2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)最新文献_第2页

Brushless Doubly-Fed Reluctance Machine Drive for Turbo- Electric Distributed Propulsion Systems 涡轮电力分布式推进系统的无刷双馈磁阻电机驱动

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4987

Shivang Agrawal, A. Banerjee, R. Beach

引用次数: 8

Trim Analysis of a Classical Octocopter After Single-Rotor Failure 经典八旋翼机单旋翼失效后的配平分析

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5035

Ariel Walter, M. McKay, R. Niemiec, F. Gandhi

{"title":"Trim Analysis of a Classical Octocopter After Single-Rotor Failure","authors":"Ariel Walter, M. McKay, R. Niemiec, F. Gandhi","doi":"10.2514/6.2018-5035","DOIUrl":"https://doi.org/10.2514/6.2018-5035","url":null,"abstract":"The performance of an octocopter with single rotor failure is examined in hover and forward flight conditions. The aircraft model uses blade element theory coupled with a finite-state dynamic inflow model to determine rotor aerodynamic forces (thrust, drag, and side-force) and moments (rolling moment, pitching moment, and torque). Failure of various rotors is considered in both flight conditions and an understanding is developed of how the aircraft trims post-failure in terms of multirotor controls defined for the aircraft. In hover, the baseline octocopter trims with all rotors operating at the same rotational speed. When a rotor fails, trim solutions exist that utilize the original reactionless controls of the aircraft to drive the commanded thrust of the failed rotor to zero. The combination of reactionless controls used varies depending on the position of the failed rotor. Post-failure, the primary and reactionless multirotor controls are redefined for each rotor in terms of the original multirotor controls. In forward flight, rotor failure is recovered in a similar manner to the hover case, with additional inputs required to compensate for the rotor hub moments and in-plane forces that were not present in hover. Overall, trim solutions exist for any single rotor failure in both hover and forward flight at 10 m/s. In hover, rotor failure requires an additional 10.7% increase in power to trim, in forward flight this penalty is found to range between 7.7 and 13% depending on the rotor that has failed.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"114 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115733532","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

New Dynamic End-to-End Modeling of More Electric Aircraft Power Systems 多电动飞机动力系统的新动态端到端建模

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5011

Mehrdad Mark Ehsani, Ahmad Bashaireh

{"title":"New Dynamic End-to-End Modeling of More Electric Aircraft Power Systems","authors":"Mehrdad Mark Ehsani, Ahmad Bashaireh","doi":"10.2514/6.2018-5011","DOIUrl":"https://doi.org/10.2514/6.2018-5011","url":null,"abstract":"Aircraft power and propulsion system design is evolving towards more electric technology for the purpose of improving overall efficiency. This poses new challenges for modelling, simulation, optimal design of systems containing mechanical and electrical components, including many switching power electronic converters. The generalized gyrator theory and time-domain transfer function theory provide new tools for studying the dynamics and stability of such electromechanical systems. This paper presents these concepts to help with the analysis, design and control of the more electric aircraft. Using the generalized gyrator theory, the mechanical components can be transferred to the electrical side of the system and representedby their electrical models. The time-domain transfer function theory of power electronics provides a method to model switching power electronics converters as a generalized transformer. This allows for the referral of circuit elements from one side of the switching converter to the other. As a result, the complex aircraft electromechanical system can be reduced to an electrical circuit simplified model. This will assist in the detailed analysis, design and control of the system, prior to physical prototyping (iron-bird). In addition, the overall system circuit model will provide a better insight into the operation and interactions between the components of the system. Basic theory, example case studies, and future applications and benefits to the more electric aircraft will be presented and discussed","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"67 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114854456","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: 0

Design of Superconducting AC Propulsion Motors for Hybrid Electric Aerospace 用于混合动力航空航天的超导交流推进电机设计

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5000

Charalampos D. Manolopoulos, M. Iacchetti, Alexander C. Smith, P. Tuohy, X. Pei, M. Husband, Paul Miller

{"title":"Design of Superconducting AC Propulsion Motors for Hybrid Electric Aerospace","authors":"Charalampos D. Manolopoulos, M. Iacchetti, Alexander C. Smith, P. Tuohy, X. Pei, M. Husband, Paul Miller","doi":"10.2514/6.2018-5000","DOIUrl":"https://doi.org/10.2514/6.2018-5000","url":null,"abstract":"The aerospace industry has ambitious environmental emissions and noise reduction targets that have led to some radical proposals for future aerospace transportation technologies. One of the disruptive technologies identified is hybrid electric propulsion. The use of electrical machines for aerospace propulsion is not a new concept. Fully superconducting machines have the potential to deliver the step-change in specific torque, power and efficiency capabilities required for large civil transport aircraft applications. However fully superconducting machines are still in their infancy. This paper looks at the electromagnetic design of two different stator design concepts for an AC fully superconducting machine for an aerospace distributed fan motor using a benchmark aerospace specification. A benchmark aerospace specification of 1 MW was chosen and the design of a conventional permanent-magnet machine was used to assess the performance of the two equivalent fully superconducting AC motor designs. The AC fully superconducting machine includes superconducting bulk magnets mounted on a conventional rotor core and an MgB2 superconducting wire wound stator in a non-magnetic core. The paper looks at a fully superconducting air-cored stator design to reduce weight and a new yokeless stator design is proposed to reduce the armature losses. The paper will look at the key design issues of the different motor designs in relation to the current aerospace targets for efficiency and power densities.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123792565","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: 10

Development of Megawatt-Scale Medium-Voltage High Efficiency High Power Density Power Converters for Aircraft Hybrid-Electric Propulsion Systems 飞机混合动力推进系统中兆瓦级中压高效率高功率密度功率变换器的研制

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5007

Di Zhang, Jiangbiao He, D. Pan, M. Dame, M. Schutten

{"title":"Development of Megawatt-Scale Medium-Voltage High Efficiency High Power Density Power Converters for Aircraft Hybrid-Electric Propulsion Systems","authors":"Di Zhang, Jiangbiao He, D. Pan, M. Dame, M. Schutten","doi":"10.2514/6.2018-5007","DOIUrl":"https://doi.org/10.2514/6.2018-5007","url":null,"abstract":"Hybrid-electric propulsion system is an enabling technology to make the aircrafts more fuel-saving, quieter, and lower carbide emission. In this paper, a megawatt-scale power converter based on a hybrid three-level active neutral-point-clamped (3L-ANPC) topology is developed. To achieve high efficiency, the switching devices operated at carrier frequency in the 3L-ANPC converter are configured by the emerging Silicon Carbide (SiC) Metal-Oxide Semiconductor Field-Effect Transistors (MOSFETs), while the conventional Silicon (Si) Insulated-Gate Bipolar Transistors (IGBTs) are selected for the switches modulated at the fundamental output frequency. The dc-bus voltage is increased from the conventional 270 V to 2.4 kV to reduce the power cable weight in the aircraft. Unlike the traditional 400 Hz aircraft electric systems, the rated fundamental output frequency of the inverter here is boosted to 1.4 kHz to drive the high-speed motor. Systematic hardware development and new PWM strategy for the 3L-ANPC inverter will be presented in this paper, and the associated experimental results are shown to verify the performance of this MW-scale medium-voltage inverter. It is shown that the 1-MW power inverter achieves an efficiency of99% and power density of 12 kVA/kg, which provides a promising solution to the realization of high-efficiency high-density aircraft hybrid propulsion systems.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134407825","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: 18

An Approach for Utilizing Power Flow Modeling for Simulations of Hybrid Electric Propulsion Systems 利用潮流建模进行混合动力推进系统仿真的方法

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5018

Jeffryes W. Chapman, J. Litt

引用次数: 13

Early-Stages Comfort Simulation of an E-Aircraft 电子飞机早期舒适性仿真

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4986

Cassio Faria, F. Chauvicourt, R. Hallez, Claudio Colangeli, J. Cuenca, H. van der Auweraer, T. Olbrechts, Djiby Toure, Olivier Broca

{"title":"Early-Stages Comfort Simulation of an E-Aircraft","authors":"Cassio Faria, F. Chauvicourt, R. Hallez, Claudio Colangeli, J. Cuenca, H. van der Auweraer, T. Olbrechts, Djiby Toure, Olivier Broca","doi":"10.2514/6.2018-4986","DOIUrl":"https://doi.org/10.2514/6.2018-4986","url":null,"abstract":"The electrification of transportation systems is increasingly taking place in our every-day landscape, including aviation applications. Besides obvious challenges in thrust generation and safety due to the powertrain changes, there is another aspect of the multi-physical behavior of an aircraft that can be affected: acoustic noise. It is important for an e-aircraft designer to comprehend the impact of the system-level design choices on the acoustic noise radiation of the e-aircraft, whether one relates to environmental noise pollution or passenger comfort. This paper proposes a functional modelling scheme to allow for the assessment of interior cabin noise in the early stages of the aircraft design process. This is accomplished by the combination of three source processes: the air-borne, wind and structural-borne contributions. The simulation results presented here are qualitatively compared to experimental data collected from a light one-propeller conventional aircraft modified with an electric motor, demonstrating the ability of the proposed approach to match the main features of the measured data.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"633 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133285933","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: 0

System Weight Comparison of Electric Machine Topologies for Electric Aircraft Propulsion 电动飞机推进电机拓扑结构的系统重量比较

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4983

Aaron D. Anderson, Nathaniel J. Renner, Yuyao Wang, Shivang Agrawal, Samith Sirimanna, Dongsu Lee, A. Banerjee, K. Haran, Matthew J. Starr, J. Felder

{"title":"System Weight Comparison of Electric Machine Topologies for Electric Aircraft Propulsion","authors":"Aaron D. Anderson, Nathaniel J. Renner, Yuyao Wang, Shivang Agrawal, Samith Sirimanna, Dongsu Lee, A. Banerjee, K. Haran, Matthew J. Starr, J. Felder","doi":"10.2514/6.2018-4983","DOIUrl":"https://doi.org/10.2514/6.2018-4983","url":null,"abstract":"An important thrust in current aerospace research is aircraft electrification, including propulsion system electrification. For an electrified propulsion system to provide net benefit over conventional propulsion, high specific power, power density, and efficiency requirements of the electrical system must be met. This paper expands on previous work by comparing electric machine topologies for electric aircraft propulsors while considering tradeoffs in the power electronics, fault response equipment, and gearbox components. Permanent magnet synchronous machine (PMSM), brushless DC machine (BLDC), switched reluctance machine (SRM), brushless doubly-fed reluctance machine (BDFRM), and induction machine (IM) topologies are explored. A parametric design tool including finite element analysis is used to create a viable design for each machine type. Next, analytical sizing equations are used to scale the designed machines to varying operating speeds and aspect ratios. In addition, gearbox, power electronics, circuit breaker, clutch, thermal management system, and energy storage weights are predicted based on current power densities of research designs. It is well established that PMSMs have outstanding power density and this study shows that when considering additional drive and fault response components, PMSMs still maintain the weight advantage.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"246 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133928833","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: 44

A Review of the State-of-the-Art Superconductor Technology for High Power Applications 大功率超导体最新技术综述

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5030

M. Susner, T. Haugan

{"title":"A Review of the State-of-the-Art Superconductor Technology for High Power Applications","authors":"M. Susner, T. Haugan","doi":"10.2514/6.2018-5030","DOIUrl":"https://doi.org/10.2514/6.2018-5030","url":null,"abstract":"The all-electric or hybrid electric aircraft concepts promise to open up a new revolution in aviation design. However, with this paradigm shift comes problems in the use of existing materials. For example, normal conductors such as Cu or Al exhibit waste heat with a geometric dependence on current (Q=I2 R) which, for higher power (current) applications necessitates that costly and heavy cooling apparatus be installed. The sheer volume of conductor needed for high power applications also serves to increase weight. In this paper we advocate for the use of superconducting materials to serve the aerospace industry's need for high power electric aircraft as they can carry exponentially more current in the superconducting state than normal conductors, thus reducing weight and volume. The weight and size of any cooling apparatus associated with superconductivity will thus be much reduced in size as well. In rotating machines (i.e. motors and generators) superconductors have the added benefit of being able to sustain much higher magnetic fields than conventional materials, thus enabling higher efficiencies. In this paper we will first detail the advantages of superconductors for use in aircraft platforms and then proceed with brief summaries of the current state-of-the-art for the most advanced (in terms of R&D effort) superconducting systems. We will conclude with a brief summary in machine technology where we will address the problem of AC Losses.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"44 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123090392","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: 5

Multidisciplinary Optimization of Urban-Air-Mobility Class Aircraft Trajectories with Acoustic Constraints 具有声学约束的城市-空气机动类飞行器轨迹多学科优化

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4985

Robert Falck, Daniel Ingraham, Eliot D. Aretskin-Hariton

引用次数: 17