Статті в журналах: "Electric VTOL"

1

Bacchini, Alessandro, and Enrico Cestino. "Electric VTOL Configurations Comparison." Aerospace 6, no. 3 (February 28, 2019): 26. http://dx.doi.org/10.3390/aerospace6030026.

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In the last ten years, different concepts of electric vertical take-off and landing aircrafts (eVTOLs) have been tested. This article addresses the problem of the choice of the best configuration. VTOLs built since the fifties are presented and their advantages, disadvantages, and problems are discussed. Three representative eVTOLs, one for each main configuration, are compared on five main parameters and three reference missions. The parameters are disk loading, total hover time, cruise speed, practical range, and flight time. The performance of the eVTOLs on the urban, extra-urban, and long-range mission is evaluated computing the time and energy required. The results show that the best configuration depends on the mission. The multirotor is more efficient in hover. The vectored thrust jet is more efficient in cruise and has a higher range. The lift + cruise is a compromise.

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2

Zong, Jianan, Bingjie Zhu, Zhongxi Hou, Xixiang Yang, and Jiaqi Zhai. "Evaluation and Comparison of Hybrid Wing VTOL UAV with Four Different Electric Propulsion Systems." Aerospace 8, no. 9 (September 9, 2021): 256. http://dx.doi.org/10.3390/aerospace8090256.

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Electric propulsion technology has attracted much attention in the aviation industry at present. It has the advantages of environmental protection, safety, low noise, and high design freedom. An important research branch of electric propulsion aircraft is electric vertical takeoff and landing (VTOL) aircraft, which is expected to play an important role in urban traffic in the future. Limited by battery energy density, all electric unmanned aerial vehicles (UAVs) are unable to meet the longer voyage. Series/parallel hybrid-electric propulsion and turboelectric propulsion are considered to be applied to VTOL UAVs to improve performances. In this paper, the potential of these four configurations of electric propulsion systems for small VTOL UAVs are evaluated and compared. The main purpose is to analyze the maximum takeoff mass and fuel consumption of VTOL UAVs with different propulsion systems that meet the same performance requirements and designed mission profiles. The differences and advantages of the four types propulsion VTOL UAV in the maximum takeoff mass and fuel consumption are obtained, which provides a basis for the design and configuration selection of VTOL UAV propulsion system.

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3

Bacchini, Alessandro, and Enrico Cestino. "Key aspects of electric vertical take-off and landing conceptual design." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 3 (November 8, 2019): 774–87. http://dx.doi.org/10.1177/0954410019884174.

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The recent advances in battery energy density and electric propulsion systems for automotive applications are enabling the development of the electric vertical take-off and landing (VTOL) aircraft. The electric VTOL is a new means of transport that can fly like an aircraft and take off and land vertically like a helicopter, sometimes called personal aerial vehicle. This paper compares it to the existing vehicles that may compete with it and addresses the estimation of its performances in hover, cruise flight, and the transition phase. The main parameters affecting performances are then discussed. Considerable space is dedicated to the battery mass to total mass ratio.

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4

Donateo, Teresa, Claudia Lucia De Pascalis, and Antonio Ficarella. "Synergy Effects in Electric and Hybrid Electric Aircraft." Aerospace 6, no. 3 (March 6, 2019): 32. http://dx.doi.org/10.3390/aerospace6030032.

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The interest in electric and hybrid electric power system has been increasing, in recent times, due to the benefits of this technology, such as high power-to-weight ratio, reliability, compactness, quietness, and, above all, elimination of local pollutant emissions. One of the key factors of these technologies is the possibility to exploit the synergy between powertrain, structure, and mission. This investigation addresses this topic by applying multi-objective optimization to two test cases — a fixed-wing, tail-sitter, Vertical Take-off and Landing Unmanned Aerial Vehicle (VTOL-UAV), and a Medium-Altitude Long-Endurance Unmanned Aerial Vehicle (MALE-UAV). Cruise time and payload weight were selected as goals for the first optimization problem, while fuel consumption and electric endurance were selected for the second one. The optimizations were performed with Non-dominated Sorting Genetic Algorithm-II (NSGA-II) and S-Metric Selection Evolutionary Multiobjective Algorithm (SMS-EMOA), by taking several constraints into account. The VTOL-UAV optimization was performed, at different levels (structure only, power system only, structure and power system together). To better underline the synergic effect of electrification, the potential benefit of structural integration and multi-functionalization was also addressed. The optimization of the MALE-UAV was performed at two different levels (power system only, power system, and mission profile together), to explore the synergic effect of hybridization. Results showed that large improvements could be obtained, either in the first test case when, both, the powertrain design and the aircraft structure were considered, and in the optimization of the hybrid electric UAV, where the optimization of the aircraft flight path gave a strong contribution to the overall performances.

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5

Booker, Julian, Caius Patel, and Phillip Mellor. "Modelling Green VTOL Concept Designs for Reliability and Efficiency." Designs 5, no. 4 (October 28, 2021): 68. http://dx.doi.org/10.3390/designs5040068.

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All-electric and hybrid-electric aircraft are a future transport goal and a possible ‘green’ solution to increasing climate-related pressures for aviation. Ensuring the safety of passengers is of high importance, informed through appropriate reliability predictions to satisfy emerging flight certification requirements. This paper introduces another important consideration related to redundancy offered by multiplex electric motors, a maturing technology which could help electric aircraft manufacturers meet the high reliability targets being set. A concept design methodology is overviewed involving a symbolic representation of aircraft and block modelling of two important figures of merit, reliability, and efficiency, supported by data. This leads to a comparative study of green aircraft configurations indicating which have the most potential now, and in the future. Two main case studies are then presented: an electric tail rotor retrofitted to an existing turbine powered helicopter (hybrid) and an eVTOL aircraft (all-electric), demonstrating the impact of multiplex level and number of propulsion channels on meeting target reliabilities. The paper closes with a summary of the important contribution to be made by multiplex electric machines, well as the advancements necessary for green VTOL aircraft sub-systems, e.g., power control unit and batteries, to improve reliability predictions and safety further.

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6

Zhu, Yingtao, Bingjie Zhu, Jianan Zong, and Xixiang Yang. "Modeling and optimization of the energy system for series hybrid electric fixed-wing VTOL." Journal of Physics: Conference Series 2351, no. 1 (October 1, 2022): 012005. http://dx.doi.org/10.1088/1742-6596/2351/1/012005.

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In this paper, the fixed-wing vertical take-off and landing (VTOL) aircraft is studied. Based on the typical mission profile, the flight process of fixed-wing VTOL aircraft is divided into rotor mode and fixed-wing mode, and the dynamic models of the two modes are established respectively. The power transmission model of the series hybrid electric system is established, the concept of hybridization for power (Hp ) is introduced, and an optimization method of power allocation based on Hp is proposed. The optimization method is verified by simulation, and the results show that, compared with the pure electric energy system, the performance of the optimized hybrid energy system is improved obviously.

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7

Fang, Zixuan, and Leonardo Callegaro. "Phase-Shifted TAB Converter System for Electric VTOL Aircraft." IOP Conference Series: Earth and Environmental Science 804, no. 3 (July 1, 2021): 032031. http://dx.doi.org/10.1088/1755-1315/804/3/032031.

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8

Zong, Jianan, Bingjie Zhu, Zhongxi Hou, Xixiang Yang, and Jiaqi Zhai. "Sizing and Mission Profile Analysis of the Hybrid-Electric Propulsion System for Retrofitting a Fixed Wing VTOL Aircraft." International Journal of Aerospace Engineering 2022 (February 7, 2022): 1–10. http://dx.doi.org/10.1155/2022/9384931.

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Hybrid-electric technology can be expected to improve the performance of fixed wing vertical takeoff and landing (VTOL) aircraft. In this paper, we demonstrated a method of retrofitting a single-energy propulsion system prototype with a hybrid-electric propulsion system. Since the hybrid-electric system has several working modes, the optimal design results have strong coupling with mission performance. Therefore, we propose an analysis method of the mission profile to determine the design point. Finally, the payload-range sensitivity is studied. The results show that the hybrid-electric propulsion system can greatly increase the mission profile of aircraft. The analysis method of the mission profile also provides perspective for the hybrid-electric propulsion system design.

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9

Palaia, Giuseppe, Karim Abu Salem, Vittorio Cipolla, Vincenzo Binante, and Davide Zanetti. "A Conceptual Design Methodology for e-VTOL Aircraft for Urban Air Mobility." Applied Sciences 11, no. 22 (November 16, 2021): 10815. http://dx.doi.org/10.3390/app112210815.

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Recent progress of electric systems has raised attention towards hybrid-electric and full-electric aircraft. Nevertheless, the current low battery energy density limits the application of these propulsive architectures to large transport aircraft. In the context of the general aviation category, full-electric aircraft for the so-called Urban Air Mobility scenario are gaining increasing interest. These air taxis, also called e-VTOL, are conceived to exploit vertical take-off and landing capabilities, to carry people from one point to another, typically within the same city. In this paper, a new conceptual design methodology for urban air vehicles is presented and applied to an innovative convertiplane, called TiltOne, based on a box-wing architecture coupled with tilt-wing mechanisms. Several TiltOne configurations have been designed according to the current regulations imposed by European Union Aviation Safety Agency, and sensitivity analyses have been carried out on the varying main design parameters, such as wing loading and propellers’ disk loading, as well as main top-level aircraft requirements. The results provide an overview for today’s operational capabilities of such aircraft and, in addition, depict possible scenarios for a near-future horizon, based on the assumption of increased performance levels for the electric powertrain components. In such scenario, two different concepts of operations are analysed and discussed: the first is based on a given design range, long enough to cover the urban distances; the second is conceived to exploit the capability of flying multiple shorter missions with a single battery charge. The designed TiltOne configurations derived from these different approaches are presented, highlighting their potential capabilities and possible drawbacks.

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10

Zhu, Yingtao, Bingjie Zhu, Xixiang Yang, Zhongxi Hou, and Jianan Zong. "Fuzzy Logic-Based Energy Management Strategy of Hybrid Electric Propulsion System for Fixed-Wing VTOL Aircraft." Aerospace 9, no. 10 (September 25, 2022): 547. http://dx.doi.org/10.3390/aerospace9100547.

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An energy management strategy for a series hybrid electric propulsion system designed for a fixed-wing vertical take-off and landing (VTOL) aircraft is presented in this paper. The proposed method combines an ideal operating line (IOL) and fuzzy logic. Fuzzy logic is used to dynamically and optimally allocate the output power of the generator and the battery pack according to the power requirement of the aircraft and the SOC of the battery pack. The IOL controller is used to optimize the internal combustion engine (ICE) operating point to improve the fuel economy of the system. The detailed aircraft model and energy system model are established. The flight process of a 100 kg scale VTOL aircraft under a typical mission profile is simulated. The simulation results show that running the ICE based on IOL can greatly improve its efficiency The introduction of fuzzy logic to optimize the power allocation of the generator and battery pack improves the overall efficiency of the system. The feasibility and effectiveness of the energy management strategy proposed in this paper are verified, and the design ideas and analysis methods are provided for the energy management of a hybrid electric aircraft.

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11

Maghfiroh, Hari, Chico Hermanu, and Vernanda Sitorini Zul Hizmi. "POSITION CONTROL OF VTOL SYSTEM USING ANFIS VIA HARDWARE IN THE LOOP." SINERGI 25, no. 3 (July 30, 2021): 309. http://dx.doi.org/10.22441/sinergi.2021.3.008.

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Electric motors have been widely applied in various equipment. One application is found in Unmanned Aerial Vehicles (UAVs). An electric motor speed control system that can balance the aircraft's position is one of the mandatory features that must be owned by the aircraft. The position balancer control also supports the Vertical Take-Off Landing (VTOL) system. This study's VTOL position control system uses Hardware-in-the-loop (HIL) method with MATLAB Simulink and Arduino. ANFIS (Adaptive Neuro-Fuzzy Inferences System) is used as a position control algorithm. The controller performance is compared with conventional PID and FLC (Fuzzy Logic Controller). The system is tested as an initial position variation and loading test. The experiment shows that HIL can help fast prototyping by faster changes in the controller algorithms and is easy to program. The result is varied in each experiment. In the ISE (Integral Square of Error) point of view, ANFIS is better than PID by 100 % and has a very small difference from FLC in the initial position test. ANFIS is better by 95.44% and 4.56% compared with PID and FLC in the loading test, respectively.

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12

Li, Huiling, and Kun Liu. "Aerodynamic Design Optimization and Analysis of Ducted Fan Blades in DEP UAVs." Aerospace 10, no. 2 (February 8, 2023): 153. http://dx.doi.org/10.3390/aerospace10020153.

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In order to reduce the dependence on fossil fuels, the concept of distributed electric propulsion (DEP) has been introduced. At present, there are a few studies on the small electric propulsion engines of DEP vertical take-off and landing (VTOL) UAVs. According to the design requirements of DEP VTOL UAV ducted fans, the aerodynamic design of a ducted fan is carried out in this paper. Firstly, the initial model is established by referring to theoretical derivations. Then, Bezier curves are used to control the mid-arc and thickness distributions of the blade profiles at different blade heights in order to realize the parameterization as design variables. Finally, the objective function that can represent the performance of the rotor is selected, and a multi-objective genetic algorithm is used to optimize the performance. The optimal results are obtained, and the aerodynamic characteristics are analyzed. Compared with the initial model, the total pressure ratio and isentropic efficiency of the optimized model are increased by 5.3% and 7.8%, respectively, reaching 1.20 and 90.37%. Meanwhile, the aerodynamic performance of the optimized model is improved, indicating that the performance of the rotor is significantly enhanced and that the design task is completed.

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13

Tyan, Maxim, Nhu Van Nguyen, Sangho Kim, and Jae-Woo Lee. "Comprehensive preliminary sizing/resizing method for a fixed wing – VTOL electric UAV." Aerospace Science and Technology 71 (December 2017): 30–41. http://dx.doi.org/10.1016/j.ast.2017.09.008.

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14

Li, Yafei, and Minghuan Liu. "Path Planning of Electric VTOL UAV Considering Minimum Energy Consumption in Urban Areas." Sustainability 14, no. 20 (October 18, 2022): 13421. http://dx.doi.org/10.3390/su142013421.

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As a new mode of transportation in the future, electric vertical take-off and landing unmanned aerial vehicles (eVTOL UAV) can undertake the task of logistics distribution and carry people in urban areas. It is challenging to carry out research designed to plan the path of eVTOL UAVs which can have a safe and sustainable operation mode in urban areas. Therefore, this work proposes a method for planning an obstacle-free path for eVTOL UAVs in urban areas with the goal of minimizing energy consumption. It aims to improve the safety and sustainability of eVTOL UAV operations. Based on variations of air density with height, a more accurate formula for calculating battery energy consumption of eVTOL UAV is derived. It is used in the vertical takeoff and landing phase and horizontal flight phase, respectively. Considering the influence of buildings on eVTOL UAV operation, a path planning method applicable to complex urban environments is proposed. The safe nodes of eVTOL UAV flight are obtained by using Voronoi diagrams based on building locations. Then, the complete shortest and obstacle-free path is obtained by using a Dubins geometric path and Floyd algorithm. After obtaining the obstacle-free paths for all flight height zones, the battery energy consumption of the eVTOL UAV in each flight height zone is calculated. Then, the flight height with the minimum energy consumption is obtained. The simulation results show that the path length obtained by the proposed path planning method is shorter than that obtained by particle swarm optimization; the total battery energy consumption changes in the same pattern in the low-altitude areas and high-altitude areas; the difference between the maximum and minimum energy consumption in the small area enables the eVTOL UAV to cover about 350 m more, and about 420 m more in the large area. Therefore, in future high-frequency UAV mission flights, choosing the altitude with the lowest energy consumption can reduce UAV operator costs. It can also significantly increase UAV transport range and make UAVs operate more sustainably.

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15

Vieira, Darli Rodrigues, Dreyfus Silva, and Alencar Bravo. "Electric VTOL aircraft: the future of urban air mobility (background, advantages and challenges)." International Journal of Sustainable Aviation 5, no. 2 (2019): 101. http://dx.doi.org/10.1504/ijsa.2019.10023187.

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16

Vieira, Darli Rodrigues, Dreyfus Silva, and Alencar Bravo. "Electric VTOL aircraft: the future of urban air mobility (background, advantages and challenges)." International Journal of Sustainable Aviation 5, no. 2 (2019): 101. http://dx.doi.org/10.1504/ijsa.2019.101746.

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17

Finger, D. Felix, Carsten Braun, and Cees Bil. "Impact of electric propulsion technology and mission requirements on the performance of VTOL UAVs." CEAS Aeronautical Journal 10, no. 3 (December 11, 2018): 827–43. http://dx.doi.org/10.1007/s13272-018-0352-x.

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18

Matt, Daniel, Lorenzo Piscini, Nadhem Boubaker, Anthony Gimeno, Philippe Enrici, and Mourad Aitakkache. "Low-Voltage, High-Frequency Synchronous Motor for Aerospace Applications." Electronics 11, no. 17 (August 30, 2022): 2719. http://dx.doi.org/10.3390/electronics11172719.

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This article details the design of a permanent magnet synchronous electric motor prototype dedicated to the direct drive of the propeller for VTOL (Vertical Take-Off and Landing) and CTOL (Conventional Take-off and Landing) aircrafts. Our main aim is to maximise the power-to-weight ratio whilst not compromising the efficiency and the reliability. The originality of the research is based on the implementation of an armature winding using solid copper bars; we show that it is possible to use such an approach in an electric machine operating at very high frequency (1800 Hz) through a precise study on the shape of the bars to counter the additional losses. A prototype has been successfully manufactured; manufacturing details and some of the experimental test results are presented here.

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19

Donateo, Teresa, Claudia Lucia De Pascalis, and Antonio Ficarella. "Electric Aircraft: Exploiting the Synergy between Powertrain, Energy Management and Structure." MATEC Web of Conferences 233 (2018): 00026. http://dx.doi.org/10.1051/matecconf/201823300026.

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This study aims at investigating the synergy between powertrain and structure within the design process of a fixed-wing tail-sitter unmanned aerial vehicle (UAV). The UAV is equipped with a pure-electric power system and has vertical take-off and landing capabilities (VTOL). The problem is addressed by running a contemporary optimization of the parameters of both the powertrain and the UAV’s structure, in order to maximize electric endurance and payload weight through the usage of a performant multi-objective evolutionary algorithm named SMS-EMOA. Three different designs are selected, discussed and compared with literature results on the same UAV to quantify the increase of payload and cruise time that can be obtained by exploiting the synergy between structure and powertrain. The potentiality of furtherly improving payload through the usage of multi-functional panels, while keeping the same endurance, is also quantified and compared with the technologies proposed in literature.

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20

Ng, Wanyi, Mrinalgouda Patil, and Anubhav Datta. "Hydrogen Fuel Cell and Battery Hybrid Architecture for Range Extension of Electric VTOL (eVTOL) Aircraft." Journal of the American Helicopter Society 66, no. 1 (January 1, 2021): 1–13. http://dx.doi.org/10.4050/jahs.66.012009.

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The objective of this paper is to study the impact of combining hydrogen fuel cells with lithium-ion batteries through an ideal power-sharing architecture to mitigate the poor range and endurance of battery powered electric vertical takeoff and landing (eVTOL) aircraft. The benefits of combining the two sources is first illustrated by a conceptual sizing of an electric tiltrotor for an urban air taxi mission of 75 mi cruise and 5 min hover. It is shown that an aircraft of 5000–6000 lb gross weight can carry a practical payload of 500 lb (two to three seats) with present levels of battery specific energy (150 Wh/kg) if only a battery–fuel cell hybrid power plant is used, combined in an ideal power-sharing manner, as long as high burst C-rate batteries are available (4–10 C). A power plant using batteries alone can carry less than half the payload; use of fuel cells alone cannot lift off the ground. Next, the operation of such a system is demonstrated using systematic hardware testing. The concepts of unregulated and regulated power-sharing architectures are described. A regulated architecture that can implement ideal power sharing is built up in a step-by-step manner. It is found only two switches and three DC-to-DC converters are necessary, and if placed appropriately, are sufficient to achieve the desired power flow. Finally, a simple power system model is developed, validated with test data and used to gain fundamental understanding of power sharing.

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21

Jung, Yeondeuk, and Hyungsik Choi. "Actuator Mixer Design in Rotary-Wing Mode Based on Convex Optimization Technique for Electric VTOL UAV." Journal of the Korean Society for Aeronautical & Space Sciences 48, no. 9 (September 30, 2020): 691–701. http://dx.doi.org/10.5139/jksas.2020.48.9.691.

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22

An, Jae-Hyun, Do-Youn Kwon, Kwon-Su Jeon, Maxim Tyan, and Jae-Woo Lee. "Advanced Sizing Methodology for a Multi-Mode eVTOL UAV Powered by a Hydrogen Fuel Cell and Battery." Aerospace 9, no. 2 (January 27, 2022): 71. http://dx.doi.org/10.3390/aerospace9020071.

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A critical drawback of battery-powered eVTOL UAVs is their limited range and endurance, and this drawback could be solved by using a combination of hydrogen fuel cells and batteries. The objective of this paper is to develop a sizing methodology for the lift+cruise-type eVTOL UAV powered by a hydrogen fuel cell and battery. This paper presents the constraints analysis method for forward flight/VTOL multi-mode UAV, the regression model for electric propulsion system sizing, a sizing method for an electric propulsion system and hydrogen fuel cell system, and a transition analysis method. The total mass of the UAV is iteratively calculated until convergence, and the optimization method is used to ensure that the sizing results satisfy the design requirements. The sizing results are the UAV’s geometry, mass, and power data. To verify the accuracy of the proposed sizing methodology, the sizing and the conceptual design phase results of a 25 kg hydrogen fuel-cell-powered UAV are compared. All parameters had an error within 10% and satisfied the design requirements.

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23

Hu, Josin, and Julian Booker. "Preliminary Sizing of Electric-Propulsion Powertrains for Concept Aircraft Designs." Designs 6, no. 5 (October 13, 2022): 94. http://dx.doi.org/10.3390/designs6050094.

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The drive towards a greener and more sustainable future is encouraging the aviation industry to move towards increasing electrification of its fleet. The development of electric propulsion technologies also requires new approaches to assess their viability in novel configurations. A methodology is proposed which consists of four sub-procedures; powertrain modelling, performance analysis, aerodynamic modelling, and sizing. This approach initially considers powertrain modelling using AIAA symbol representations, and a review of the available literature establishes state-of-the-art component values of efficiency, specific power, specific energy, and specific fuel consumption. The sizing procedure includes a mission and aerodynamic analysis to determine the energy and power requirements, and it relies on a mass regression model based on full-electric, hybrid, VTOL and fixed-wing aircraft found in the literature. The methodology has been applied to five case studies which are representative of a wide range of missions and configurations. Their predicted masses from the sizing procedure have been validated against their actual masses. The predicted total mass shows generally good agreement with the actual values, and in addition, accurate values for active mass have been predicted. A sensitivity analysis of the sizing procedure suggests that future work may include a more accurate analysis of aerodynamics and mission if the methodology were to be applied for selecting aircraft concepts.

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24

Kim, Boseong, Jeonggyu Bak, Senghyun Yun, Sooyoung Cho, Juhyung Ha, Gyusung Park, Geunho Lee, Sunghong Won, Changmo Moon, and Jinsoo Cho. "Feasibility Study of a Series Hybrid-Electric Propulsion System for a Fixed Wing VTOL Unmanned Aerial Vehicle." Journal of the Korean Society for Aeronautical & Space Sciences 43, no. 12 (December 1, 2015): 1097–107. http://dx.doi.org/10.5139/jksas.2015.43.12.1097.

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25

Sahwee, Z., N. L. Mohd Kamal, S. Abdul Hamid, N. Norhashim, N. Lott, and M. H. Mohd Asri. "Drag Assessment of Vertical Lift Propeller in Forward Flight for Electric Fixed-Wing VTOL Unmanned Aerial Vehicle." IOP Conference Series: Materials Science and Engineering 705 (December 2, 2019): 012007. http://dx.doi.org/10.1088/1757-899x/705/1/012007.

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26

Żugaj, Marcin, Mohammed Edawdi, Grzegorz Iwański, Sebastian Topczewski, Przemysław Bibik, and Piotr Fabiański. "An Unmanned Helicopter Energy Consumption Analysis." Energies 16, no. 4 (February 20, 2023): 2067. http://dx.doi.org/10.3390/en16042067.

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The number of operations incorporating E-VTOL aircrafts is increasing each year, and the optimization of the energy consumption of such vehicles is a major problem. In this paper, a small-scale ARCHER helicopter’s energy consumption is analyzed, wherein different flight conditions, main rotor revolutions, and flight control system settings are considered. The helicopter dynamic model was developed in the FLIGHTLAB environment and was then validated based on flight test data. The model used for the calculation of energy consumption was developed using the electric and dynamic characteristics of the main rotor, electric motor, and transmission system. The main part of this work concerns the analysis of electric energy consumption during the vehicle’s flight via the use of an automatic flight control system (AFCS) that ensures repeatable flight conditions. The AFCS was designed such that it includes both path and attitude control to provide hover and cruise control modes. The helicopter’s energy consumption was analyzed during different phases of flight, when executing maneuvers, and using different main rotor angular velocities to perform - a given task. The results show that the level of energy consumption significantly depends on the helicopter’s main rotor revolutions, flight speed, and the maneuvers performed. The proposed methodology can be used in prospective energy-efficient mission planning and UAV helicopter design.

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27

Amargianitakis, Daniel, Rodney H. Self, Antonio J. Torija, and Anderson R. Proença. "Towards predicting noise-power-distance curves for propeller and rotor powered aircraft." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 3 (August 1, 2021): 3909–20. http://dx.doi.org/10.3397/in-2021-2555.

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Propeller and rotor based propulsion systems are the dominating choice of power delivery system in the upcoming Urban Air Mobility market. Fully electric air-taxis (car sized vehicles with Vertical Take-off and Landing, VTOL, capabilities) concepts are using the benefits of the scalable properties of electric motors to distribute propulsor units all over the airframe. The large variety of concepts and configurations of these vehicles poses a serious issue in predicting noise generated on the ground. The need for a high-level model to aid in acoustic decision making is evident. Through the demonstrated methodology of computationally deriving Noise - Power - Distance curves for conventional turbo fan aircraft, this paper delivers the capability of dealing with propeller propulsion systems and the associated propeller tonal noise sources to generate the NPDs and therefore noise exposure maps. The aims can be broken down into two objectives: a) demonstrate the capabilities of the proposed propeller harmonics noise scaling laws to calculate noise variation from a baseline scenario and b) incorporate the scaling components into the larger capability of producing noise exposure contours, by the means of computationally deriving NPD curves for propeller powered aircraft. Preliminary NPD curves for General Aviation sized propeller power aircraft are generated and discussed.

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28

Goyal, Rohit, and Adam Cohen. "Advanced Air Mobility: Opportunities and Challenges Deploying eVTOLs for Air Ambulance Service." Applied Sciences 12, no. 3 (January 24, 2022): 1183. http://dx.doi.org/10.3390/app12031183.

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Advanced air mobility (AAM) is a broad concept enabling consumers access to on-demand air mobility, cargo and package delivery, healthcare applications, and emergency services through an integrated and connected multimodal transportation network. While a number of technical and social concerns have been raised about AAM, early use cases for emergency response and aeromedical transport may be key to demonstrating the concept and building public acceptance. Using a five-step multi-method approach consisting of preliminary scoping, modeling performance metrics, developing baseline assumptions, analyzing scenarios, and applying a Monte Carlo sensitivity analysis, this study examines the potential operational and market viability of the air ambulance market using a variety of aircraft and propulsion types. The analysis concludes that electric vertical take-off and land (eVTOL) aircraft could confront a number of operational and economic challenges for aeromedical applications compared to hybrid vertical take-off and land (VTOL) aircraft and rotorcraft. The study finds that technological improvements such as reduced charge times, increased operational range, and battery swapping could make the eVTOL aircraft more reliable and cost-effective for aeromedical transport.

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Ben-Moshe, Boaz. "Power Line Charging Mechanism for Drones." Drones 5, no. 4 (October 1, 2021): 108. http://dx.doi.org/10.3390/drones5040108.

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The use of multirotor drones has increased dramatically in the last decade. These days, quadcopters and Vertical Takeoff and Landing (VTOL) drones can be found in many applications such as search and rescue, inspection, commercial photography, intelligence, sports, and recreation. One of the major drawbacks of electric multirotor drones is their limited flight time. Commercial drones commonly have about 20–40 min of flight time. The short flight time limits the overall usability of drones in homeland security applications where long-duration performance is required. In this paper, we present a new concept of a “power-line-charging drone”, the idea being to equip existing drones with a robotic mechanism and an onboard charger in order to allow them to land safely on power lines and then charge from the existing 100–250 V AC (50–60 Hz). This research presents several possible conceptual models for power line charging. All suggested solutions were constructed and submitted to a field experiment. Finally, the paper focuses on the optimal solution and presents the performance and possible future development of such power-line-charging drones.

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Lee, Yu-Been, and Jae-Sang Park. "Hover Performance Analyses of Coaxial Co-Rotating Rotors for eVTOL Aircraft." Aerospace 9, no. 3 (March 9, 2022): 152. http://dx.doi.org/10.3390/aerospace9030152.

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Hover performance analyses of coaxial co-rotating rotors (or stacked rotors), which can be used as lifting rotors for electric VTOL (eVTOL) aircraft, are conducted here. In this study, the rotorcraft comprehensive analysis code, CAMRAD II, is used with the general free-wake model. The generic coaxial co-rotating rotor without the blade taper and built-in twist is considered as the baseline rotor model, and the rotor is trimmed to match a prescribed rotor thrust value. The hover performance, including the rotor power and Figure of Merit (FM), is investigated for various index angles, axial spacings, blade taper ratios, and built-in twist angles. A maximum FM value is obtained near an index angle of 0° and 10° when the axial spacing is below and above 5.27%R, respectively. When the index angle is 0° and axial spacing is 1.44% R, the maximum increments in the FM are 3.03% and 6.06%, respectively, for a rotor with a blade taper ratio of 0.8 and a built-in twist angle of −12°. Therefore, this simulation study demonstrates that the hover performance of coaxial co-rotating rotors can be changed by adjusting the index angle or the axial spacing.

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31

Krishna, Vamsi, Eduardo Lima Simões da Silva, and Arne Døssing. "Experiments on magnetic interference for a portable airborne magnetometry system using a hybrid unmanned aerial vehicle (UAV)." Geoscientific Instrumentation, Methods and Data Systems 10, no. 1 (January 27, 2021): 25–34. http://dx.doi.org/10.5194/gi-10-25-2021.

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Abstract. Using unmanned aerial vehicles (UAVs) for airborne magnetometry offers not only improved access and rapid sampling but also reduced logistics costs. More importantly, the UAV-borne aeromagnetometry can be performed at low altitudes, which makes it possible to resolve fine features otherwise only evident in ground surveys. Developing such a UAV-borne aeromagnetometry system is challenging owing to strong magnetic interference introduced by onboard electric and electronic components. An experiment concerning the static magnetic interference of the UAV was conducted to assess the severity of the interference of a hybrid vertical take-off and landing (VTOL) UAV. The results of the static experiment show that the wing area is highly magnetic due to the proximity to servomotors and motors, whereas the area along the longitudinal axis of the UAV has a relatively smaller magnetic signature. Assisted by the static experiment and aerodynamic simulations, we first proposed a front-mounting solution with two compact magnetometers. Subsequently, two dynamic experiments were conducted with the setup to assess the dynamic interference of the system. The results of the dynamic experiments reveal that the strongest source of in-flight magnetic interference is the current-carrying cables connecting the battery to the flight controller and that this effect is most influential during pitch maneuvers of the aircraft.

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32

Chrit, Mounir, and Marwa Majdi. "Improving Wind Speed Forecasting for Urban Air Mobility Using Coupled Simulations." Advances in Meteorology 2022 (October 12, 2022): 1–14. http://dx.doi.org/10.1155/2022/2629432.

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Hazardous weather, turbulence, wind, and thermals pose a ubiquitous challenge to Unmanned Aircraft Systems (UAS) and electric-Vertical Take-Off and Landing (e-VTOL) aircrafts, and the safe integration of UAS into urban area requires accurate high-granularity wind data especially during landing and takeoff phases. Two models, namely, Open-Source Field Operation and Manipulation (OpenFOAM) software package and Weather Research and Forecasting (WRF) model, are used in the present study to simulate airflow over Downtown Oklahoma City, Oklahoma, United States. Results show that computational fluid dynamics wind simulation driven by the atmospheric simulation significantly improves the simulated wind speed because the accurate modeling of the buildings affects wind patterns. The evaluation of different simulations against six Micronet stations shows that WRF-CFD numerical evaluation is a reliable method to understand the complicated wind flow within built-up areas. The comparison of wind distributions of simulations at different resolutions shows better description of wind variability and gusts generated by the urban flows. Simulations assuming anisotropy and isotropy of turbulence show small differences in the predicted wind speeds over Downtown Oklahoma City given the stable atmospheric stratification showing that turbulent eddy scales at the evaluation locations are within the inertial subrange and confirming that turbulence is locally isotropic.

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33

Kita, Koichi, Atsushi Konno, and Masaru Uchiyama. "Hovering Control of a Tail-Sitter VTOL Aerial Robot." Journal of Robotics and Mechatronics 21, no. 2 (April 20, 2009): 277–83. http://dx.doi.org/10.20965/jrm.2009.p0277.

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This paper describes system development and hovering control of a tail-sitter VTOL aerial robot. The tail-sitter VTOL aerial robot developed from model aircraft parts, sensors, microcomputers, and other components hovers autonomously thanks to attitude, altitude, and position control. Attitude control error averages 1-2°and altitude control error several centimeters. The aerial robot demonstrated both fixed-point hovering and trajectory tracking in hover mode.

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34

Ottaviani, Marco, Luca Giammichele, and Renato Ricci. "Design, Assembly and Testing of a Mobile Laboratory Based on a VTOL Scale Motorglider." Tecnica Italiana-Italian Journal of Engineering Science 65, no. 2-4 (July 30, 2021): 414–21. http://dx.doi.org/10.18280/ti-ijes.652-440.

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The objective of this paper is to explain the design steps and performance analysis of a vertical take-off and landing (VTOL) unmanned air vehicle (UAV) based on a Pilatus B4 glider scale model. Energy consumption, forces and thrust analyses are carry out to determinate the perfect match between low take-off weight and high aerodynamic performance. As a first approach a complete analysis of glider aerodynamic performances are settle to understand and design a proper support for VTOL conversion. Longitudinal static stability is fulfilled by evaluating the center of gravity location with respect to neutral position, nevertheless dynamic stability, and V-n diagram in VTOL configuration are evaluated to guarantee a correct behavior during fixed wing flight mode. In addition, power requirements, motor thrust capability and tilt-motors servo assisted system performance are determinate in perspective of flight performance to find out the perfect transition from multirotor take-off and landing mode to fixed-wing flying state. For these purposes a test bench has being designed to evaluate thrust, electrical absorption and rpm motor behavior along the throttle range. Finally, the assembly and preliminary tests are performed in order to validate the VTOL and Forward flight capability.

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35

Li, Xiaoda, Yongliang Wu, Xiaowen Shan, Haofan Zhang, and Yang Chen. "Estimation of Airflow Parameters for Tail-Sitter UAV through a 5-Hole Probe Based on an ANN." Sensors 23, no. 1 (December 30, 2022): 417. http://dx.doi.org/10.3390/s23010417.

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Fixed-wing vertical take-off and landing (VTOL) UAVs have received more and more attention in recent years, because they have the advantages of both fixed-wing UAVs and rotary-wing UAVs. To meet its large flight envelope, the VTOL UAV needs accurate measurement of airflow parameters, including angle of attack, sideslip angle and speed of incoming flow, in a larger range of angle of attack. However, the traditional devices for the measurement of airflow parameters are unsuitable for large-angle measurement. In addition, their performance is unsatisfactory when the UAV is at low speed. Therefore, for tail-sitter VTOL UAVs, we used a 5-hole pressure probe to measure the pressure of these holes and transformed the pressure data into the airflow parameters required in the flight process using an artificial neural network (ANN) method. Through a series of comparative experiments, we achieved a high-performance neural network. Through the processing and analysis of wind-tunnel-experiment data, we verified the feasibility of the method proposed in this paper, which can make more accurate estimates of airflow parameters within a certain range.

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36

Meister, O., N. Frietsch, C. Ascher, and G. F. Trommer. "Adaptive path planning for VTOL-UAVs." IEEE Aerospace and Electronic Systems Magazine 24, no. 7 (July 2009): 36–41. http://dx.doi.org/10.1109/maes.2009.5208559.

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37

Meister, O., N. Frietsch, Ch Ascher, and G. F. Trommer. "Adaptive path planning for VTOL-UAVs." Gyroscopy and Navigation 1, no. 4 (October 2010): 279–84. http://dx.doi.org/10.1134/s2075108710040073.

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38

Tang, Hongyan, Dan Zhang, and Zhongxue Gan. "Control System for Vertical Take-Off and Landing Vehicle’s Adaptive Landing Based on Multi-Sensor Data Fusion." Sensors 20, no. 16 (August 7, 2020): 4411. http://dx.doi.org/10.3390/s20164411.

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Vertical take-off and landing unmanned aerial vehicles (VTOL UAV) are widely used in various fields because of their stable flight, easy operation, and low requirements for take-off and landing environments. To further expand the UAV’s take-off and landing environment to include a non-structural complex environment, this study developed a landing gear robot for VTOL vehicles. This article mainly introduces the adaptive landing control of the landing gear robot in an unstructured environment. Based on the depth camera (TOF camera), IMU, and optical flow sensor, the control system achieves multi-sensor data fusion and uses a robotic kinematical model to achieve adaptive landing. Finally, this study verifies the feasibility and effectiveness of adaptive landing through experiments.

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39

Panigrahi, Siddhant, Yenugu Siva Sai Krishna, and Asokan Thondiyath. "Design, Analysis, and Testing of a Hybrid VTOL Tilt-Rotor UAV for Increased Endurance." Sensors 21, no. 18 (September 7, 2021): 5987. http://dx.doi.org/10.3390/s21185987.

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Unmanned Aerial Vehicles (UAVs) have slowly but steadily emerged as a research and commercial hotspot because of their widespread applications. Due to their agility, compact size, and ability to integrate multiple sensors, they are mostly sought for applications that require supplementing human effort in risky and monotonous missions. Despite all of these advantages, rotorcrafts, in general, are limited by their endurance and power-intensive flight requirements, which consequently affect the time of flight and operational range. On the other hand, fixed-wing aircrafts have an extended range, as the entire thrust force is along the direction of motion and are inherently more stable but are limited by their takeoff and landing strip requirements. One of the potential solutions to increase the endurance of VTOL rotorcrafts (Vertical Take-Off and Landing Vehicles) was to exploit the thrust vectoring ability of the individual actuators in multi-rotors, which would enable take-off and hovering as a VTOL vehicle and flight as a fixed-wing aircraft. The primary aim of this paper is to lay out the overall design process of a Hybrid VTOL tilt-rotor UAV from the initial conceptual sketch to the final fabricated prototype. The novelty of the design lies in achieving thrust vectoring capabilities in a fixed-wing platform with minimum actuation and no additional control complexity. This paper presents novel bi-copter that has been designed to perform as a hybrid configuration in both VTOL and fixed wing conditions with minimum actuators in comparison to existing designs. The unified dynamic modelling along with the approximation of multiple aerodynamic coefficients by numerical simulations is also presented. The overall conceptual design, dynamic modeling, computational simulation, and experimental analysis of the novel hybrid fixed-wing bi-copter with thrust vectoring capabilities aiming to substantially increase the flight range and endurance compared to the conventional aircraft rotorcraft configurations are presented.

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40

Bauersfeld, L., L. Spannagl, G. Ducard, and C. Onder. "MPC Flight Control for a Tilt-Rotor VTOL Aircraft." IEEE Transactions on Aerospace and Electronic Systems 57, no. 4 (August 2021): 2395–409. http://dx.doi.org/10.1109/taes.2021.3061819.

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41

Zhao, Junmin, Zhongyun Fan, Min Chang, and Gang Wang. "Coupling Effects on Distributed Multi-Propeller Channel Wing at Low Speed Condition." Energies 15, no. 15 (July 23, 2022): 5352. http://dx.doi.org/10.3390/en15155352.

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Channel wing is a propeller-coupling layout that has good low-speed performance and S/VTOL potential. Focused on the application of this layout at the S/VTOL stage, this paper attempts to find the interaction mechanism for the distributed propeller channel wing. Firstly, the computation method based on RANS equations for propeller–wing integration was established with Momentum Source Method, which was compared with the unsteady Sliding Mesh method and validated by a ducted propeller. Secondly, the performances and aerodynamic characteristics of the single-propeller channel wings with two different airfoils were analyzed, and a ground test for the scaled model was conducted. Finally, a four-propeller channel wing was analyzed and compared with single-propeller channel wing, then the flow field characteristics were discussed in depth. The study shows that the airfoil shape will strongly affect the lift of channel wing at S/VTOL stage. Multi-propeller channel wing analysis indicates that rotational direction plays an important role in outside propeller interaction, where outboard-up rotation increases outside channel lift. In addition, the propeller wake also shows special distortion and dissipation behaviors, which are strongly affected by adjacent propellers.

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42

Li, Boyang, Jingxuan Sun, Weifeng Zhou, Chih-Yung Wen, Kin Huat Low, and Chih-Keng Chen. "Transition Optimization for a VTOL Tail-Sitter UAV." IEEE/ASME Transactions on Mechatronics 25, no. 5 (October 2020): 2534–45. http://dx.doi.org/10.1109/tmech.2020.2983255.

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43

Redkin, A. V., Yu A. Yaloza, and I. E. Kovalev. "Reliability assessment of convertible aircraft with hybrid propulsion system and multirotor lifting system." Civil Aviation High Technologies 23, no. 5 (October 28, 2020): 76–96. http://dx.doi.org/10.26467/2079-0619-2020-23-5-76-96.

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Projects and experimental models of innovative concepts of VTOL aircraft with a hybrid propulsion system are attracting great interest and investment inflow all over the world. In this regard, when developing new concepts, it is important to understand how much better they will be than the currently operated rotorcraft and convertible aircraft in terms of reliability and flight safety, to be able to use them for passenger transportation in the future. In addition, when designing and choosing the optimal layout, it is necessary to know the contribution of each element and unit to the reliability of the aircraft as a whole in order to meet the requirements. To calculate the reliability indicators, the method of structural diagrams was chosen, and the calculation methodology was developed. The general classification of modern innovative concepts of convertible aircraft is considered, schematic diagram of hybrid propulsion system and its main parameters are determined. The article discusses the influence of the number of lifting rotor groups and their location on the possibility to continue the flight in hover mode in case of failure of one rotor group, the necessary power reserve of lifting electric motors is determined to ensure the given safety condition. In accordance with the adopted structural diagram, the main functional groups of the hybrid propulsion system of convertible aircraft operating in different flight modes are determined. The basic modes of a typical flight profile of a convertible aircraft are considered, time intervals characteristic for each mode are set. For each flight mode, a structural scheme of reliability of functional groups of a hybrid propulsion system is constructed, having a serial or parallel connection of elements, depending on their influence on the consequences of failure, the equation for calculating the probability of fail-free operation is derived. For lifting rotor groups, a combination of critical failures of more than one group is considered, and the equation is composed to calculate the probability of a catastrophic event in hover mode. Based on the obtained equations, the resulting calculation of the probability of fail-free operation, the probability of failure per flight hour for each flight mode was carried out separately and in total for the entire flight. Thus, for all flight modes, the probabilities of a catastrophic and emergency event, as well as a difficult situation in flight, are considered. A comprehensive analysis of the obtained results of reliability indicators calculation for convertible aircraft with six lifting rotors and two turboprop engines made it possible to conclude that it meets the requirements of the 25th part of aviation regulations for transport aircraft. A good potential margin of up to 10-2 was determined for the probability of a catastrophic failure in take-off, landing and transitional modes. The elements and subsystems that are critical for fail-free operation are identified, and ways to improve their reliability and the aircraft as a whole are proposed.

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Ye, Huawen, Meng Li, and Neng Wan. "Landing control design for a VTOL aircraft." IET Control Theory & Applications 14, no. 6 (April 16, 2020): 855–64. http://dx.doi.org/10.1049/iet-cta.2018.6244.

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45

ÇAKIR, HASAN, and DİLEK FUNDA KURTULUŞ. "Design and aerodynamic analysis of a VTOL tilt-wing UAV." Turkish Journal of Electrical Engineering and Computer Sciences 30, no. 3 (January 1, 2022): 767–84. http://dx.doi.org/10.55730/1300-0632.3810.

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46

Mejia Salazar, Carlos Enrique, and Julián Esteban Rendón Roldán. "Fractional order modeling of a nonlinear electromechanical system." Enfoque UTE 9, no. 4 (December 21, 2018): 45–56. http://dx.doi.org/10.29019/enfoqueute.v9n4.398.

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This paper presents a novel modeling technique for a VTOL electromechanical nonlinear dynamical system, based on fractional order derivatives. The proposed method evaluates the possible fractional differential equations of the electromechanical system model by a comparison against actual measurements and in order to estimate the optimal fractional parameters for the differential operators of the model, an extended Kalman filter was implemented. The main advantages of the fractional model over the classical model are the simultaneous representation of the nonlinear slow dynamics of the system due to the mechanical components and the nonlinear fast dynamics of the electrical components.

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47

Jabbari Asl, Hamed. "Robust vision-based tracking control of VTOL unmanned aerial vehicles." Automatica 107 (September 2019): 425–32. http://dx.doi.org/10.1016/j.automatica.2019.06.004.

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48

Roza, Ashton, and Manfredi Maggiore. "A Class of Position Controllers for Underactuated VTOL Vehicles." IEEE Transactions on Automatic Control 59, no. 9 (September 2014): 2580–85. http://dx.doi.org/10.1109/tac.2014.2308609.

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49

Hwang, Soo-Jung, Yu-Shin Kim, and Myeong-Kyu Lee. "Tilt Rotor-Wing Concept for Multi-Purpose VTOL UAV." International Journal of Aeronautical and Space Sciences 8, no. 1 (June 30, 2007): 87–94. http://dx.doi.org/10.5139/ijass.2007.8.1.087.

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50

Metni, Najib, Jean-Michel Pflimlin, Tarek Hamel, and Philippe Souères. "Attitude and gyro bias estimation for a VTOL UAV." Control Engineering Practice 14, no. 12 (December 2006): 1511–20. http://dx.doi.org/10.1016/j.conengprac.2006.02.015.

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