2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)最新文献_第3页

Energy Management for Electric Aircraft via Optimal Control: Cruise Phase 基于最优控制的电动飞机能量管理:巡航阶段

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3565

Mengyuan Wang, M. Mesbahi

{"title":"Energy Management for Electric Aircraft via Optimal Control: Cruise Phase","authors":"Mengyuan Wang, M. Mesbahi","doi":"10.2514/6.2020-3565","DOIUrl":"https://doi.org/10.2514/6.2020-3565","url":null,"abstract":"The demand for energy savings and reducing environmental and noise impact has lead to an unprecedented interest and rapid development of electric aircraft technology. In order to improve the efficiency of an All-Electric Aircraft (AEA) during the cruise phase, this paper formulates the corresponding energy optimization as an optimal control problem (OCP). The OCP is formulated around minimizing the so-called Direct Operating Cost (DOC), a combination of time-related and battery charge costs. It is shown that this OCP leads to a singular control structure when the thrust is taken as the control input. We then proceed to derive the analytical solution on the singular arc using the Pontryagin’s Minimum Principle (PMP); moreover, the control structure and \"junction\" points are obtained through the numerical solver Tomlab. One of the main contributions of this work is considering the impact of the battery dynamics on the overall operating cost. In particular, by implementing the so-called Empirical Circuit Model (ECM) for the battery in our problem setup, we provide a comparative analysis on the effect of the battery modeling on the resulting optimal thrust profile.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"138 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124712656","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2

Analysis of Self-Cooling method of a Rotor using Buoyancy Driven Convection 浮力驱动对流转子自冷方法分析

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3574

R. Kabir, O. Y. Abotsi, J. Kizito

引用次数: 0

Electromagnetic Analysis of Fully Superconducting Synchronous Machines for Future Turbo Electric Propulsion Systems 未来涡轮电力推进系统中全超导同步电机的电磁分析

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3550

Y. Terao, Y. Ishida, H. Ohsaki, D. Heideman, K. Okai, H. Taguchi

引用次数: 3

High Efficiency Megawatt Motor Thermal Stator Preliminary Design 高效率兆瓦级电机热定子初步设计

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3602

Gerald Szpak, Andrew D. Smith, Jerald T. Thompson, A. Woodworth, R. Jansen

{"title":"High Efficiency Megawatt Motor Thermal Stator Preliminary Design","authors":"Gerald Szpak, Andrew D. Smith, Jerald T. Thompson, A. Woodworth, R. Jansen","doi":"10.2514/6.2020-3602","DOIUrl":"https://doi.org/10.2514/6.2020-3602","url":null,"abstract":"The High Efficiency Megawatt Motor (HEMM) is being designed to meet the needs of Electrified Aircraft Propulsion (EAP). The key objective of HEMM is to establish a motor technology which simultaneously attains high specific power (>16kW/kg ratio to electromagnetic weight) and high efficiency (>98%) by judicious application of high temperature superconducting wire and integrated thermal management. This paper describes the design of the first full size prototype stator for the HEMM motor. This prototype will be used to retire development risks for both the thermal management system design as well as manufacturing challenges. The stator must be able to operate up to a 500 amps without internal temperatures exceeding 200°C. Key features of the stator are liquid cooling of the coils by circulating fluid between the rotor and the stator, a slotless core, and a vacuum tube that houses the rotor. Having the rotor in a vacuum minimizes the heat transfer to the rotor from the stator. This is critical to maintaining cryogenic temperatures on the rotor coils. Addressing the thermal management challenges of the stator involves a combination of minimizing the losses to reduce the heat load and optimizing the cooling system by maximizing the conductive heat transfer in the coils and the convective heat transfer from the coils to the fluid. Manufacturing challenges being addressed include: vacuum pressure impregnation of the assembly with epoxy, winding and fabrication of the vacuum chamber. As this paper will show, the design is feasible from a manufacturing standpoint and the analysis indicates that it will be possible to achieve the performance goal of operating up to 500 amps without internal temperatures exceeding 200 °C","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123655282","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 12

Computational Evaluation of an OML-based Heat Exchanger Concept for HEATheR 基于oml的石楠换热器概念的计算评价

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3575

E. Sozer, D. Maldonado, K. Bhamidipati, Sydney L. Schnulo

引用次数: 8

Feasibility Assessments of a Hybrid Turboelectric Medium Altitude Long Endurance Unmanned Aerial Vehicle 混合动力涡轮电动中高空长航时无人机的可行性评估

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3577

Gokcin Cinar, A. Markov, Jonathan C. Gladin, Elena Garcia, D. Mavris, S. Patnaik

{"title":"Feasibility Assessments of a Hybrid Turboelectric Medium Altitude Long Endurance Unmanned Aerial Vehicle","authors":"Gokcin Cinar, A. Markov, Jonathan C. Gladin, Elena Garcia, D. Mavris, S. Patnaik","doi":"10.2514/6.2020-3577","DOIUrl":"https://doi.org/10.2514/6.2020-3577","url":null,"abstract":"Electrified propulsion systems can provide potential environmental and performance benefits for future aircraft. The choice of the right propulsion architecture and the power management strategy depends on a number of factors, the airframe, electrification objectives and metrics of interest being the most critical ones. Therefore, the generic advantages and disadvantages of various electrified propulsion architectures must be quantified to assess feasibility and any possible benefits. Moreover, the objectives and the metrics of interest can be different for military applications than commercial ones. This research investigates the feasibility of turboelectric and hybrid turboelectric propulsion architectures integrated within a medium altitude long endurance surveillance unmanned aerial vehicle. The electrified propulsion system is desired to provide the same endurance and takeoff and landing field length characteristics of the baseline aircraft. This paper presents the results of the first phase of this research where only the electrified propulsion system is sized while the airframe is kept fixed. Physics-based models and a generic mission analysis methodology are used to evaluate the performance of the major subsystems of the propulsion system and to provide a full flight mission history. A state of the art rechargeable battery is employed for the hybrid case. Various power management strategies where the battery is discharged and charged in different flight segments are explored for varying sizes of battery packs. Results indicate that, while none of the architectures can offset the added weight and the efficiency factors of the electrical components as expected, the hybrid turboelectric propulsion architecture can provide fuel burn and performance benefits when sized for, and operated under, a specific set of power management strategies.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"70 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124983318","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 4

Multidisciplinary Systems Analysis of a Six Passenger Quadrotor Urban Air Mobility Vehicle Powertrain 六人座四旋翼城市空中机动车辆动力系统多学科系统分析

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3564

G. L. Thomas, Jeffryes W. Chapman, Jonathan Fuzaro Alencar, Hashmatullah Hasseeb, David J. Sadey, J. Csank

{"title":"Multidisciplinary Systems Analysis of a Six Passenger Quadrotor Urban Air Mobility Vehicle Powertrain","authors":"G. L. Thomas, Jeffryes W. Chapman, Jonathan Fuzaro Alencar, Hashmatullah Hasseeb, David J. Sadey, J. Csank","doi":"10.2514/6.2020-3564","DOIUrl":"https://doi.org/10.2514/6.2020-3564","url":null,"abstract":"There is a high degree of research interest in the design space for electric vertical takeoff and landing (eVTOL) vehicles, because these vehicles are seen as key enablers for urban air mobility. This work further explores the eVTOL design space, by presenting an analysis of a six-passenger eVTOL quadrotor powertrain, with integrated power, propulsion, and thermal management systems modeled using the Numerical Propulsion System Simulation (NPSS) and the NPSS Power System Library. Four powertrain architectures are modeled at the same design point and compared over a design mission. Results from an architecture trade study show that a hybrid architecture performs best in terms of range, however, the hybrid needs batteries with high specific energy and specific power in order to obtain a benefit over turboelectric architectures. Parameteric sensitivity studies are conducted to determine correlations between component parameters and system metrics. This data provides useful indicators for further technological improvement. Lastly an initial TMS model is presented, and sensitivity studies on TMS design parameters are presented as well, to show high level TMS design trends.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"49 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114076942","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 9

Tradespace Exploration of Electrified Propulsion and More-Electric Aircraft Generators 电气化推进和多电飞机发电机的贸易空间探索

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3583

M. Boyd, K. Yost, S. Patnaik

{"title":"Tradespace Exploration of Electrified Propulsion and More-Electric Aircraft Generators","authors":"M. Boyd, K. Yost, S. Patnaik","doi":"10.2514/6.2020-3583","DOIUrl":"https://doi.org/10.2514/6.2020-3583","url":null,"abstract":"The ongoing quest for higher electrical power on board electrified aircraft propulsion systems and more-electric aircraft is placing significant importance and challenges on rightly designed electric machines. As the power growth trend continues, the availability of robust and lightweight megawatt-class generators is critical. The design for these high-power generators provides significant challenges compared to present needs, and therefore a better understanding of the feasible generator design space and potential trade-offs between suitable efficiency, specific power, and performance requirements is necessary. Understanding this tradespace helps to reduce risk in generator development and allows for improved coordination between generator designers and aircraft-system integrators. To help achieve this goal, a Generator Design Tool has been developed by the Air Force Research Laboratory. It is a population-based design tool for wound-field synchronous machines that applies a genetic algorithm in order to perform multi-objective optimization to minimize mass and loss. The optimization relies on a magnetic equivalent circuit model to assess the machine’s performance and ensure that all design requirements are fully satisfied. The tradespace exploration capabilities of the tool are leveraged to investigate trends in the size and performance of generator designs for electrified aircraft and more-electric aircraft. Trade-offs in number of poles, mass versus loss, and in setting various design constraints are investigated. Limitations in high-speed operation and possible options for opening up the design space to higher speeds while potentially adding complexity and risk in the design were explored.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"295 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-08-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123935352","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 2

A Cryogenically-Cooled MW Inverter for Electric Aircraft Propulsion 一种用于电动飞机推进的低温冷却MW逆变器

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3598

Ruirui Chen, Jiahao Niu, Ren Ren, Handong Gui, Fred Wang, L. Tolbert, Benjamin B. Choi, G. Brown

引用次数: 18

A Study of Large Scale Power Extraction and Insertion on Turbofan Performance and Stability 大规模抽插功率对涡扇性能和稳定性的影响研究

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3547

Jeffryes W. Chapman

引用次数: 6