• Title/Summary/Keyword: 전기 수직이착륙기

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A Study on the Certification System for eVTOL Aircraft (전기추진 수직이착륙 항공기 인증제도에 대한 고찰)

  • Lim, Daejin;Yee, Kwanjung
    • Journal of Aerospace System Engineering
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    • v.15 no.3
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    • pp.20-29
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    • 2021
  • As the feasibility of urban air mobility (UAM) service using electric vertical take-off and landing (eVTOL) aircraft increases due to aircraft electrification, distributed propulsion, and artificial intelligence technologies, the U.S. and European aeronautical societies have been improving their certification system and regulations for the type certification of eVTOL. The improved certification system is expected to be ready in the near future, after the European Union Aviation Safety Agency (EASA) proposed the VTOL Special Condition, SC-VTOL in 2019. However, the current domestic certification system is still insufficient to properly respond to eVTOL. This study investigated the development trends of foreign eVTOL and certification systems, identified considerations to improve the domestic certification system, and proposed the measures for type certificates and type certificates validation of eVTOL based on the comparison between SC-VTOL and Korea airworthiness standards (KAS).

Actuator Mixer Design in Rotary-Wing Mode Based on Convex Optimization Technique for Electric VTOL UAV (컨벡스 최적화 기법 기반 전기추진 수직이착륙 무인기의 추진 시스템 고장 대처를 위한 회전익 모드 믹서 설계)

  • Jung, Yeondeuk;Choi, Hyungsik
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.48 no.9
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    • pp.691-701
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    • 2020
  • An actuator mixer design using convex optimization technique situation where the propulsion system of an electric VTOL UAV during vertical take-off and landing maneuvers is proposed. The attainable control set to analyze the impact from failure of each motor and propeller can be calculated and illustrated using the properties of the convex function. The control allocation can be defined as a convex function optimization problem to obtain an optimal solution in real time. The mixer is implemented using a convex optimization solver, and the performance of the control allocation methods is compared to the attainable control set. Finally, the proposed mixer is compared with other techniques with nonlinear sux degree-of-freedom simulation.

Development of Mission Analysis Tool for eVTOL Aircrafts of Lift-Tilt Concept (Lift-Tilt 개념의 eVTOL 항공기 임무 분석 도구 개발)

  • Paek, Seung-Kil;Chae, Sanghyun;Kang, Hee Jung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.10
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    • pp.859-870
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    • 2021
  • 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.

Study on Performance Analyses on Coaxial Co-rotating Rotors of e-VTOL Aircraft for Urban Air Mobility (도심 항공 교통을 위한 전기동력 수직 이착륙기의 동축 동회전 로터의 성능해석 연구)

  • Lee, Yu-Been;Park, Jae-Sang
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.12
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    • pp.1011-1018
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    • 2021
  • This numerical study conducts the modeling and the hover performance analyses of coaxial co-rotating rotor(or stacked rotor), using a rotorcraft comprehensive analysis code, CAMRAD II. The important design parameters such as the index angle and axial spacing for the coaxial co-rotating rotor are varied in this simulation study. The coaxial co-rotating rotor is trimmed using the torque value of the upper rotor of the previous coaxial counter-rotating rotor or the total thrust value of the previous coaxial counter-rotating rotor in hover. The maximum increases in the rotor thrust is 1.84% for the index angle of -10° when using the torque trim approach. In addition, the maximum decreases in the rotor power is 4.53% for the index angle of 20° with the thrust trim method. Thus, the present study shows that the hover performance of the coaxial co-rotating rotor for e-VTOL aircraft can be changed by the index angle.

Feasibility Study of a Series Hybrid-Electric Propulsion System for a Fixed Wing VTOL Unmanned Aerial Vehicle (고정익 수직이착륙 무인항공기를 위한 하이브리드-전기 추진시스템의 타당성 연구)

  • Kim, Boseong;Bak, Jeonggyu;Yun, Senghyun;Cho, Sooyoung;Ha, Juhyung;Park, Gyusung;Lee, Geunho;Won, Sunghong;Moon, Changmo;Cho, Jinsoo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.43 no.12
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    • pp.1097-1107
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    • 2015
  • General VTOL aircraft uses gas turbine engine which has high power to weight ratio. However, in the VTOL UAV in small sector, the gas turbine as a prime mover is not adequate because of the limitation of the high fuel consumption ratio of the gas turbine. In this research, The Series Hybrid-Electric Propulsion System(SHEPS) has been proposed and technology survey & comparison analysis has conducted to constitute propulsion system for engine, electric motor and battery. To achieve this object a 65kg-class P-UAV from "Company I" was used. And to estimate the validity of power control algorithm and developed power management control, Matlab/simulink$^{(R)}$ has been used for the simulation. As a result, the developed algorithm worked comparatively well and the research has predicted that SHEPS was satisfied enough for 7 hour of endurance for mission profile.

Analysis of the Total System Error Correlation of Hybrid Fixed-Wing UAV (Unmanned Aerial Vehicle) according to Environmental Factor (환경요인에 따른 복합형 수직이착륙 무인항공기의 통합 시스템 오차 상관도 분석)

  • Songgeun Eom;Jeongmin Kim;Jeonghwan Oh;Dongjin Lee;Doyoon Kim;Sanghyuck Han
    • 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.

Computational Simulation of Coaxial eVTOL Aircraft in Ground Effect (동축 반전 전기동력 수직이착륙기의 지면 효과에 대한 전산해석)

  • Yang, Jin-Yong;Lee, Hyeok-Jin;Myong, Rho-Shin;Lee, Hakjin
    • 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.

Aeroacoustic Analysis of UAM Aircraft in Ground Effect for Take-off/Landing on Vertiport (버티포트 이착륙을 고려한 지면 효과를 받는 UAM 항공기에 대한 공력소음 해석 연구)

  • Jin-Yong Yang;Hyeok-Jin Lee;Min-Je Kang;Eunmin Kim;Rho-Shin Myong;Hakjin Lee
    • Journal of Aerospace System Engineering
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    • v.17 no.2
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    • pp.26-37
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    • 2023
  • Urban air mobility (UAM) is being developed as part of the next-generation aircraft, which could be a viable solution to entrenched problems of urban traffic congestion and environmental pollution. A new airport platform called vertiport as a space where UAM can take off and land vertically is also being introduced. Noise regulations for UAM will be strict due to its operation in a highly populated urban area. Ground effects caused by vertiport can directly affect aerodynamic forces and noise characteristics of UAM. In this study, ground effects of vertiport on aerodynamic loads, vorticity field, and far-field noise were analyzed using Lattice-Boltzmann Method (LBM) simulation and Ffowcs Williams and Hawkings (FW-H) acoustic analogy with a permeable surface method.

Battery Sensitivity Analysis on Initial Sizing of eVTOL Aircraft (전기 추진 수직이착륙기의 초기 사이징에 대한 배터리 민감도 분석)

  • Park, Minjun;Choi, Jou-Young Jason;Park, Se Hwan
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.50 no.12
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    • pp.819-828
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    • 2022
  • Sensitivity of aircraft sizing depending on battery performance was studied for a generic quad tilt rotor type electric vertical takeoff and landing vehicle. The mission requirements proposed by Uber Elevate and NASA were used for initial sizing, and the calculated gross weight is ranged between 5,000lb and 11,000lb for battery specific energy range of 200-400Wh/kg in pack level and continuous discharge rate range of 4-5C. For the assumed gross weight of 7,000lb, the required battery performance was calculated with two different criteria: available power and energy, and the effects of battery specific energy and discharge rate are analyzed. The maximum discharge rate is also recommended considering failure cases such as one battery pack inoperative and one prop rotor inoperative.

Disturbance Observer and Time-Delay Controller Design for Individual Blade Pitch Control System Driven by Electro-Mechanical Actuator (전기-기계식 구동기 기반 개별 블레이드 피치 조종 시스템의 제어를 위한 외란 관측기와 시간 지연제어기 설계)

  • Jaewan Choi;Minyu Kim;Younghoon Choi
    • Journal of Aerospace System Engineering
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    • v.18 no.1
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    • pp.29-36
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    • 2024
  • Recently, the concept of Urban Air Mobility (UAM) has expanded to Advanced Air Mobility (AAM). A tilt rotor type of vertical take-off and landing aircraft has been actively studied and developed. A tilt-rotor aircraft can perform a transition flight between vertical and horizontal flights. A blade pitch angle control system can be used for flight stability during transition flight time. In addition, Individual Blade Control (IBC) can reduce noise and vibration generated in transition flight. This paper proposed Disturbance Observer Based Control (DOBC) and Time Delay Control (TDC) for individual blade control of an Electro-Mechanical Actuator (EMA) based blade pitch angle control system. To compare and analyze proposed controllers, numerical simulations were conducted with DOBC and TDC.