Earticle

Recent advances in autonomous flight, electric propulsion, and distributed architectures have enabled the rapid emergence of future air systems such as AAVs, UAVs, and eVTOL aircraft, whose software-intensive and autonomous operational characteristics differ fundamentally from those of conventional manned aircraft. This study analyzes the technical and operational characteristics of these systems and identifies structural gaps in existing airworthiness certification frameworks, discussing the applicability of performance-based certification, risk-based airworthiness approaches, and digital airworthiness concepts as practical directions for future certification reform.

Today's modern society faces traffic congestion with numerous cars, urbanization is rapidly progressing all over the world, and the number of large cities is increasing, so the traffic congestion problem is inevitably intensified. However, in order to improve traffic congestion, it is impossible to increase the supply of public transportation such as subways and buses indefinitely, and it is expected that ground transportation congestion will continue despite the expansion of roads and railways. An innovative transportation system is needed. UAM will be operated at the elevation of 300~600m in cities. However, there are no legal grounds on the acknowledgement of ownership of air space above land to what elevation and compensation in accordance with the limitation of such ownership, thereby inducing concerns for violation of constitution in the event of radical occurrence of disputes on the ownership of air space above land at the time of introduction of UAM. Accordingly, it is deemed that legislation of the ‘Regulations on the compensation for the use of air space above land for public interest project in accordance with the UAM operation’ and policy alternatives for this aspect is presented.

Humans have dreamed of being able to fly freely in the sky anytime, anywhere. People’s desire for a flying car is always the object of admiration of people from when airplanes were not commercialized until now, however it is gradually coming to reality. In fact there are few empirical studies in this field so far. this study examines the evolution process from a remote piloted vehicle, which is the first model of a drone, to a personal aerial vehicle (PAV) developed to improve today's traffic congestion. As a result, by examining the concept of drones and the development process of drones extensively, a more accurate policy should be presented on how drone-related laws and policies should be revised in the future. Therefore, through this study, it is believed that it will help to provide guidelines on which areas should focus on in revising the drone law.

The urban aerial mobility (UAM) system, such as drone taxi or air taxi, is one of future on-demand transportation networks. Among them, electric vertical takeoff and landing (eVTOL) is one of UAM systems that is for identifying the locations of passengers, flying to the positions where the passengers are located, loading the passengers, and delivering the passengers to their destinations. In this paper, we propose a distributed deep reinforcement learning where the agents are formulated as eVTOL vehicles that can compute the optimal passenger transportation routes under the consideration of passenger behaviors, collisions among eVTOL, and eVTOL battery status.

Urban air mobility (UAM) has recently attracted lots of attention as a solution to urban centralization and global warming. Electric vertical take-off and landing (eVTOL) is a concept that emerges as one of the promising and clean technologies for UAM. There are two difficult challenges for eVTOL aircraft to solve. One is how to improve the weight efficiency of aircraft, and the other is how to complete long-range missions for UAM’s flight scenarios. To approach these challenges, we propose a consolidated concept design of battery-fuel cell hybrid tiltrotor aircraft with a liquid hydrogen (LH2) fuel tank. The efficiency of a battery-fuel cell hybrid powertrain system on the designed eVTOL aircraft is compared to that of a battery-only powertrain system. This paper shows how much payload can increase and the flight scenario can be improved by hybridizing the battery and fuel cell and presenting a detailed concept of a cryogenic storage tank for LH2.

본 연구에서는 모듈형 PAV(Personal Air Vehicle)의 설계 및 Prototype 제작을 통해 기존 PAV의 활용성과 확장성에 대한 가능성을 확인하고자 한다. 모듈형 PAV는 비행을 담당하는 Aerial Module, 결합을 위한 Connector Module, 지상에서 구동되는 Ground Module, 그리고 운송용 Transport Module로 구성된다. Aerial Module 하단에 부착된 Connector Module을 통해 Transport Module이 탈부착 되는 방식이다. 실험 진행은 실제 비행이 가능한 1:8.5 비율의 소형 Prototype을 설계한 후 제작하여 비행 테스트를 했다. 비행 로그 분석 결과 기체는 Roll, Pitch, Yaw 각도에서 안정적인 자세 제어를 보였다. 또한 진동과 가속도 수치도 허용범위 내에 있는 것을 확인했다. 이를 통해 탈부착이 가능한 모듈형 PAV의 실현 가능성을 확인했다.

This study aims to evaluate the usability and scalability potential of modular PAV by designing and prototyping a modular PAV system. The modular PAV consists of an Aerial Module for flight, a Connector Module for combination, a Ground Module that operates on the ground, and a Transport Module for transportation. The Transport Module can be detached and attached via the Connector Module attached to the bottom of the Aerial Module. For the experiment, a small prototype with a scale of 1:8.5 capable of actual flight was designed, manufactured, and flight tested. The flight log analysis results showed that the airframe had stable attitude control in the Roll, Pitch, and Yaw angles. In addition, it was confirmed that the vibration and acceleration values w ere within the acceptable range. Through this, we confirmed the feasibility of a modular PAV that can be detached.

This study aims to determine the importance of each factor considered when operating a rotorcraft in a city. After identifying factors that could affect urban air mobility, we reviewed the influencing factors by applying an analytic hierarchy process (AHP). Level 1 classifies the essential factors of the urban operation of rotorcraft in nominal and off-nominal situations. The factors corresponding to the characteristics of each were composed of lower levels, such as Levels 2 and 3. Using this, the importance of influencing factors was analyzed and the most important factors were determined. The most influential factors of the urban operation of rotorcraft included engine failure, fire situations, and vehicle safety. Accordingly, an environment that can guarantee safe operation by considering the most influential factors in advance in an actual operation stage must be constructed.

미래 운송수단으로 거론되는 UAM을 중심으로 함께 주목받는 eVTOL 항공기의 양력과 항속속도 및 항속거리 증대를 위해 Tilt Rotor와 Tandem Wing 개념을 본 논문의 기체에 도입했다. 기체를 제작 및 비행 실험을 진행하여 비행 영상과 비행 로그를 확보했다. 비행 영상과 비행 로그를 분석한 결과 기체 모멘트가 과도하게 앞으로 쏠리는 현 상이 발생했고 자세가 회복되지 않음을 파악했다. 이에 XFLR5에서 날개 붙임각과 면적을 변경하며 기체의 세로안정 성을 확보하기 위한 최적의 피칭 모멘트 계수를 도출되도록 CATIA를 통해 설계된 기체를, XFLR5로 해석했다. 본 연구의 결과는 Tilt Rotor와 Tandem Wing이 적용된 기체가 안정적인 피칭 모멘트 계수를 가질 수 있도록 도움을 주며, 이를 통해 세로안정성을 더욱 향상할 수 있는 새로운 방안을 제시했다.

To improve the lift, cruise speed, and range of eVTOL aircraft, which are being considered as future transportation vehicles, this paper introduces the concepts of Tilt Rotor and Tandem Wing to the aircraft. We developed an aircraft and conducted flight experiments to obtain flight videos and flight logs. The results of the analysis of the flight videos and flight logs showed that the aircraft's moment was excessively forward and the attitude was not recovered. To address this problem, we modified the wing incidence angles and surface areas in XFLR5 to obtain the optimal pitching moment coefficients to ensure vertical stability. We then analyzed the redesigned aircraft, developed using CATIA, through XFLR5. The results of this study provide valuable insights, suggesting that the incorporation of Tilt Rotor and Tandem Wing designs can contribute to achieving stable pitching moment coefficients. This innovative approach offers a promising avenue to significantly enhance vertical stability in UAM vehicles, paving the way for future advancements in the field.

도심환경에서 운용하는 eVTOL(electric-powered Vertical Take-Off and Landing) UAM(Urban Air Mobility) 항공기는 복잡한 도심 속에서 버티포트 접근 및 착륙 시 조종사에게 높은 인지 및 조종 부담을 유발할 수 있다. 본 논문에서는 기체에 장착된 카메라를 활용한 자동 비행 시스템을 제안하여 조종사의 부담을 경감하고 운용 안정성을 향상시키고자 한다. 제안된 시스템은 전방 카메라를 이용해 실제 착륙 지점인 TLOF(Touchdown and Lift-Off)를 탐지하고, 추출된 특징점에 RANSAC(Random Sample Consensus) 알고리즘을 적용하여 TLOF와의 상대 거리 및 각도를 계산함으로써 접근을 수행한다. 착륙 단계에서는 하방 카메라로부터 얻은 TLOF 중심 픽셀과의 좌표 오차를 기반으로 착륙을 수행한다. 시뮬레이션의 경우 도심풍을 모사한 환경을 구성하였으며, 결과적으로 버티포트에 착륙하는 것을 확인하였다

electric-powered vertical take-off and landing(eVTOL) urban air mobility(UAM) aircraft operating in urban environments can impose high cognitive and control workload on pilots during vertiport approach and landing. This paper proposes an autonomous flight system using onboard cameras to reduce pilot workload and improve operational safety. The forward-facing camera detects the touchdown and lift-off(TLOF) and applies the random sample consensus(RANSAC) algorithm to the extracted feature points to estimate the relative distance and angle for approach. During the landing phase, the aircraft performs the final descent based on the pixel-coordinate error between the TLOF center and the downward-facing camera image. An urban wind simulation environment was configured. Tests were run in this environment, confirming the aircraft is successfully landing on the vertiport.

본 논문에서는 다양한 eVTOL (electric vertical take-off and landing) 항공기의 안전성 평가 수행을 위한 가변형 시뮬레이션 환경을 구축하고자 한다. eVTOL 항공기마다 적용되는 Inceptor, 항공기 동역학 모델, 제어기가 상이하므로, 이를 가변형으로 구성하여 eVTOL 항공기마다 안전성 시험 평가 시뮬레이션을 수행할 수 있도록 구성하였다. eVTOL 항공기의 안전성 평가 수행을 위한 시험 항목 및 성능 지표를 설정하였으며, 시험 항목별 시험절차에 따라 안전성 시험 평가 시 필요한 지상보조설비를 구상하여 시뮬레이션 환경에 구현하였다. 또한, 시뮬레이션 내 eVTOL 항공기의 데이터를 활용한 안전성 성능 분석을 위해 MATLAB/Simulink 기반의 시뮬레이션 비행데이터 수집 환경을 구축하고, 안전성 성능 분석을 위한 툴을 구현하였다. 최종적으로 본 논문에서 구현한 가변형 시뮬레이션 환경에서의 안전성 시험 비행 수행 및 성능 분석을 수행하였으며, 정상적으로 수행되는 것을 확인함으로써 시뮬레이션 환경을 검증하였다.

This paper aims to establish a reconfigurable flight simulation environment to conduct safety evaluation of various electric vertical take-off and landing (eVTOL) aircraft. Since the inceptor, aircraft dynamics model, and controller applied to each eVTOL aircraft are different, it was configured to be variable so that a simulation can be executed for each eVTOL aircraft. Test elements and performance indicators were set to perform safety evaluation of eVTOL aircraft. Ground auxiliary equipments were designed and implemented in a simulation environment according to test procedures for each test element. In addition, to analyze safety performance, a simulation flight data collection environment based on MATLAB/Simulink and a tool for safety performance analysis were implemented. Test flight and analysis were conducted in the implemented simulation environment in this paper. Finally, this study shows the environment was verified by confirming that it was performed normally.

전 세계의 많은 대도시는 도시화에 따른 지상 및 지하 교통망이 포화되고 있다. 또한 지구온난화 방지를 위한 탄소배출 규제가 더욱 엄격해지고 있으며 이러한 문제의 해결책으로 복잡한 도심에서도 운행 가능한 eVTOL이 차세대 친환경 교통수단으로 각광받고 있다. 본 연구에서는 eVTOL을 멀티콥터형, 양력+순항형, 추력편향형으로 분류하여 각 유형별 eVTOL들의 호버 효율과 회전판 하중을 계산하였으며 공력해석 프로그램인 OpenVSP, Fluent와 JavaProp을 이용하여 각국의 감항당국 및 우버 사에서 발표한 보고서를 바탕으로 가까운 미래에 실현될 eVTOL의 원활한 운행에 필요한 배터리 비에너지를 계산하고 분석하였다.

In many metropolitan cities around the world, ground and underground transportation networks are saturated due to urbanization. In addition, regulations on carbon emissions to prevent global warming are becoming stricter, and eVTOL, which will be operating in complex cities, is gaining popularity as the next generation of eco-friendly transportation. In this study, the hover lift efficiency and disc loading of eVTOLs for each type were calculated by classifying eVTOLs into following types: multicopter, lift+cruise, and vectored thrust. In addition, using the aerodynamic analysis programs OpenVSP, Fluent and Javaprop, the specific battery energy required for the smooth operation of eVTOL, which will be realized in the near future, was calculated and analyzed base on reports published by Uber and airworthiness authorities of each country.

eVTOL (electric vertical take-off and landing) 항공기의 안정적인 도심 비행을 위해서는 조종성과 안정성 확보가 필수적이다. 하지만 기존 유인항공기와 다른 특성을 가진 eVTOL 항공기에 대한 명확한 조종성 규격이 마련되지 않았다. 따라서, 본 논문에서는 기존 유인 항공기의 조종성 규격을 바탕으로 eVTOL 항공기에 적합한 조종성 평가항목을 식별하고, 평가를 통해 예측 조종성 기준을 만족하는 제어시스템을 설계하였다. Lift-Cruise 형상의 eVTOL 항공기에 SVO (simplified vehicle operation) 조종 법칙과 SCAS (stability and control augmentation System) 기반 제어 법칙을 적용하였다. CONDUIT (control designer's unified interface)을 활용하여 level 1 기준을 충족하는 것을 확인하였고, 검증을 하기 위해 HQTE (handling qualities task elements)를 바탕으로 X-Plane 기반의 시뮬레이션 환경에서 할당 조종성 평가를 수행하여 조종성이 확보된 제어시스템을 설계하였다.

To ensure stable urban flight of electric vertical take-off and landing(eVTOL) aircraft, securing handling qualities and stability is essential. However, clear handling qualities standards for eVTOL aircraft, which have different characteristics from conventional manned aircraft, have not yet been established. Therefore, this paper identifies handling qualities evaluation criteria suitable for eVTOL aircraft based on the handling qualities standards for manned aircraft and designs a control system that meets the predicted handling qualities criteria through evaluation. simplified vehicle operation(SVO) control laws and stability and control augmentation system(SCAS)-based control laws were applied to the lift-cruise configuration eVTOL aircraft. Using control designer's unified interface(CONDUIT), it was confirmed that the level 1 standard was met, and to validate the system, assigned handling qualities evaluation was performed using handling qualities task elements(HQTE) in an X-Plane based simulation environment, resulting in the design of a control system that ensures handling qualities.

항우연은 eVTOL 항공기의 개념설계 및 기본설계를 위한 설계프레임워크를 개발하고 있다. 오픈소스 SUAVE 패키지를 활용하여 틸트 프롭 및 리프트 프롭을 갖는 Lift-Tilt 개념의 전기수직이착륙기에 대한 저충실도 임무분석도구를 개발하였다. 그 개발을 위하여 SUAVE의 프롭성능해석 기능을 검토하였다. 매 임무 세그먼트에서 트림해를 자동적으로 찾기 위해 병렬처리 및 실험계획법을 통한 전역최적화 기법을 적용한 알고리듬을 구현하였다. 동 도구를 사용하여 1인승급 전기추진 수직이착륙 유무인 겸용 개인항공기(OPPAV)의 임무분석을 수행하고 동 항공기의 기본설계데이터와 비교하였다.

KARI (Korea Aerospace Research Institute) is developing a design framework for the concept and preliminary design of eVTOL aircrafts. A low fidelity mission analysis tool was developed for the eVTOL aircrafts of Lift-Tilt Concept, which have tilt propellers and lift propellers, using open source SUAVE package. For its development, a review for the propeller performance analysis functionality was made. To find the trim solution at each mission segment automatically, an algorithm is implemented, using a global optimization technique through parallel processings and DOE(design of experiment). Using the tool, the one seated eVTOL OPPAV(optionally piloted personal air vehicle) was modeled and evaluated, which results were compared with the preliminary design data.

본 연구는 PAV 국내 상용화를 위한 eVTOL의 발전에 필수적인 기술 트리를 개발하기 위하여 실시되었다. eVTOL에 특화된 기술 개발 전략 수립 관련 연구가 부족하다는 것을 고려하여 법적, 제도적인부분들을 제외한, eVTOL 기체 완성을 목표로 기술 트리를 제작했다. 문헌연구를 통해 단일모드의eVTOL 형식의 PAV가 지배 제품임을 확인하였고 이에 따라 항공 공학적 접근을 사용하여 eVTOL을중심으로 상위 기술 항목과 하위 기술 항목으로 구성된 1차 eVTOL 기술 트리를 작성하였다. 그 후, 전문가 인터뷰를 진행하여 eVTOL 기체 완성을 위한 상세 사양에 대한 의견들을 수집했고 1차 기술트리에 대한 10명의 전문가 의견을 바탕으로 정성 및 정량 분석을 실시하였다. 이를 바탕으로 1차 기술 트리를 수정 및 보완하여 1) 추진, 2) 공력, 3) 배터리․동력원, 4) 소재․구조, 5) 제어․자율비행, 6) 항공전자․통신의 상위 항목으로 구성된 최종 eVTOL 기술 트리를 제안하였다. 각각의 하위 기술항목들에 대해서는 본문에서 자세히 설명하였다. 본 연구에서 제안된 eVTOL 기술 트리는 기술 항목들의 핵심 기술에 대해 통합적으로 고려할 수 있으며, 향후 국내 PAV 산업의 발전을 위한 기술연구투자 우선순위 수립에 기여할 수 있을 것이다.

This study aims to identify and develop a technology tree necessary to eVTOL development for PAV commercialization in Korea. Considering the fact that little is known about the technological development strategies of eVTOL, this study attempted to design the technology tree with the purpose of completing eVTOL aircraft construction, excluding laws and regulations. The analysis consists of a literature review and interviews with 10 experts from the PAV industry to build an eVTOL-focused technology tree. Specifically, single mode eVTOL was found to be a dominant design in the PAV industry by using comprehensive literature review. With this information, the study used an aerospace engineering approach to create the first version of eVTOL-focused technology tree. Expert opinions on eVTOL’s detailed specifications were gathered through the interviews. Quantitative and qualitative research was then conducted, separately or together, based on the respondents’ assessments of the initial eVTOL-focused technology tree. This resulted in the creation of a more sophisticated version of eVTOL-focused technology tree comprising of six main categories: 1) propulsion, 2) aerodynamics, 3) battery?power, 4) material?structure, 5) control?autonomous flight, 6) avionics?communication. Further information with regard to subcategories in each main category is provided in the text. The finally suggested eVTOL-focused technology tree facilitates an integrated analysis of core technologies and has potential to contribute to further studies of determining the priorities for the investment in research and development of the domestic PAV industry.

A large amount of time and cost is consumed due to congestions caused by an increasing number of cars which results in a lot of emissions. To overcome these problems, a new electric vertical takeoff and landing (eVTOL) aircraft is being considered. Since vertical take off and landing without a separate runway is realized and electricity is used as a power source, it could solve the saturated ground traffic congestions without emissions. In this paper, the initial sizing was performed based on the Nexus 6HX of Belltextron which is a tilt-ducted fan type. In this study, the electric propulsion system that only uses battery was implemented instead of current Nexus 6HX hybrid electric propulsion. Aerodynamic analyses were performed using OpenVSP and XFLR5. Power-to-weight ratio, wing loading, estimated weight were calculated with these analyses.

본 연구에서는 반복 설계를 통한 틸트 + 정지로터형 전기추진 수직이착륙 항공기(eVTOL)의 개념설계를 수행하였다. 현대자동차의 S-A1을 기준 형상으로 하여 도심항공모빌리티(UAM)의 개념을 사용하여 임무 형상을 정의하고 OpenVSP, XFLR5 소프트웨어를 사용하여 형상 설계와 공력해석을 수행하였다. 설계된 형상을 바탕으로 필요 동력을 추정한 뒤 배터리의 요구성능과 최대 이륙 중량(MTOW)을 계산하였다. Microsoft Excel과 Visual Basic Application을 사용해 반복적으로 계산하였으며, 이 과정에서 전기모터의 중량 추정식을 새롭게 고안하였다. 또한 자동화된 프로그램을 이용하여 eVTOL의 설계변수별 민감도 분석을 수행하였다.

In this study, the conceptual design of a tilt + stopped rotor type electric vertical take-off and landing (eVTOL) aircraft was performed using design iteration. Based on Hyundai Motor's S-A1, the mission profile was defined using the concept of urban air mobility (UAM), and configuration design and aerodynamic analysis were performed using OpenVSP and XFLR5 software. After estimating the required power for the designed eVTOL, the required performance of the battery and the maximum take-off weight (MTOW) were calculated. . It was iteratively calculated using Microsoft Excel and Visual Basic Application, and a new electric motor weight estimation formula was derived. Also, the sensitivity analyses of each design variables of an eVTOL was performed using the automated program.

자동차 대수의 증가로 인한 지상 교통의 혼잡을 극복하기 위해 많은 회사들이 새로운 방식의 운송 수단인 미래형 개인항공기(PAV)를 제안하였다. 미래형 개인항공기 중에서도 전기를 동력으로 사용하고 수직 이착륙이 가능한 전기수직이착륙(eVTOL)항공기가 주목을 받고 있으며 그러한 항공기들의 형상은 멀티콥터형에서 틸트 덕티드팬까지 다양하다. 본 연구에서는 eVTOL 유형별 장단점 등 특성을 분석하였다. 틸트날개형, 복합형, 멀티콥터형의 대표적인 eVTOL PAV인 바하나, 오로라, 볼로콥터에 대해 구성성분 합계 방식을 사용하여 유해항력을 구하였으며, 항공기 설계 및 공력 해석 프로그램인 OpenVSP와 XFLR5 프로그램을 사용하여 표면적과 유도항력을 구하였다. eVTOL PAV에 사용되는 배터리는 테슬라 2170 배터리로 가정하고 항속거리를 계산하였다. 또한 각 eVTOL에 대해 이착륙 및 순항을 포함한 임무형상별로 에너지소모 및 최대 비행시간을 계산하여 비교하였다.

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.

도심의 심각한 교통체증을 해결하기 위한 수단으로 도심항공교통(UAM, Urban Air Mobility)이 등장하고 있다. UAM용 비행체는 화석연료를 사용하지 않고 전기 배터리를 동력원으로 하는 전기동력 수직이착륙기(eVTOL)이다. eVTOL의 안정성을 담보하기 위한 기술 기준은 아직 마련되지 않았다. eVTOL 선진국이라는 유럽과 미국에서도 기존의 항공기 기술 기준을 응용하여 사용하고 있다. 유럽과 미국의 항공기 감항 기준과 eVTOL에 대해 적용하고 있는 기준을 살펴보고 우리나라의 eVTOL 기술 기준 정립 방향을 모색해 보고자 한다.

Urban Air Mobility (UAM) is emerging as a means to solve serious traffic congestion in the city. The UAM aircraft is an electrically powered vertical takeoff and landing aircraft (eVTOL) powered by electric batteries without using fossil fuels. Technical standards have not yet been established to ensure the stability of eVTOL. Europe and the United States, which are advanced eVTOL countries, are also using existing aircraft technology standards. I would like to look at the aircraft surveillance standards in Europe and the United States and the standards applied to eVTOL, and explore the direction of establishing eVTOL technology standards in Korea.

대도시 도심의 교통 정체를 해결하기 위한 방법의 하나로 전기수직이착륙 개인항공기(eVTOL PAV)를 활용한 도심항공 모빌리티(UAM)의 관심이 증가하고 있다. 도심항공 모빌리티에 사용할 비행체인 eVTOL은 추진방식에 따라 복합형, 틸트 로터형, 틸트 날개형, 틸트 덕티드 팬형, 멀티콥터형으로 분류된다. 본 연구에서는 멀티콥터형인 에어버스사의 시티에어버스를 기본 모델로 주어진 임무 형상에 맞게 역설계 기법을 사용하여 기본 개념설계를 수행하였다. 공력해석 프로그램인 OpenVSP를 사용하여 표면적과 양항비, 항력계수를 계산하였다. 각 임무 구간별 소요되는 동력을 계산하였고, 그에 맞는 배터리와 모터를 비교하여 선정하였다. 또한 eVTOL 구성품별 중량을 추정하여 전체 총 중량을 예측하였다.

As a means of solving traffic congestion in the downtown of large city, the interest in urban air mobility (UAM) using electric vertical take-off landing personal aerial vehicle (eVTOL PAV) is increasing. eVTOL configurations that will be used for UAM are classified by lift-and-cruise, tilt rotors, tilt-wings, tilted-ducted fans, multicopters, depending on propulsion types. This study tries to perform preliminary conceptual design for a given mission profile using reverse engineering techniques by taking the multicopter type Airbus's CityAirbus as a basic model. Wetted area, lift to drag ratio, drag coefficients were calculated using the OpenVSP which is an aerodynamic analysis software. The power required for each mission section of CityAirbus were calculated, and the corresponding battery and motor were selected. Also, total weight was predicted by estimating component weights of eVTOL.

최근 많은 나라 대도시의 교통체증과 더불어 지구온난화로 인해 차세대 친환경 교통수단인 eVTOL이 각광받고 있다. 본 연구에서는 많은 유형의 eVTOL 중 고정로터와 틸트로터가 결합된 복합형 eVTOL인 현대자동차 S-A1의 외부형상을 벤치마킹하여 역설계 기법을 활용하여 기본 형상을 구현하였다. CATIA를 사용하여 기본 형상을 구현한 후 항공기 설계 및 공력해석 프로그램인 OpenVSP, XFLR5를 사용하여 공력해석을 수행하였고 비교분석을 통해 익형과 붙임각, 상/하반각을 선택한 후 항공기 표면적 및 항력, 양력을 계산하였다. 또한 주어진 임무형상을 수행하기 위한 필요 동력을 산정하고 추정식과 자료조사를 통하여 구성품과 전체 무게를 추정하였다.

Recently, eVTOL, the next-generation of eco-friendly transportation, has been in the spotlight due to global warming along with traffic jams in large cities of many countries. This study benchmark the external features of Hyundai Motors S-A1, a compound eVTOL combined fixed and tilt rotors among many types of eVTOLs, to create the basic configuration using reverse design techniques. Basic configurations were created using CATIA and aerodynamic analyses were performed using the aircraft design and aerodynamic analysis programs, OpenVSP, XFLR5, and the aircraft wetted area, drag, and lift were calculated after selecting the airfoil, incidence angle, and dihedral and anhedral angles through trade study. Also, required powers were estimated for completing the given mission profile and components weight and the total weight were predicted using the estimation formula and data survey.