• Journal of the Korean Society of Propulsion Engineers
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• v.21 no.6
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• pp.83-90
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• 2017

Performance analysis of the turboshaft engines for combined rotorcraft was executed. A tip jet and a ducted fan aircraft were selected for combined rotorcraft application. Gasturb 12 software was used for turboshaft engine performance analysis. In the results, maximum required power for the tip jet engine is about 1,600 hp class and maximum required power for the ducted fan engine is about 1,000 hp class at the required aircraft mission. This is due to the additional power of the auxiliary compressor to get a bleed air mass flow rate for the tip jet operation. At the same time, fuel consumption of the tip jet aircraft is 2.8 times larger than ducted fan case. Therefore ducted fan type aircraft is more efficient than tip jet aircraft in terms of fuel economy.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.9
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• pp.671-680
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• 2020

This paper describes an improved beam analysis for compound rotorcraft fuselage design. The present beam approach is capable of analyzing fuselage composed of stiffeners using equivalent layer methodology. Thickness of the skin and laminated layer approach are suggested based on the unified beam formulation. The analysis which considers an equivalent stiffener layer is performed for a fuselage with stiffeners and preliminary study about the specification of stiffeners is conducted and compared by the results using the existing software.

• Proceedings of the Korea Technology Innovation Society Conference
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• 2005.10a
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• pp.619-636
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• 2005

기술의 복합성이 증가하고 제품의 존속 수명주기가 불확실해지면서 기술개발자가 의도하는 바와는 관계없이 사업 영역과 기술기반의 변하고 있다. 이러한 환경 속에서 산업 내 기술의 특성을 분석하는 이른바 산업기술분석 역할은 매우 중요하다. 그러나 그 범위가 매우 광범위하고 그 중 기술개발에 있어 관련된 산업기술분석의 프레임이 구체적으로 적용된 사례를 제한적이다. 따라서 다양한 산업을 지원하는 정부 기술개발 기회의 경우, 반도체에 적용되는 모듈러 기반 기술개발 틀과 성과분석이 항공기, 지능형 로봇과 같은 복합 시스템 산업에 그대로 적용해왔던 것이 현실이다. 이는 기술을 제품화함에 있어 필수적인 개발시스템의 기술적 속성이 산업기술 분석 방법론에 효과적으로 체화되지 못했기 때문이다 본 연구는 시스템과 서브 부품으로 구성되는 제품설계 특성을 구조화한 제품 아키텍쳐 이론을 소개하고 이를 기술개발체계에 적용하는 실증적 연구를 수행한다. 실증적 분석을 위해 항공기 개발 전 과정을 분해하고 아키텍쳐 분석방법을 실제 적용하였다. 아키텍쳐는 대표적으로 모듈 형(Module)과 인테그랄 형(Integral)으로 구분한다. 실제로 한 가지의 제품 안에도 모듈형 부품과 인테그랄 형 부품이 복합적으로 혼합되어 있는 경우가 많다. 또한, 제품을 어느 레벨까지 분해할 지에 따라 모듈화의 정도도 달라 질 수 있다. 본 연구는 아키텍쳐 중 Integral 속성의 정도를 파악하여 아키텍쳐 정도를 파악하였다. 측정 기준으로 첫째, 타 부품과의 기능적인 상호연관성과 둘째, 체계종합 설계와의 상호의존성 두 가지를 설정하였다. 이러한 두 가지 아키텍쳐 기준을 547개의 항공우주 부품 및 기술을 적용해 본 결과, 항공기 개발과정은 총 $65\%$의 인테그럴 속성을 가지고 있으며 기술분야 별로 아키텍쳐 정도가 다르게 나타나고 있었다(전자 부품은 분야는 오히려 모듈형에 가까웠음). 비단 항공기 개발과정 뿐만 아니라 다른 산업, 제품에도 적용될 수 있는 틀을 마련함으로써, 기존 연구개발기회에서 산업기술 분석을 통한 체계적 기획으로 전환할 수 있는 새로운 대안을 제시한다. 결과적으로 산업기술의 특성과 구조를 반영한 기술개발 방법론으로 아키텍쳐 이론을 적용할 수 있는 단초를 마련했으며, 이것은 본 논문이 기대하는 바이기도 하다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.2
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• pp.141-149
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• 2018

This paper presents a neural network controller design for complex damage to a blended wing Unmanned Aerial Vehicle(UAV): partial loss of main wing and vertical tail. Longitudinal/lateral axis instability and the change of flight dynamics is investigated via numerical simulation. Based on this, neural network based adaptive controller combined with two types of feedback linearization are designed in order to compensate for the complex damage. Performance of two kinds of dynamic inversion controllers is analyzed against complex damage. According to the structure of the dynamic inversion controller, the performance difference is confirmed in normal situation and under damaged situation. Numerical simulation verifies that the instability from the complex damage of the UAV can be stabilized via the proposed adaptive controller.

• Journal of Advanced Navigation Technology
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• v.24 no.2
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• pp.73-84
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• 2020

To overcome ground congestions due to growing number of cars, a lot of companies have proposed personal aerial vehicle (PAV). Among PAV, electric vertical take-off and landing (eVTOL) aircrafts capable of vertical take-off and landing with electric power are drawing attention, and their configurations vary from multicopters to tilt ducted fans. This study tries to analyze the characteristics of each eVTOL design configurations. Parasite drag was calculated using component build up method for Vahana, Aurora, Volocopter representing each eVTOL PAV type of tilt-wing, compound, and multicopter. Wetted area and induced drag was calculated using OpenVSP and XFLR5 that are aircraft design and aerodynamic analysis software. The batteries used in the eVTOL PAV was assumed as Tesla 2170 batteries and flight ranges were calculated. Also, energy consumption and maximum flight time for the given mission profile including take-off and landing, cruising segments were compared for each eVTOL.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.37-37
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• 2000

복합재료는 높은 무게비 강도 및 강성뿐만 아니라 우수한 재료 특성 때문에 경량화와 구조적 안전성이 요구되는 항공기의 구조재로서 사용이 증대되고 있다. 소형 민용항공기는 구조적 안전성과 함께 제작과 정비, 유지보수의 용이성이 중요시된다. 본 연구에서는 복합재료를 구조재로 사용하였을 때의 성능변화와 경량화 등을 검토하기 위하여 기존의 알루미늄 합금을 이용하여 설계된 소형 프로펠러 경항공기 날개의 구조재로서 복합재료를 사용하여 재설계하였다. 날개의 기본 구조는 스킨, 스파, 웹으로 구성된 상자형 단면으로 설계하였으며 날개의 구조재로서 탄소/에폭시를 사용하여 상용 유한요소해석코드인 NISAII를 이용하여 굽힘, 좌굴 등의 응력해석을 수행하였고 기존 설계된 날개와의 성능비교를 위하여 알루미늄 합금으로 설계된 날개를 모델링하여 해석한 결과와 비교하였다. 비교결과 구조재로 탄소/에폭시를 사용하여 설계된 날개가 무게비 성능면에서 더 우수함을 확인하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.6
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• pp.509-516
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• 2007

Mathematical modeling and vibration control of a tiltrotor aircraft composite wing-rotor system are investigated in this study. A wing-mounted rotor can be tilted from the vertical position to a horizontal one, and vice versa. Effect of vibration control of the wing-rotor system via piezoelectricity is studied as a function of tilt angle, ply angle of composite wing and rotor's spin speed. Composite wing is modeled as a thin-walled box beam having a circumferentially uniform stiffness configuration that produces elastic coupling between flap-lag and between extension-twist behavior. Numerical simulations are provided and pertinent conclusions are outlined.

• Journal of Aerospace System Engineering
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• v.14 no.spc
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• pp.39-48
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• 2020

This paper deals with the process of estimating the environmental noise generated from the actual flying aircraft using the noise measurement results obtained through the wind tunnel test and verifying it through flight tests. In order to evaluate the environmental noise of an aircraft, noise tests and evaluations are generally conducted according to the procedures prescribed by the International Civil Aviation Organization (ICAO). In this paper, we introduced environmental noise evaluation method that can be applied to composite both fixed-wing aircraft and multi-copter, and introduced the evaluation method by experiment. This paper introduces the process of simulating the noise test results measured in the wind tunnel test using real flight test results. In addition, in consideration of flight operating conditions and noise measurement methods proposed by the ICAO, the effective perceived noise level (EPNL) was predicted by performing both the wind tunnel test and the aircraft flight test.

• Journal of Advanced Navigation Technology
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• v.26 no.6
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• pp.448-455
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• 2022

In this study, when establishing a UTM(UAS Traffic Management) system, a corridor must be set to separate the flight distance between unmanned aerial vehicles, and the size of the corridor was calculated in consideration of TSE(Total System Error). The flight data of the straight section and the turning section were collected using a hybrid vertical take-off and landing unmanned aerial vehicle. The flight data were derived from the TSE using the SQSM(Scalar Quantity Summation Method) method, and the impact on the straight and turning sections was analyzed by calculating in detail by NSE(Navigation System Error) and FTE(Flight Technical Error). The corridor size was calculated by referring to the TSE analysis results and PBN (Performance-based Navigation) manual.

• 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.