2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)最新文献_第4页

Impact of Electric Propulsion on Aircraft Noise - All-Electric Light Aircrafts Case Study 电力推进对飞机噪声的影响——全电动轻型飞机案例研究

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4982

R. Hallez, Claudio Colanaeli, J. Cuenca, L. De Ryck

{"title":"Impact of Electric Propulsion on Aircraft Noise - All-Electric Light Aircrafts Case Study","authors":"R. Hallez, Claudio Colanaeli, J. Cuenca, L. De Ryck","doi":"10.2514/6.2018-4982","DOIUrl":"https://doi.org/10.2514/6.2018-4982","url":null,"abstract":"Aircraft electrification is on the verge of radically changing air transportation. Energy-efficient distributed propulsion, vertical take-off and landing capabilities and reduced emissions are some examples of the great possibilities that electric propulsion offers and how it could disrupt air travel and urban air mobility in the future. Next to the many technological challenges associated with such new concepts, important regulatory barriers still need to be overcome to make it come true. One aspect of particular attention is the impact on environmental noise. In this paper, the acoustic performance of two all-electric light aircrafts is assessed based on ground and in-flight measurements. The investigated aircrafts are the Magnus eFusion, first all-electric aerobatic training airplane in the world and the Extra 330LE, world's first electric aircraft to tow a glider into the sky. For both airplanes, the actual impact of electric propulsion on exterior radiated noise during fly-over is quantified - for the first time - using two variants of the same aircraft, equipped with two different propulsion systems: in one case with a conventional piston engine, in the other case with an electric motor. Cabin noise is also assessed for the two aircraft variants. Sound quality metrics as well as sound source localization techniques are used to perform a detailed analysis of the interior and exterior aircraft noise and to get insight into the noise generation mechanisms. The manuscript details the complete set of measurement techniques which are available for acoustic engineers to develop quieter electric aircrafts in the future. It reports about the setup and execution of the test campaign; it describes the processing of the acquired data and discusses the major findings. Results highlight the different footprints of the two types of propulsion in terms of fly-over and cabin interior noise levels.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"19 4","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132467562","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

Modeling and Control Design for a Turboelectric Single Aisle Aircraft Propulsion System 涡电单通道飞机推进系统建模与控制设计

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5010

Joseph W. Connolly, Jeffryes W. Chapman, Erik J. Stalcup, Keith R. Hunker, A. Chicatelli, G. L. Thomas

{"title":"Modeling and Control Design for a Turboelectric Single Aisle Aircraft Propulsion System","authors":"Joseph W. Connolly, Jeffryes W. Chapman, Erik J. Stalcup, Keith R. Hunker, A. Chicatelli, G. L. Thomas","doi":"10.2514/6.2018-5010","DOIUrl":"https://doi.org/10.2514/6.2018-5010","url":null,"abstract":"A nonlinear dynamic model with full flight envelope controller is developed for the propulsion system of a partially turboelectric single-aisle aircraft. The propulsion system model consists of two turbofan engines with a large percentage of power extraction, feeding an electric tail fan for boundary layer ingestion. The dynamic model is compared against an existing steady state design model. An electrical system model using a simple power flow approach is integrated into existing modeling tools used for dynamic simulation of the turbomachinery of the vehicle. In addition to the simple power flow model of the electrical system, a more detailed model is used for comparison at a key vehicle transient flight condition. The controller is a gain scheduled proportional-integral type that is examined throughout the flight envelope for performance metrics such as rise time and operability margins. Potential improvements in efficiency for the vehicle are explored by adjusting the power split between the energy used for thrust by the turbofans and that extracted to supply power to the tail fan. Finally, an operability study of the vehicle is conducted using a 900 nautical mile mission profile for a nominal vehicle configuration, a deteriorated propulsion system at the end of its operating life, and an optimized power schedule with improved efficiency.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"1 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":"130938737","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: 14

High Frequency Electric Machines for Boundary Layer Ingestion Fan Propulsor 边界层吸入风扇推进用高频电机

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4990

Andy Yoon, K. Haran

引用次数: 13

Hierarchical Weight Optimization Design of Aircraft Power Electronics Systems Using Metaheuristic Optimization Methods 基于元启发式优化方法的飞机电力电子系统分层权重优化设计

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4980

Qian Li, R. Burgos, D. Boroyevich

引用次数: 9

Partial Discharge Detection in an Aeronautical Power Cable 航空电力电缆局部放电检测

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5033

M. Karadjian, N. Imbert, C. Munier, M. Kirkpatrick, E. Odic

引用次数: 3

A New Liquid Hydrogen Based Superconducting Coil Test Rig to Measure AC Losses 一种新型液氢超导线圈交流损耗测试装置

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5028

J. Hartwig, B. Fraser, G. Brown, David Koci, Keith R. Hunker, C. Bowman, L. Kohlman, P. Schrum, David Matten

{"title":"A New Liquid Hydrogen Based Superconducting Coil Test Rig to Measure AC Losses","authors":"J. Hartwig, B. Fraser, G. Brown, David Koci, Keith R. Hunker, C. Bowman, L. Kohlman, P. Schrum, David Matten","doi":"10.2514/6.2018-5028","DOIUrl":"https://doi.org/10.2514/6.2018-5028","url":null,"abstract":"This paper presents the design, development, operation, and test capabilities of a proposed superconducting coil testbed to measure AC losses at the NASA Glenn Research Center. Superconducting AC losses are important in the design of electric stators and rotors, power transmission lines, transformers, fault current limiters, magnets, and superconducting energy storage (not batteries). The new liquid hydrogen based rig will allow superconducting coil testing across a wide range of test parameters, including injected current (0−3400 A), frequency (0–400 Hz), magnetic field up to 0.6 T, phase angle between induced voltage and injected current (−180–180°), coil coolant temperature (18–28K), and AC power loss (5–30W). While the target application of interest is 20K superconducting MgB2 (the only superconductor that can presently be made with low AC losses) stator coils for future electric machines, the rig can accommodate test articles with straight wire, tape, cables, coils of any shape, any allowable combination of superconducting wire and fluid (e.g. YBCO coils and liquid nitrogen), and AC or DC testing. The new spin rig builds upon an existing Air Force spin rig through a more flexible mode of fluid control, a wider gap space for test articles (up to 10.2 cm) for test articles, and can accommodate test articles over a wider range of operating temperatures (18–95K) using liquid hydrogen, gaseous helium, or liquid nitrogen as the working fluid, thus supporting direct-cooled machines below 77K.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"60 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":"129157291","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: 1

Electric Propulsion Architecture Assessment via Signomial Programming 基于信号编程的电力推进结构评估

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5026

Aidan Dowdle, D. K. Hall, J. Lang

{"title":"Electric Propulsion Architecture Assessment via Signomial Programming","authors":"Aidan Dowdle, D. K. Hall, J. Lang","doi":"10.2514/6.2018-5026","DOIUrl":"https://doi.org/10.2514/6.2018-5026","url":null,"abstract":"This paper presents the application of signomial programming to the assessment and multidisciplinary optimization of electric propulsion systems. Analytic models for electrical and mechanical propulsion system components are developed that are compatible with the signo-mial programming objective and constraint forms. These models capture the dependence of mass and efficiency on material properties and operating conditions. Standalone optimization of the electrical cable and motor model illustrates a trade-off between mass and efficiency at the component level. These component models are subsequently integrated into various propulsion architectures and are optimized while taking into account the component dependencies (e.g., fan and motor shaft speed). Specifically, turbofan, turboelectric and geared turboelectric propulsion architectures are optimized on the metrics of fuel consumption and propulsion system mass. The results show that the optimal component masses and efficiencies depend on the propulsion architecture, operating point, and performance metric under consideration, and that signomial programming is useful for determining them.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"36 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":"124583977","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: 11

High-Speed Permanent Magnet Synchronous Machine for Short-Term Operation in an Electrically Powered High-Lift System 大功率电力系统中短期运行的高速永磁同步电机

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4989

G. Narjes, Felix Kauth, Jan Müller, Axel Mertens, Jörg Seume, Bernd Ponick

{"title":"High-Speed Permanent Magnet Synchronous Machine for Short-Term Operation in an Electrically Powered High-Lift System","authors":"G. Narjes, Felix Kauth, Jan Müller, Axel Mertens, Jörg Seume, Bernd Ponick","doi":"10.2514/6.2018-4989","DOIUrl":"https://doi.org/10.2514/6.2018-4989","url":null,"abstract":"The noise footprint of aircraft at airports is one of the major reasons, why many of these facilities are located on the outskirts of cities instead of near the city centre. One approach to reduce this footprint is to increase the lift coefficient by using electrically powered high-lift systems (EPHLS) which are located near each wing's flaps. Each system consists of a turbo compressor which is directly driven by a permanent magnet synchronous machine at a maximum rotational speed of 60,000 rpm and a maximum required power of 80 kW. Current investigations focus on the enhancement of the aircraft's take-off and landing which limit the operating time of the EPHLS to a maximum of 240 s. This paper will highlight the design of the three main components of the EPHLS, namely SiC converter, electrical machine, and turbo compressor. The machine design is significantly influenced by the short operating time, thus moving the critical thermal parameters to the transient regime of the temperature characteristics. The thermal parameters for this machine design will be discussed and iterated for several scaled power levels, as the EPHLS consists of several turbo compressors along the wing span with different ratings. These are thermally characterized and compared to conclude what the scaling of electrical machines for short-term operation means for the thermal characteristic parameters. In the end, a different reference design point for the electrical machine is identified, a fast and simple way for the scaling of electrical machine designs for short-term operation with respect to power is found and conclusions for the design and scaling of combined power electronics, electrical machine, and turbo compressor systems are drawn.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"9 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":"129516756","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

Optimal Propellers for a Small Hybrid Electric Fuel-Cell UAS 小型混合动力燃料电池无人机的最佳螺旋桨

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4981

R. MacNeill, D. Verstraete

引用次数: 6

Recent Advances of Power Electronics Applications in More Electric Aircrafts 电力电子技术在电动飞机上应用的最新进展

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5008

Jiangbiao He, Di Zhang, D. Torrey

引用次数: 25