2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)最新文献_第5页

Putting Universities in Charge Yields Early Success for NASA Aeronautics 让大学负责为NASA航空航天业带来早期成功

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3570

K. Datta, J. Cavolowsky, R. Barhydt

引用次数: 0

Conceptual Design of a 10-passenger Thin-haul Electric Aircraft 10座轻型电动飞机的概念设计

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3589

Boning Yang, Fangyuan Lou, N. Key

引用次数: 2

Solid-State Exergy Optimized Electric Aircraft Thermal and Fault Management 固态火用优化电动飞机热与故障管理

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3576

R. Dyson, L. Rodriguez, Mary Ellen Roth, P. Raitano

引用次数: 5

Demagnetization Simulations of High-Power Electric Motors for Reliable Electric Aircrafts 可靠电动飞机用大功率电动机消磁仿真

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3585

Saeed Jahangirian, A. Hassanpour, S. Krishnan

引用次数: 3

Design and Analysis of the Thermal Management System of a Hybrid Turboelectric Regional Jet for the NASA ULI Program NASA ULI项目混合动力涡轮电动区域喷气机热管理系统设计与分析

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3572

Mingxuan Shi, M. Sanders, Alan Alahmad, Christopher A. Perullo, Gokcin Cina, D. Mavris

{"title":"Design and Analysis of the Thermal Management System of a Hybrid Turboelectric Regional Jet for the NASA ULI Program","authors":"Mingxuan Shi, M. Sanders, Alan Alahmad, Christopher A. Perullo, Gokcin Cina, D. Mavris","doi":"10.2514/6.2020-3572","DOIUrl":"https://doi.org/10.2514/6.2020-3572","url":null,"abstract":"A team of researchers from multiple universities are collaborating on the demonstration of a hybrid turboelectric regional jet for 2030 under the NASA ULI Program. The thermal management is one of the major challenges for the development of such an electric propulsion concept. Existing studies hardly modeled the thermal management systems with the propulsion systems nor integrated it to the aircraft for system- and mission-level analyses. Therefore, it is very difficult to verify whether a design of the thermal management system is feasible and optimal based on current literature. To fill this gap, this paper presents a design of the thermal management system for the hybrid turboelectric regional jet under the ULI program and integrates it to the aircraft. The TMS is tested against the cooling requirements, where the thermal loads from the electric propulsion system are quantified through the whole mission. Potential solutions for peak thermal loads during takeoff and climb are also proposed and analyzed, where additional coolant or phase change materials are used. Moreover, the impacts of the TMS on the system- and mission-level performance are investigated by the presented integration approach as well. It is discovered that a basic oil-air thermal management system cannot fully remove the heat during the early mission segments. Using additional coolant or phase change materials as heat absorption can handle such heating problem, but penalty due to additional weight is added. It is found that greater penalties in fuel burn and takeoff weight are added by additional coolant solution than the phase change material solution.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"8 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":"126433552","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: 15

Electromagnetic Redesign of NASA’s High Efficiency Megawatt Motor NASA高效率兆瓦电机的电磁重新设计

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3600

Thomas F. Tallerico, J. Scheidler, Dongsu Lee, K. Haran

{"title":"Electromagnetic Redesign of NASA’s High Efficiency Megawatt Motor","authors":"Thomas F. Tallerico, J. Scheidler, Dongsu Lee, K. Haran","doi":"10.2514/6.2020-3600","DOIUrl":"https://doi.org/10.2514/6.2020-3600","url":null,"abstract":"NASA’s high efficiency megawatt motor (HEMM) is being developed to achieve the performance needed by single aisle class electrified aircraft. It is a 1.4 MW electric machine designed as a generator for NASA’s STARC-ABL concept vehicle. It has performance objectives of greater than 16 kW/kg electromagnetic specific power and 98% efficiency. A significant flaw in the preliminary electromagnetic design of HEMM was recently discovered. The stator teeth in the preliminary design would have caused the magnetic flux in the rotating components of HEMM to oscillate at a very high frequency (12,240 Hz). Two independent energy loss analyses are presented to show that the frequency of this oscillation would have been high enough to cause eddy current losses that significantly exceed the rotor’s loss limit (51 W), despite the very small magnitude of the oscillation (<0.01 T). To eliminate these rotor losses while continuing to meet the target performance, it was determined that the stator teeth needed to be removed and the electromagnetic geometry of the motor needed to be revised. The revised, slotless HEMM design is summarized. Also presented is a sensitivity analysis of the new design to key unknown variables such as the temperature of and number of turns in the superconducting rotor coils and the stator winding’s average temperature.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"9 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":"121389956","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

Optimal Weight Power System Design and Synthesis for More Electric Aircraft 多电动飞机最优重量动力系统设计与综合

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3545

Angel A. Recalde, S. Bozhko, J. Atkin

{"title":"Optimal Weight Power System Design and Synthesis for More Electric Aircraft","authors":"Angel A. Recalde, S. Bozhko, J. Atkin","doi":"10.2514/6.2020-3545","DOIUrl":"https://doi.org/10.2514/6.2020-3545","url":null,"abstract":"The synthesis of a power distribution architecture for More Electric Aircraft requires weight optimization in order to reduce energy consumption. The weight of an aircraft power distribution system depends on various factors such as the functional and safety requirements, as well as component selection and location. Functional and safety requirements can be translated into a set of connectivity and reliability constraints to produce an architecture that represents an abstract topology of the power system. However, component selection and location aims to produce a solution that is closer to a final implementation. Then, this paper presents an optimization based design formulation that synthesizes a power system architecture considering component selection and location in order to shorten the gap between the topology and the physical implementation. Given the complexity in producing and solving such formulation, linear transformations are performed to enable the use powerful commercial solvers and reach a minimum weight electrical distribution system. Therefore, the design is presented as a Mixed Integer Linear Programming problem and a case study is used to exemplify the synthesis of a power distribution architecture that is optimal.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"398 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":"116506114","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

Commercial Hybrid Electric Aircraft Thermal Management Sensitivity Studies 商用混合动力飞机热管理敏感性研究

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3558

J. Rheaume, C. Lents

{"title":"Commercial Hybrid Electric Aircraft Thermal Management Sensitivity Studies","authors":"J. Rheaume, C. Lents","doi":"10.2514/6.2020-3558","DOIUrl":"https://doi.org/10.2514/6.2020-3558","url":null,"abstract":"Weight sensitivity studies were carried out on a Thermal Management System (TMS) of a parallel Hybrid Electric Propulsion (HEP) system of a commercial single aisle aircraft. The HEP system features a battery that feeds a Low Spool Motor (LSM) to assist the fan of a high bypass ratio geared turbofan. The first study gauged the impact of the Energy Storage, Conversion, & Distribution (ECS&D) system on the size of the Air Oil Cooler (AOC) and the Fuel Oil Cooler (FOC). The HEP system results in decreased FOC weight by 11% due to lower fuel flow at higher temperature due to the LSM and its heat load. Conversely, AOC weight increased by 32% also due to the higher heat load. A second study examines the effect of efficiency of the battery and motor drive on the TMS. Increases in efficiency of the battery from 95% to 96% and the motor drive (MD) from 96% to 98% decrease the weights of their Ram air Coolant Coolers (RCC) by 26% and 38%, respectively, as well as the heat sink air flow through them. Lastly, the altitude at which the Battery ram air Cooled Cooler (Bat RCC) was sized to reject the full heat load on a hot day (8 kft vs 20 kft) was examined. A TMS weight decrease in excess of 50 lbs. is possible for the 20 kft case provided that batteries are sufficiently pre-cooled below ambient temperature prior to take-off.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"25 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":"124590219","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

A Model Based Approach to Analyze the Impact of Different Ambient Temperatures on Emergency Flight Time 基于模型的不同环境温度对应急飞行时间影响分析

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3546

Murat Keskin, Oğuz Kağan Keles, M. Bagriyanik

引用次数: 0

Power Distribution and Thermal Management Modeling for Electrified Aircraft 电气化飞机的功率分配和热管理建模

2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2020-08-17 DOI: 10.2514/6.2020-3578

Saakar Byahut, A. Uranga

{"title":"Power Distribution and Thermal Management Modeling for Electrified Aircraft","authors":"Saakar Byahut, A. Uranga","doi":"10.2514/6.2020-3578","DOIUrl":"https://doi.org/10.2514/6.2020-3578","url":null,"abstract":"Despite the substantially lower energy per unit mass of batteries compared to hydrocarbon fuels, electrification of the aircraft propulsion system could lead to increases in energy efficiency for certain types of missions. This work builds on the electric powertrain component models (battery, converter, motor) from previous work and presents models for the propulsor, power distribution system, thermal management system(TMS), and wiring in order to complete an all-electric propulsion system framework. This framework is used to simulate a propulsion system with power loads representative of a commuter aircraft mission that transports 19 passengers over 100nmi. Results show that the battery makes up over 60% of the total propulsion system mass, indicating that improvements in battery technology are essential to lower propulsion system mass. Despite making up a smaller fraction of the propulsion system mass, the other components impact the overall system via their efficiency since that sizes the battery and the TMS. Distributed propulsion is found to lower the propulsion system mass, with diminishing returns beyond 10 propulsors due to the increased heat rejection and hence TMS mass.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"78 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":"126305097","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: 6