ship motion by sea wave, In case of a manned helicopter, a pilot lands a helicopter on the deck during quiescent period of ship motion, which is perceived from different visual cues around landing spot. The capability to predict this quiescent period is very important especially for shipboard recovery of VTOL UAV in harsh environments. This paper describes how to predict heave motion of a ship for shipboard landing of a VTOL UAV. For simulation, ship motion by sea wave was generated using a 4,000 ton class US destroyer model. Heave motion of ship deck was predicted by applying auto-regression method to generated time series data of ship motion.

• Proceedings of the Safety Management and Science Conference
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• 2002.05a
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• pp.263-268
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• 2002

국내 공항에서 보유하고 있는 제한된 주기장에 대한 이용률과 주기되어 있는 항공기의 탑승에 소요되는 시간 및 도보거리는 공항의 운영 및 승객의 편리성 평가에 주요한 척도가 되고 있으며, 공항의 주요 운영 목표는 합리적인 항공기 주기장 배정을 통한 주기장 이용률의 최대화 및 터미널 이용 승객의 편리성 증대라 할 수 있다. 이에 본 연구에서는 대상 공항의 시설배치, 터미널 구조, 공항의 이용 승객 등을 고려하여 사용 가능한 주기장의 이용률의 최대화하고 터미널에서의 여객 이동거리를 최소화하는 주기장 배정 알고리즘의 개발과 그 결과를 국내 공항에 적용시키는 것을 그 목적으로 한다. 이를 위하여 기존의 GAP 정식화 모델을 최적화 소프트웨어인 LINGO를 활용하여 다중 시간 주기를 갖는 복잡한 문제를 단일 시간주기를 갖는 문제로 변환하기 위한 접근 방법을 제시함으로써 기존의 OR 접근 방법이 가지는 최적해 산출을 위한 긴 소요시간의 문제를 해결하고 실제 공항에 적용하여 실시간 의사결정을 위한 배정 결과를 제공하였다. 본 연구를 통하여 현재 발견적 기법에만 의존하여 수행되는 주기장 배정결과를 최적화 알고리즘을 통하여 산출함으로써 공항의 주요한 운영 목표인 항공사 및 여객의 시간 비용을 최소화할 수 있다. 또한 기상 악천후로 인한 항공기의 이착륙 지연이 발생할 경우 복잡한 문제를 배정 알고리즘에 의해 신속히 해결함으로써 공항 운영의 효율성뿐만 아니라 공항 안전에도 기여할 수 있을 것이다.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.6
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• pp.56-63
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• 2009

In this paper, we present technical survey results on propulsion systems for Personal Air Vehicles (PAV). Reciprocating engines are suitable for current PAVs because of their superior efficiency and price advantages, except they produce noise problems. Turbo-Shaft engines are suitable for VTOL PAVs because of high specific power and wide operating range even though they are expensive. However, fuel cells and batteries may replace conventional engines in the near future.

• Journal of Aerospace System Engineering
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• v.9 no.4
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• pp.55-61
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• 2015

In this study, we peformed optimal design of a composite skid landing gear, one of the solid spring shock absorbers, for light vertical takeoff and landing aircraft. Although a solid spring type has poor energy dissipation capability, it is commonly used for light aircraft where sink speeds are low and shock absorption is non-critical in terms of simplicity, low cost and weight reduction. In this paper, design parameters of solid spring such as sink speed, gear leg length, deflection and landing load factor were reviewed. In order to meet structural requirements such as deflection and strength, finally, we conducted optimal design of the composite skid landing gear for VTOL UAV using genetic algorithm and pattern search algorithm.

• Journal of the Korea Convergence Society
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• v.8 no.6
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• pp.219-226
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• 2017

As the UAV industry is getting matured, various types of UAVs have appeared in many application fields, including filming, reconnaissance, rescue, and etc. and it requires the quick hardware designs, particularly a battery pack, of the UAV. We developed the automatic battery pack design tool for the convenient battery pack configuration design of the hoverable type delivery UAV. With inputs, including current profile, voltage profile, various kinds of cell specifications, desired battery pack voltage, and etc. the automatic battery pack design tool calculates a pack having the minimum weight and the maximum capacity by combining either homogeneous cells or heterogeneous cells. Also, the tool could predict the capacity fading trend of the designed battery pack configuration.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.7
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• pp.26-31
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• 2003

In this paper, supersonic jets impinging on axisymmetric cone were investigated to obtain fundamental design data for jet deflector case of example being VTOL/STOL or rocket launch. It was of interest to study flow phenomena such as shock interactions and separation induced by shear layer. Experiments were conducted to obtain schlieren flow visualization and measurement of surface pressure. Numerical results are compared with the experimental result. The dominant feature of the flow is the shock pattern induced by the interaction between the cone shock and the barrel shock. This pattern can take a wide variety of forms depending on the structure of the free jet and strongly influences the form of the surface pressure distributions.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.6
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• pp.556-561
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• 2009

The UAV(Unmanned Aerial Vehicle) that is remotely operating in various and long flight environments must have a very reliable propulsion system. Precise fault diagnosis of the turbo shaft engine for the Smart UAV that has the vertical take-off, landing and forward flight behaviors can promote reliability and availability. This work proposes a new diagnostic method that can identify the faulted components from engine measuring parameter changes using Fuzzy Logic and quantify its faults from the identified fault pattern using Neural Network Algorithms. The proposed diagnostic method can detect not only single fault but also multiple faults.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.3
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• pp.58-64
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• 2007

It is well known that the aircraft engine inlet should be safely designed against the bird strike at the aircraft development stage. The aircraft accident is increasing for FOD(Foreign Object Damage), especially bird of runway circumference. The aircraft accident due to bird strike brings about economic loss which is connected with the life of passengers. In this study, MSC/DYTRAN has been utilized to analyze the aircraft engine inlet against the bird strike. In order to validate the proposed method for the bird strike analysis, this study was performed with comparison of precedence study results.