2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)最新文献_第5页

Novel Thermal Energy Conversion Technologies for Advanced Electric Air Vehicles 先进电动飞行器的新型热能转换技术

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4993

R. Dyson

引用次数: 6

Dynamic Flight Simulation of Spanwise Distributed Electric Propulsion for Directional Control Authority 面向方向控制机构的展向分布式电力推进动力飞行仿真

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4997

J. Freeman, Garrett T. Klunk

{"title":"Dynamic Flight Simulation of Spanwise Distributed Electric Propulsion for Directional Control Authority","authors":"J. Freeman, Garrett T. Klunk","doi":"10.2514/6.2018-4997","DOIUrl":"https://doi.org/10.2514/6.2018-4997","url":null,"abstract":"A linear time-invariant state-space model was developed to simulate the six-degree-of-freedom aircraft dynamics of the Aircraft for Distributed Electric Propulsion Throttle-based Flight Control (ADEPT-FC), a 34 lb remote controlled aircraft featuring eight overwing electric ducted fans (EDFs) distributed spanwise along the wing's trailing edge. This model utilized parasite drag estimates from OpenVSP's parasite drag tool, trimmed stability coefficients from VSPAERO's stability coefficient solver, and mass properties measured from the as-built aircraft to populate the traditional vehicle dynamics portion of the model's state-space matrices. A second-order state-space frequency model of propulsor dynamics was developed and tuned to the frequency response of the Schübeler EDF as measured in wind-tunnel testing. The influence of propulsor thrust on the vehicle's dynamics was derived and superimposed into the vehicle dynamics state-space model, bridging the gap between a conventional vehicle's state-space model and the propulsor dynamics frequency models for each propulsor. This updated vehicle dynamics model can be provided both aircraft control surface deflections and propulsor thrust inputs to simulate the dynamic response of the vehicle. Without consideration of anticipated propulsion airframe integration (PAI) cross-coupling effects, the simulator developed herein suggested that asymmetric throttle mixing of the EDFs should provide a similar response to that of a rudder deflection. It is anticipated that addition of the PAI effects will magnify the roll rate associated with the maneuver, caused by thrust-induced lift over the outside wing. Further development of this technology could enable a reduction or elimination of the aircraft's vertical tail.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"23 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":"128300982","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

A New High-Temperature Sensing Device by Making Use of TBC Thermistor for Intelligent Propulsion Systems 基于TBC热敏电阻的新型智能推进系统高温传感装置

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5015

Franklin Li Duan, Haotian Weng, Zhonglin Ji, Mingkai Hu, Xueqiang Cao, Qiang Wang, Jing Shao, Yuzhen Lin, Jianchen Wang, Zhichao Wang

{"title":"A New High-Temperature Sensing Device by Making Use of TBC Thermistor for Intelligent Propulsion Systems","authors":"Franklin Li Duan, Haotian Weng, Zhonglin Ji, Mingkai Hu, Xueqiang Cao, Qiang Wang, Jing Shao, Yuzhen Lin, Jianchen Wang, Zhichao Wang","doi":"10.2514/6.2018-5015","DOIUrl":"https://doi.org/10.2514/6.2018-5015","url":null,"abstract":"Thermal barrier coating (TBC) is an important material for aero-engine as a good thermal and electrical insulator. However this ceramic layer becomes electrically conductive at elevated temperatures above 600°C. By making use of its thermal resistance sensitivity to ambient temperature a smart thermal sensor can also be formulated to monitor the surface temperature on aero-engine turbine blade. In this paper the fabrication of this new sensor is reported together with comprehensive high-temperature characterizations such as repeatability, responsiveness and measurement error evaluation under various high temperature cycling and aero-engine onsite combustion test. Results show this sensor is capable to test the surface temperature in 500–1 000°C range or higher. YSZ-based (yttria-stabilized zirconia) TBC thermistor sensor shows a reliable and repeatable resistor vs temperature behavior and comparable responsiveness as conventional thermalcouple device with the measurement errors in 3%. Sensor fabrication is fairly simpels just involving a platinum soldering on TBC surface for wiring connection to outside meters. A new test array based on the YSZ thermal resistor is proposed as a temperature distribution monitor and verified by the aid of thermal-electrical interactive simulations. This simple methodology can be used for quick checking of surface temperature on turbine guide vane used in combustion chamber and other relevant parts.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"29 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":"132795567","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, Fabrication, and Critical Current Testing of No-Insulation Superconducting Rotor Coils for NASA's 1.4 MW High-Efficiency Megawatt Motor NASA 1.4 MW高效兆瓦电机无绝缘超导转子线圈的设计、制造和临界电流测试

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5002

J. Scheidler, Thomas F. Tallerico

引用次数: 20

Propulsion Scaling Methods in the Era of Electric Flight 电动飞行时代的推进尺度方法

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4978

Michael J. Duffy, Abigail E. Sevier, R. Hupp, E. Perdomo, S. Wakayama

引用次数: 17

Research and Development Status of Manned Electric Flapping-Wing Aircraft 载人电动扑翼飞机的研究与发展现状

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-4999

L. Qing, Nie Xiaofang, Zhou Ximing

引用次数: 0

Mission Analysis and Emissions for Conventional and Hybrid-Electric Regional Jet Aircraft 常规和混合动力支线喷气飞机的任务分析和排放

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-08 DOI: 10.2514/6.2018-5025

Gabrielle E. Wroblewski, Phillip J. Ansell

{"title":"Mission Analysis and Emissions for Conventional and Hybrid-Electric Regional Jet Aircraft","authors":"Gabrielle E. Wroblewski, Phillip J. Ansell","doi":"10.2514/6.2018-5025","DOIUrl":"https://doi.org/10.2514/6.2018-5025","url":null,"abstract":"The mission performance and lifecycle CO2 emissions of a simulated hybrid-electric regional transport aircraft were analyzed utilizing a flight performance simulation developed in MATLAB/Simulink. Publicly-available Embraer ERJ-175 data was used as a model to simulate a representative regional jet transport. After completing simulations to obtain the flight performance of a baseline, conventional regional jet aircraft, a parallel hybrid drivetrain was embedded into the model, and a series of flight performance simulation data were obtained for a representative hybrid-electric regional jet. Various missions with different degrees of hybridization and battery specific energy densities were simulated and the resulting range and fuel burn characteristics were compared to the conventional system. To investigate the potential for hybrid-electric aircraft to reduce aircraft CO2emissions, the CO2emissions from both fuel burn and production of battery energy were modeled for each hybrid aircraft configuration. The results indicate that dramatic reductions in CO2emissions per passenger mile are achievable when compared to conventional systems of equivalent range for all hybrid cases. However, only mid-future battery technology allowed for reductions in CO2emissions per passenger mile when compared to the maximum range conventional mission.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"387 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":"114904454","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: 7

NASA's Magnetic Gearing Research for Electrified Aircraft Propulsion 美国国家航空和宇宙航行局电气化飞机推进的磁性传动装置研究

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-07 DOI: 10.2514/6.2018-4988

J. Scheidler, V. Asnani, Thomas F. Tallerico

引用次数: 41

Tail Area Reduction for Aircraft with Spanwise Distributed Electric Propulsion 面向展向分布式电力推进飞机尾翼面积减小研究

2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS) Pub Date : 2018-07-01 DOI: 10.2514/6.2018-5022

Garrett T. Klunk, J. Freeman, Benjamin T. Schiltgen

{"title":"Tail Area Reduction for Aircraft with Spanwise Distributed Electric Propulsion","authors":"Garrett T. Klunk, J. Freeman, Benjamin T. Schiltgen","doi":"10.2514/6.2018-5022","DOIUrl":"https://doi.org/10.2514/6.2018-5022","url":null,"abstract":"Spanwise arrays of electrically driven propulsors may enable significant reductions to the required vertical tail area of an aircraft. The relationship between traditional empennage design and the driving requirements detailed in 14 CFR Part 25 was mapped, and the opportunities in which spanwise distributed electric propulsion could influence the empennage design were identified. The design of the electric microgrid that transmits and controls the flow of power to the propulsors was found to play a critical role in evaluating the potential merits of those opportunities. Careful design of the microgrid architecture was found to relax the asymmetric thrust design condition for the vertical tail to a point of irrelevance. Furthermore, active control of differential thrust between the propulsors could provide dynamic yaw stability to the aircraft, allowing the entire vertical tail to be removed. In contrast, however, a lighter weight microgrid architecture designed with no reconfigurability could exacerbate the asymmetric thrust and require a larger-than-nominal vertical tail. This paper explores the above opportunities and their associated costs as applied to the ECO-150 vision vehicle.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"72 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114614176","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: 13