Готові списки джерел за темами / Electric VTOL

Добірка наукової літератури з теми "Electric VTOL"

Автор: Grafiati
Опубліковано: 14 березня 2023

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Статті в журналах з теми "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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Анотація:
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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Анотація:
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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Анотація:
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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Анотація:
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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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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Анотація:
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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Анотація:
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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Анотація:
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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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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Анотація:
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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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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Анотація:
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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Більше джерел

Дисертації з теми "Electric VTOL"

1

Glassock, Richard R. "Design, modelling and measurement of hybrid powerplant for unmanned aerial vehicles (UAVs)." Thesis, Queensland University of Technology, 2012. https://eprints.qut.edu.au/61052/1/Richard_Glassock_Thesis.pdf.

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Анотація:
The success or effectiveness for any aircraft design is a function of many trade-offs. Over the last 100 years of aircraft design these trade-offs have been optimized and dominant aircraft design philosophies have emerged. Pilotless aircraft (or uninhabited airborne systems, UAS) present new challenges in the optimization of their configuration. Recent developments in battery and motor technology have seen an upsurge in the utility and performance of electric powered aircraft. Thus, the opportunity to explore hybrid-electric aircraft powerplant configurations is compelling. This thesis considers the design of such a configuration from an overall propulsive, and energy efficiency perspective. A prototype system was constructed using a representative small UAS internal combustion engine (10cc methanol two-stroke) and a 600W brushless Direct current (BLDC) motor. These components were chosen to be representative of those that would be found on typical small UAS. The system was tested on a dynamometer in a wind-tunnel and the results show an improvement in overall propulsive efficiency of 17% when compared to a non-hybrid powerplant. In this case, the improvement results from the utilization of a larger propeller that the hybrid solution allows, which shows that general efficiency improvements are possible using hybrid configurations for aircraft propulsion. Additionally this approach provides new improvements in operational and mission flexibility (such as the provision of self-starting) which are outlined in the thesis. Specifically, the opportunity to use the windmilling propeller for energy regeneration was explored. It was found (in the prototype configuration) that significant power (60W) is recoverable in a steep dive, and although the efficiency of regeneration is low, the capability can allow several options for improved mission viability. The thesis concludes with the general statement that a hybrid powerplant improves the overall mission effectiveness and propulsive efficiency of small UAS.
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2

Kriel, Steven Cornelius. "A comparison of control systems for the flight transition of VTOL unmanned aerial vehicles." Thesis, Link to the online version, 2008. http://hdl.handle.net/10019/1334.

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3

Venter, Jacob. "Development of an experimental tilt-wing VTOL unmanned aerial vehicle." Thesis, Link to the online version, 2006. http://hdl.handle.net/10019/225.

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4

Gising, Andreas. "MALLS - Mobile Automatic Launch and Landing Station for VTOL UAVs." Thesis, Linköping University, Department of Electrical Engineering, 2008. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-15980.

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The market for vertical takeoff and landing unmanned aerial vehicles, VTOL UAVs, is growing rapidly. To reciprocate the demand of VTOL UAVs in offshore applications, CybAero has developed a novel concept for landing on moving objects called MALLS, Mobile Automatic Launch and Landing Station. MALLS can tilt its helipad and is supposed to align to either the horizontal plane with an operator adjusted offset or to the helicopter skids. Doing so, eliminates the gyroscopic forces otherwise induced in the rotordisc as the helicopter is forced to change attitude when the skids align to the ground during landing or when standing on a jolting boat with the rotor spun up. This master’s thesis project is an attempt to get the concept of MALLS closer to a quarter scale implementation. The main focus lies on the development of the measurement methods for achieving the references needed by MALLS, the hori- zontal plane and the plane of the helicopter skids. The control of MALLS is also discussed. The measurement methods developed have been proved by tested implementations or simulations. The theories behind them contain among other things signal filtering, Kalman filtering, sensor fusion and search algorithms. The project have led to that the MALLS prototype can align its helipad to the horizontal plane and that a method for measuring the relative attitude between the helipad and the helicopter skids have been developed. Also suggestions for future improvements are presented.

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5

Alley, Robert Jesse. "VTool: A Method for Predicting and Understanding the Energy Flow and Losses in Advanced Vehicle Powertrains." Thesis, Virginia Tech, 2012. http://hdl.handle.net/10919/33697.

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Анотація:
As the global demand for energy increases, the people of the United States are increasingly subject to high and ever-rising oil prices. Additionally, the U.S. transportation sector accounts for 27% of total nationwide Greenhouse Gas (GHG) emissions. In the U.S. transportation sector, light-duty passenger vehicles account for about 58% of energy use. Therefore incremental improvements in light-duty vehicle efficiency and energy use will significantly impact the overall landscape of energy use in America. A crucial step to designing and building more efficient vehicles is modeling powertrain energy consumption. While accurate modeling is indeed key to effective and efficient design, a fundamental understanding of the powertrain and auxiliary systems that contribute to energy consumption for a vehicle is equally as important if not more important. This thesis presents a methodology that has been packaged into a tool, called VTool, that can be used to estimate the energy consumption of a vehicle powertrain. The method is intrinsically designed to foster understanding of the vehicle powertrain as it relates to energy consumption while still providing reasonably accurate results. VTool explicitly calculates the energy required at the wheels of the vehicle to complete a prescribed drive cycle and then explicitly applies component efficiencies to find component losses and the overall energy consumption for the drive cycle. In calculating component efficiencies and losses, VTool offers several tunable parameters that can be used to calibrate the tool for a particular vehicle, compare powertrain architectures, or simply explore the tradeoffs and sensitivities of certain parameters. In this paper, the method is fully and explicitly developed to model Electric Vehicles (EVs), Series Hybrid Electric Vehicles (HEVs) and Parallel HEVs for various different drive cycles. VTool has also been validated for use in UDDS and HwFET cycles using on-road test results from the 2011 EcoCAR competition. By extension, the method could easily be extended for use in other cycles. The end result is a tool that can predict fuel consumption to a reasonable degree of accuracy for a variety of powertrains, calculate J1711 Utility Factor weighted energy consumption for Extended Range Electric Vehicles (EREVs) and determine the Well-to-Wheel impact of a given powertrain or fuel. VTool does all of this while performing all calculations explicitly and calculating all component losses to allow the user maximum access which promotes understanding and comprehension of the fundamental dynamics of automotive fuel economy and the powertrain as a system.
Master of Science
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6

Althaus, Joseph H. "An Embedded Nonlinear Control Implementation for a Hovering Small Unmanned Aerial System." Ohio University / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=ohiou1275530221.

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7

Arlinghaus, Mark C. "Autopilot Development for an RC Helicopter." Wright State University / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=wright1259002743.

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8

Argyle, Matthew Elliott. "Modeling and Control of a Tailsitter with a Ducted Fan." BYU ScholarsArchive, 2016. https://scholarsarchive.byu.edu/etd/5929.

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There are two traditional aircraft categories: fixed-wing which have a long endurance and a high cruise airspeed and rotorcraft which can take-off and land vertically. The tailsitter is a type of aircraft that has the strengths of both platforms, with no additional mechanical complexity, because it takes off and lands vertically on its tail and can transition the entire aircraft horizontally into high-speed flight. In this dissertation, we develop the entire control system for a tailsitter with a ducted fan. The standard method to compute the quaternion-based attitude error does not generate ideal trajectories for a hovering tailsitter for some situations. In addition, the only approach in the literature to mitigate this breaks down for large attitude errors. We develop an alternative quaternion-based error method which generates better trajectories than the standard approach and can handle large errors. We also derive a hybrid backstepping controller with almost global asymptotic stability based on this error method. Many common altitude and airspeed control schemes for a fixed-wing airplane assume that the altitude and airspeed dynamics are decoupled which leads to errors. The Total Energy Control System (TECS) is an approach that controls the altitude and airspeed by manipulating the total energy rate and energy distribution rate, of the aircraft, in a manner which accounts for the dynamic coupling. In this dissertation, a nonlinear controller, which can handle inaccurate thrust and drag models, based on the TECS principles is derived. Simulation results show that the nonlinear controller has better performance than the standard PI TECS control schemes. Most constant altitude transitions are accomplished by generating an optimal trajectory, and potentially actuator inputs, based on a high fidelity model of the aircraft. While there are several approaches to mitigate the effects of modeling errors, these do not fully remove the accurate model requirement. In this dissertation, we develop two different approaches that can achieve near constant altitude transitions for some types of aircraft. The first method, based on multiple LQR controllers, requires a high fidelity model of the aircraft. However, the second method, based on the energy along the body axes, requires almost no aerodynamic information.
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9

Osborne, Stephen R. "Transitions Between Hover and Level Flight for a Tailsitter UAV." Diss., CLICK HERE for online access, 2007. http://contentdm.lib.byu.edu/ETD/image/etd2054.pdf.

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10

Sanches, Matheus Pedroso. "Visual Flight Rules-based CollisionAvoidance System for VTOL UAV." Master's thesis, 2020. https://hdl.handle.net/10216/132896.

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Частини книг з теми "Electric VTOL"

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Zong, Jianan, Bingjie Zhu, and Zhongxi Hou. "Takeoff Performance Assessment and Energy Management Strategy of a Hybrid-Electric VTOL UAV." In Proceedings of 2021 International Conference on Autonomous Unmanned Systems (ICAUS 2021), 284–301. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-9492-9_29.

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2

Zheng, Weijie, Zijie Qin, Xi Zhao, Bo Zhu, and Kun Liu. "Evaluation of the Control Allocation Methods for DEP-VTOL Aircraft." In Lecture Notes in Electrical Engineering, 2442–52. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-6613-2_238.

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3

Sun, Hao, Zhou Zhou, Zhengping Wang, and Qiyuan Dong. "Transition Strategy Optimization of Tilt-Rotor VTOL UAV in Conversion Process." In Lecture Notes in Electrical Engineering, 1057–77. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2635-8_78.

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4

Staub, Franco Maurice, Yuji Shimizu, Dai Tsukada, Shosuke Inoue, Emery Premeaux, Chris Raabe, and Takeshi Tsuchiya. "A Propeller Evaluation and Selection Tool for Multicopter and VTOL Design." In Lecture Notes in Electrical Engineering, 309–22. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2689-1_23.

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Jia, Sijia, Zhenkai Zhang, Weijun Wang, and Chao Yang. "Flight Dynamics Modeling and Simulation of Propeller Deflected Slipstream VTOL Aircraft." In Lecture Notes in Electrical Engineering, 766–80. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-16-7423-5_76.

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6

Wang, Jianan, Kaidan Li, and Kewei Xia. "Intelligent Optimal Learning Control for Cooperative Formation Tracking of VTOL UAVs." In Lecture Notes in Electrical Engineering, 3005–14. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-6613-2_291.

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7

Zhu, Dehai, Yinong Zhang, Huimin Zhao, Ban Wang, and Zhenghong Gao. "Adaptive Fault-Tolerant Control of a Canard Rotor/Wing VTOL Aircraft." In Lecture Notes in Electrical Engineering, 3286–94. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-6613-2_319.

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8

Deng, Yangping. "Experimental Investigation on Ground Effect of Ducted Fan System for VTOL UAV." In Lecture Notes in Electrical Engineering, 1602–9. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_128.

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Wang, Jun, and Dang-Jun Zhao. "VTVL Trajectory Plannings via Convex Optimization and Pseudospectral Method for Mars Rover." In Lecture Notes in Electrical Engineering, 4667–80. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-15-8155-7_386.

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10

Czech, Jakub, and Wojciech Skarka. "Design of the Power Supply System for Vertical Take-Off and Landing Unmanned Aerial Vehicle." In Advances in Transdisciplinary Engineering. IOS Press, 2021. http://dx.doi.org/10.3233/atde210124.

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The article presents an analysis of the possibilities of supporting the Vertical Take off and Landing Unmanned Aerial Vehicle electric power systems by using photovoltaic cells. A typical commercial VTOL class drone with electric power was selected for analysis. Concepts of power supply supported by photovoltaic cells have been developed. Analysis of the potential change in performance through the use of such support are presented on the basis of the UAV simulation model and the model-based design. The simulation model takes into account not only the flight parameters of the drone, but also the drive system with the power supply system and the assumed variable lighting parameters. Such a multidisciplinary model was used to analyse the functional parameters. The analysis also includes hypothetical changes in the performance parameters of photovoltaic cells and their impact on the change in UAV performance as well as the impact of changes in the airframe geometry on the profitability of using such a solution.
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Тези доповідей конференцій з теми "Electric VTOL"

1

Moore, Mark. "NASA Puffin Electric Tailsitter VTOL Concept." In 10th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-9345.

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2

Darmstadt, Patarick, Timothy Krantz, Sheevangi Pathak, and Mark Valco. "Design Concepts to Meet EASA SC-VTOL-01 Single Failure Criteria." In Vertical Flight Society 78th Annual Forum & Technology Display. The Vertical Flight Society, 2022. http://dx.doi.org/10.4050/f-0078-2022-17608.

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The objective of the current work is to discuss European Union Aviation Safety Agency (EASA) SC-VTOL-01 single failure criteria, VTOL.2250(c). VTOL.2250(c) increases safety metrics compared to existing Vertical Takeoff and Landing (VTOL) regulations, creating new engineering challenges that must be addressed. Additionally, research and development targeting compliance against VTOL.2250(c) will more broadly benefit the VTOL industry, providing guidance for safer system designs. Prior studies have developed concept distributed propulsion and flight control (DPFC) system architectures and found they comply with EASA SC-VTOL-01 probabilistic failure criteria, VTOL.2510(a). Prior work developed two all-electric DPFC systems utilized in a quadrotor concept aircraft developed by the National Aeronautics and Space Administration (NASA); one uses interconnecting shafts and gearboxes to interconnect redundant motors with each rotor system and the other uses gearboxes to connect redundant motors locally, near each rotor. Common between the two electric DPFC systems were rotor shafts, epicyclic systems, and motors. The current work explores Category I failures in drive systems, relevant research to support fail-safe design practices for gear systems, research and adjacent industry trends in motor fail-safety and reliability, and proposed design concepts to comply with VTOL.2250(c). Continued research in fail-safe design concepts and design guidance will benefit eVTOL and conventional rotorcraft, alike. Continued research in these areas will benefit eVTOL certification against SC-VTOL-01, and could optimistically translate to more widespread adoption of similar fail-safe design concepts into new rotorcraft designs certified against CS-29.
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Ng, Wanyi, and Anubhav Datta. "Development of Propulsion System Models for Electric-VTOL Aircraft." In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-1750.

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Stoll, Alex M., Edward V. Stilson, JoeBen Bevirt, and Percy P. Pei. "Conceptual Design of the Joby S2 Electric VTOL PAV." In 14th AIAA Aviation Technology, Integration, and Operations Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2407.

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Demers Bouchard, Etienne, David Rancourt, and Dimitri N. Mavris. "Integration of Electric Propulsion in Efficient Heavy-Lift VTOL Concept." In 15th AIAA Aviation Technology, Integration, and Operations Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-3337.

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Ng, Wanyi, and Anubhav Datta. "Correction: Development of Propulsion System Models for Electric-VTOL Aircraft." In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-1750.c1.

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Fathepure, Meghana, Alexander L. Booker, Omar Abouzahr, Nicco Wang, and Daniel Tikalsy. "Design and Construction of an Inflatable-Winged VTOL Mars Electric Flyer." In AIAA AVIATION 2021 FORUM. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-2578.

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Ranasinghe, Naveen Deshan, and Wickrama Arachchige Don Lakitha Gunawardana. "Development of Gasoline-Electric Hybrid Propulsion Surveillance and Reconnaissance VTOL UAV." In 2021 IEEE International Conference on Robotics, Automation and Artificial Intelligence (RAAI). IEEE, 2021. http://dx.doi.org/10.1109/raai52226.2021.9508033.

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Cakin, Ugur, Zafer Kaçan, Zeynel Abidin Aydogan, and Ipek Kuvvetli. "Initial Sizing of Hybrid Electric VTOL Aircraft for Intercity Urban Air Mobility." In AIAA AVIATION 2020 FORUM. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3173.

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North, David D., Ronald C. Busan, and Greg Howland. "Design and Fabrication of the LA-8 Distributed Electric Propulsion VTOL Testbed." In AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-1188.

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