• Title/Summary/Keyword: Vertical Take Off and Landing

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Optimal UAM Route Planning with Digital Twin : Casestudy of Gangneung City

  • Ahn, Seunghyo;Kim, Changyoon;Kim, Gihong
    • KSCE Journal of Civil and Environmental Engineering Research
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    • v.44 no.5
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    • pp.733-741
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    • 2024
  • Urban Air Mobility is gaining attention as a solution to traffic congestion and air pollution in large cities, but Gangneung, the case area of this study, is a medium-sized city focusing on tourism and connectivity with other public transport rather than congested traffic. Introducing UAM here focuses on integrating aircraft that carry people, vertiports for vertical take-off and landing, and corridors through which UAM can fly. While research on aircraft and vertiports is actively conducted, studies on corridors are still lacking. Thus, this study selected a route in Gangneung, a medium-sized city in Gangwon Special Self-Governing Province, that allows UAM flights with minimal risk. For this, a safety distance specific to building heights was determined, and the damage radius in case of aircraft crashes was calculated to select the route with the least possible damage during crash or collision incidents. For analysis, aerial photos and digital maps of Gangneung City, along with building information data, were used to create high-resolution orthophotos and digital elevation models. Based on the created data, GIS-based spatial analysis and three-dimensional visualization were conducted, and a suitable UAM route for Gangneung City was determined.

Design of Lateral Fuzzy-PI Controller for Unmanned Quadrotor Robot (무인 쿼드로터 로봇 횡 방향 제어를 위한 Fuzzy-PI 제어기 설계)

  • Baek, Seung-Jun;Lee, Deok-Jin;Park, Jong-Ho;Chong, Kil-To
    • Journal of Institute of Control, Robotics and Systems
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    • v.19 no.2
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    • pp.164-170
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    • 2013
  • Quadrotor UAV (Unmanned Aerial Vehicle) is a flying robotic platform which has drawn lots of attention in the recent years. The attraction comes from the fact that it is able to perform agile VTOL (Vertical Take-Off Landing) and hovering functions. In addition, the efficient modular structure composed of four electric rotors makes its design easier compared to other single-rotor type helicopters. In many cases, a quadrotor often utilizes vision systems in order to obtain altitude control and navigation solution in hostile environments where GPS receivers are not working or deniable. For carrying out their successful missions, it is essential for flight control systems to have fast and stable control responses of heading angle outputs. This paper presents a Fuzzy Logic based lateral PI controller to stabilize and control the quadrotor vehicle equipped with vision systems. The advantage of using the fuzzy based PI controller lies in the fact that it could acquire a desired output response of a heading angle even in presence of disturbances and uncertainties. The performance comparison of the newly proposed Fuzzy-PI controller and the conventional PI controller was carried out with various simulation results.

PSO-SAPARB Algorithm applied to a VTOL Aircraft Longitudinal Dynamics Controller Design and a Study on the KASS (수직이착륙기 종축 제어기 설계에 적용된 입자군집 최적화 알고리즘과 KASS 시스템에 대한 고찰)

  • Lee, ByungSeok;Choi, Jong Yeoun;Heo, Moon-Beom;Nam, Gi-Wook;Lee, Joon Hwa
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.24 no.4
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    • pp.12-19
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    • 2016
  • In the case of hard problems to find solutions or complx combination problems, there are various optimization algorithms that are used to solve the problem. Among these optimization algorithms, the representative of the optimization algorithm created by imitating the behavior patterns of the organism is the PSO (Particle Swarm Optimization) algorithm. Since the PSO algorithm is easily implemented, and has superior performance, the PSO algorithm has been used in many fields, and has been applied. In particular, PSO-SAPARB (PSO with Swarm Arrangement, Parameter Adjustment and Reflective Boundary) algorithm is an advanced PSO algorithm created to complement the shortcomings of PSO algorithm. In this paper, this PSO-SAPARB algorithm was applied to the longitudinal controller design of a VTOL (Vertical Take-Off and Landing) aircraft that has the advantages of fixed-wing aircraft and rotorcraft among drones which has attracted attention in the field of UAVs. Also, through the introduction and performance of the Korean SBAS (Satellite Based Augmentation System) named KASS (Korea Augmentation Satellite System) which is being developed currently, this paper deals with the availability of algorithm such as the PSO-SAPARB.

Flow Analysis around Tilt-rotor Aircraft at Various Tilt Angles (틸트각 변화에 따른 틸트로터 항공기 주위의 유동해석)

  • Kim, Su-Yean;Choi, Jong-Wook
    • Journal of the Korean Society of Visualization
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    • v.9 no.2
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    • pp.40-47
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    • 2011
  • Tilt-rotor aircraft can be used in various fields because they have the capabilities of the vertical take-off and landing and the high-speed cruise flight. In the present study, the flow analysis of a tilt-rotor aircraft is conducted at various tilt angles. The lift and drag forces of the tilt-rotor aircraft are obtained and the wakes by the rotor-blade are visualized. The result shows that the rotor-blade affects the lift force in a hovering mode and the main wing has an influence on the lift force in a cruise mode. Additional thrust is required at the tilt angle of around 40 degree due to the least lift force. The drag force is dependent on the rotor-blade at overall tilt angles. The minus drag force appears between the tilt angles of 90 degree and 55 degree. Also, the drag force is dramatically increased at the other tilt angles. The wake by rotor-blade affects the flow around the fuselage of the tilt-rotor aircraft at the tilt angles of 75 degree and 60 degree.

Design and Control of a Quad-Rotor (쿼드로터 비행체의 설계 및 제어)

  • Shim, Sanghyun;Kim, Ji-Chul;Yang, Sungwook;Cheon, Dong-Ik;Lee, Sangchul;Oh, Hwa-Suk;Kang, Min-Young;Keum, Dong-Kyo
    • Journal of Aerospace System Engineering
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    • v.3 no.1
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    • pp.36-41
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    • 2009
  • Quad-rotor is one kind of a rotorcraft in Unmanned Aerial Vehicle (UAV), which consists of four rotors in total and fixed-pitch blades located at the four corners. This vehicle is emerging as popular platform for UAV research due to the simplicity of its construction, the ability of hovering and the vertical take-off and landing (VTOL) capability, etc. Because of those specific capabilities, this vehicle can be applied to many fields: search and rescue, mobile sensor networks, fire observation, etc. However a quad-rotor is much affected by the disturbance due to the characteristics of structure. So this vehicle needs attitude control for stabilizing. In this paper, we design the control law for automatic stabilization. The PID controller is used to control a brushless DC motor. And an accelerometer is used to measure the roll and pitch angles of a quad-rotor.

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Numerical Estimation of Heat flux on the Deck Exposed to the High Temperature Impinging Jet of VTOL Vehicle (수직 이착륙기의 고온 고속 배기열에 의한 함정 갑판의 열유속 계산을 위한 수치모델)

  • Jang, Hosang;Hwang, Seyun;Choi, Wonjun;Lee, Jang Hyun
    • Journal of the Korea Institute of Military Science and Technology
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    • v.21 no.1
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    • pp.74-85
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    • 2018
  • This study has analyzed the convective heat transfer on the deck exposed to the high-temperature impingement exhausting from a VTOL vehicle. The heat flow of the impingement on the deck is modeled by the convection heat transfer. The convective heat flux generated by the hot impinging jet is investigated by using both convective heat transfer formulation and conjugate heat transfer formulation. Computational fluid dynamics(CFD) code was used to compute the heat flux distribution. The RANS equation and the k-e turbulence model were used to analyze the thermal flow of the impinging jet. The heat flux distribution near the stagnation zone obtained by the conjugate heat transfer analysis shows more reasonable than the convective heat transfer analysis.

A Study on the Prevention of Bird Collision in UAM (UAM 조류 충돌 방지대책 수립에 관한 연구)

  • Daniel Kim;Hee-duk Cho;Seung-woo Lee;Jae-woo Kim
    • Journal of Advanced Navigation Technology
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    • v.28 no.3
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    • pp.338-347
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    • 2024
  • This paper deals with the study of bird collision avoidance measures in UAM operations from an operator's perspective. Urban air traffic is defined as a next-generation transportation system that uses environmentally friendly electric vertical take-off and landing (eVTOL) aircraft to provide transportation services between key points within and around urban centers. For the successful establishment of the UAM industry, it is necessary to ensure safety issues that determine public acceptance. Among the hazards that can occur in aviation operations, preventing bird collisions in urban environments is a measure that can greatly secure operational safety and public acceptance. In addition to physical measures, procedural control measures are required to prevent bird strikes. In order to ensure the safety of UAM operations, this study aims to provide a direction for the establishment of UAM bird collision prevention measures by categorizing bird collision prevention measures into physical and procedural methods and flight sections such as takeoff, landing, and corridor sections. Through this, we hope to contribute to the improvement of the safety of the urban air traffic operation system.

Aerodynamic Design of SUAV Flaperon (스마트무인기 플래퍼론 공력설계)

  • Choi, Seong-Wook;Kim, Jai-Moo
    • 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.

A Study on Multi-Fault Diagnosis for Turboshaft Engine of UAV Using Fuzzy and Neural Networks (퍼지 및 신경망을 이용한 무인 항공기용 터보축 엔진의 다중손상진단에 관한 연구)

  • Kong, Chang-Duk;Ki, Ja-Young;Kho, Seong-Hee;Koo, Young-Ju;Lee, Chang-Ho
    • 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.

Gas Turbine Engine Based Hybrid Propulsion System Modeling and Simulation (가스터빈엔진 기반 하이브리드 추진시스템 모델링 및 시뮬레이션)

  • Lee, Bohwa;Kim, Chuntaek;Jun, Sangook;Huh, Jae-Sung;Kim, Jae-Hwan
    • Journal of the Korean Society of Propulsion Engineers
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    • v.26 no.3
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    • pp.1-9
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    • 2022
  • The aircraft targeted in this study is a vertical take-off and landing aircraft with 4 to 5 passengers, and the propulsion system for the aircraft is a distributed hybrid propulsion system that uses a gas turbine engine and a battery pack as the main power source to supply the power required by multiple motors. In this study, a design/analysis platform for a hybrid propulsion system was developed using the MATLAB/Simulink program based on the preliminary design results. Through simulation analysis, the output characteristics and operating range of each power source according to the mission profile were confirmed, and through this, the feasibility of the preliminary design result was confirmed.