2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)最新文献

{"title":"Integrated Propulsive and Thermal Management System Design for Optimal Hybrid Electric Aircraft Performance","authors":"Philip C. Abolmoali, A. Donovan, S. Patnaik, Patrick T. McCarthy, Dominic J. Dierker, N. Jones, R. Buettner","doi":"10.2514/6.2020-3557","DOIUrl":"https://doi.org/10.2514/6.2020-3557","url":null,"abstract":"The use of hybrid-electric propulsion systems aboard aircraft present opportunities for improved vehicle range and endurance, reduced fuel burn, as well as lower acoustic and thermal signatures. The energy benefits anticipated by such architectures may be offset, however, by new thermal management challenges introduced by the heat generated within the components of a hybrid-electric power train. A system level modeling approach that integrates the propulsion and thermal management subsystems is therefore critical to providing insight into the various tradeoffs. The current paper explores the reduction in fuel consumption offered by a series hybrid propulsion system using an integrated system modeling approach. A numerical model of the propulsive, thermal management, and flight dynamics subsystems was developed to simulate component and system level performance of a fixed wing, 11901 lb. medium altitude long endurance (MALE) vehicle, conventionally driven by a turboprop engine.. A thermal management system was integrated with the propulsive subsystem which utilized closed loop fuel cooling for electrical devices within the hybrid drive train, as well as a Polyalphaolephin (PAO) coolant loop to absorb the heat from several aircraft level auxiliary heat loads. Ram air was utilized to provide a heat sink for the PAO cooling loop, as well as the fuel loop to ensure return-to-tank fuel temperature limits are maintained. For a notional 18 hour flight mission, with respect to the conventional propulsion system, a fuel savings of 750 lb. was obtained, despite a gain of 708 lb. associated with the added weight of electrical devices within the drive train.","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":"124312490","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}

{"title":"Design of Electric Machine for Electric Aircraft: A Case Study of Rotor-stator Configurations and Magnet Arrangements","authors":"Hiroshi Mitsuda, Y. Miyama, Kazumasa Ito, M. Yamada, H. Fukumoto","doi":"10.2514/6.2020-3586","DOIUrl":"https://doi.org/10.2514/6.2020-3586","url":null,"abstract":"Recent research on aircraft propulsion systems has looked at saving fuel and reducing carbon emissions. In particular, for electric machines used in electric aircraft, high specific density, efficiency, and power factor are needed. We studied suitable rotor-stator configurations and magnet arrangements for a 250 kW electric machine to be used in small electric aircraft by focusing on specific density. We determined that a double rotor electric machine with a polar anisotropic magnet can improve power factor by 14% as compared with a conventional inner rotor, and it can also achieve a higher efficiency and power factor. In addition, we demonstrated a novel high-efficiency heat transfer method suitable for a double rotor electric machine, designed a 5.0 kW/kg electric machine, and manufactured a prototype double rotor motor to assess the possibility of retaining teeth.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"154 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":"123262845","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}

{"title":"Model Based Optimization of Propulsion Inverter for More-Electric Aircraft Applications Using Double Fourier Integral Analysis","authors":"Mustafeez-ul-Hassan, Zhao Yuan, Hongwu Peng, A. Emon, Yingzhuo Chen, F. Luo","doi":"10.2514/6.2020-3596","DOIUrl":"https://doi.org/10.2514/6.2020-3596","url":null,"abstract":"More-electric aircraft (MEA) concept is getting popular as it increases system efficiency with less costs. The concept leads to numerous challenges including power density and volume. This paper presents a novel application of model based optimization (MBO) on 3L-TNPC inverter to determine the optimal semi-conductor selection, modulation strategy, and passive components. The algorithm extensively relies on double fourier integral analysis (DFIA) for selection of the modulation strategy and filter design. The algorithm helps optimize the design of a 450 kVA three-phase full SiC-MOSFET based inverter with peak efficiency of 99.47%. And the estimated converter efficiency at full-load is 99.10%. The algorithm developed is scalable and can be extended for future high-performance inverter design applications.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"38 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":"128337900","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}

{"title":"A Novel Approach for Noise Rejection and Partial Discharge Identification in Electric Drives for Aerospace","authors":"P. Cheetham, M. Bosworth, G. Montanari, R. Ghosh, P. Seri","doi":"10.2514/6.2020-3599","DOIUrl":"https://doi.org/10.2514/6.2020-3599","url":null,"abstract":"Aerospace electrification has to go through significant innovations regarding adjustable speed drives, which are needed to increase specific power and effectiveness of propulsion and power control systems. This involves electrical insulation design with high-electric field and, therefore, increased risk of accelerated insulation aging. This risk becomes dramatic if highly-energetic degradation phenomena, such as partial discharges, PD, incept in (unavoidable) insulation defects. However measuring partial discharges, that is, the property associated with the fastest electrical degradation mechanism in organic insulation, has to face an increasing amount of issues compared to sinusoidal AC voltage supply. Referring to power electronics for rotating machines drives, the main difficulty lies with the extraction of partial discharge pulses from the noise produced by switch commutation, especially when the slew rate is fast and the operating voltage is high, compared to the threshold for partial discharge inception. Since partial discharges tend to occur mostly during voltage rise and fall times, thus simultaneously to switching noise, poor techniques for noise rejection and partial discharge identification may affect significantly any quality, commissioning and diagnostic test performed on electrical devices and apparatus supplied by power electronic waveforms. This paper presents a novel approach to partial discharge and noise separation, which can work also for very fast switch rise times, and increased operating voltage and frequency. Based on experimental testing, this paper shows that considering the time domain, rather than the frequency domain on which noise filtering is commonly based, and resorting to signal variance evaluation, partial discharge pulses can be extracted effectively from commutation noise.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"7 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":"116428557","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}

{"title":"Integrated Power Modeling for a Solar-Powered, Computationally-Intensive Unmanned Aircraft","authors":"Or D. Dantsker, Mirco Theile, M. Caccamo","doi":"10.2514/6.2020-3568","DOIUrl":"https://doi.org/10.2514/6.2020-3568","url":null,"abstract":"In recent years, we have seen an uptrend in the popularity of UAVs driven by the desire to apply these aircraft to areas such as precision farming, infrastructure and environment monitoring, surveillance, surveying and mapping, search and rescue missions, weather forecasting, and more. The traditional approach for small size UAVs is to capture data on the aircraft, stream it to the ground through a high power data-link, process it remotely (potentially off-line), perform analysis, and then relay commands back to the aircraft as needed. Given the finite energy resources found onboard an aircraft (battery or fuel), traditional designs greatly limit aircraft endurance since significant power is required for propulsion, actuation, and the continuous transmission of visual data. All the mentioned application scenarios would benefit by carrying a high performance embedded computer system to minimize the need for data transmission. A major technical hurdle to overcome is that of drastically reducing the overall power consumption of these UAVs so they can be powered by solar arrays, and for long periods of time. This paper describes an integrated power model for a solar-powered, computationally-intensive unmanned aircraft that includes power models for solar generation, aircraft propulsion, and avionics. These power consumption and generation models are described, derived, and integrated into a cohesive system-wide aircraft power model that is presented in the form of a systemic flow diagram. Power balance expressions are also imposed based on temporal and physical constraints. Compared to works in the existing literature, the integrated model presented follows a holistic approach for UAV modeling that encompasses aircraft, propulsion, and solar models under realistic assumptions. Additionally, in order to enable high fidelity estimation while requiring minimal computation power, the model was developed to estimate the power consumption and generation based on flight path state, without needing precise aerodynamic measurements, e.g. angle-of-attack. Several of the methods have already been evaluated by means of ground and flight testing, as well as simulation, and showed errors ranging from negligible to approximately 5%. The motivation behind this work is the development of computationally-intensive, long-endurance solar-powered unmanned aircraft, the UIUC Solar Flyer, which will have continuous daylight ability to acquire and process high resolution visible and infrared imagery. Therefore, having a holistic integrated power model that can encompass power generation and consumption allows further aircraft and mission design and optimization can be performed.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"132 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":"122915383","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}

{"title":"High Efficiency Megawatt Motor Risk Reduction Activities","authors":"R. Jansen, J. Scheidler, Thomas F. Tallerico, P. Kascak, A. Woodworth, Andrew D. Smith, R. Dyson, W. Sixel, Jerald T. Thompson, Erik J. Stalcup, Yaritza De Jesus-Arce, David Avanesian, K. Duffy, Paul J. Passe, Gerald Szpak","doi":"10.2514/6.2020-3559","DOIUrl":"https://doi.org/10.2514/6.2020-3559","url":null,"abstract":"The High Efficiency Megawatt Motor (HEMM) is being designed to meet the needs of Electrified Aircraft Propulsion (EAP). A detailed design is in progress with changes that are informed by component testing. These component risk reduction activities are being conducted in three key areas: cryogenic cooler design, superconducting rotor coil design and manufacturing, and stator thermal management. The key objective of HEMM is to establish a motor technology which simultaneously attains high specific power (>16 kW/kg ratio to electromagnetic weight) and high efficiency (>98%) by judicious application of high temperature superconducting wire and integrated thermal management. Another important feature is to achieve the performance goals with an eye to aircraft integration constraints. HEMM is intended to be a direct drive motor or generator that can be cooled with a standard aircraft cooling loop that is used for other electronics on the aircraft. The updated design is presented highlighting changes from the preliminary design that were a result of knowledge gained through hardware tests of subcomponents. An overview of those subcomponent tests is also provided. The HEMM technology could be applied to a range of aircraft types that require megawatt level electrical power.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"96 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":"122508981","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}

{"title":"Design Space Exploration Study and Optimization of a Distributed Turbo-Electric Propulsion System for a Regional Passenger Aircraft","authors":"Stefan Biser, M. Filipenko, M. Boll, Nir Kastner, G. Atanasov, M. Hepperle, D. Keller, D. Vechtel, M. Noe","doi":"10.2514/6.2020-3592","DOIUrl":"https://doi.org/10.2514/6.2020-3592","url":null,"abstract":"Electric propulsion systems are considered as one possibility to reach the ambitious goals of the European Union’s Flightpath 2050 with regards to greenhouse gas emissions and noise. It has been claimed in several publications that Distributed Electric Propulsion (DEP) offers significant improvement in aerodynamic efficiency and thus a reduction in structural weight of the wing and noise emissions as well as additional degrees of freedom concerning flight control. To not outweigh those advantages by heavier drivetrains, the components within the electric propulsion system have to be extremely lightweight, efficient and reliable at the same time. The German nationally funded project SynergIE evaluates DEP for a 70 PAX regional reference aircaft with two (SE-2), six (DEP-6) and twelve (DEP-12) propulsion units with a turbo-electric drivetrain layout. This study aims to quantify the effect on the specific block fuel consumption for the different numbers of propulsors based on Top Level Aircraft Requirements (TLARs). The approach contains a coupled electric drivetrain system model which is based on physically derived, analytical models for each component linking specific subdomains, e.g., electromagnetics, structural mechanics and thermal analysis. A genetic algorithm is applied to optimise the key performance indicators (KPIs) of the electric system, before the results are fed back to the aircraft sizing process. It has been identified that constraints such as installation space or architectural decisions such as the number of propulsors have significant influence on the drivetrain weight and efficiency and interact with the whole aircraft sizing process, esp. with reference to nacelle weight and drag and thus the block fuel consumption. The study shows that the DEP-6 and DEP-12 project aircraft both have a potential of reducing the specific block fuel consumption by approx. 4.2 % and 5.8 % respectively in case of direct driven propellers, while for a geared-drive scenario a total reduction of up to 7.6 % in case of DEP-6 and 8.5 % in case of DEP-12 is possible, all compared to the direct-driven baseline (BSL) aircraft SE-2.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"16 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":"124364488","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}

{"title":"Assembly and Qualification of a Slotless Stator Assembly for a MW-Class Permanent Magnet Synchronous Machine","authors":"T. Balachandran, Samith Srimmana, Aaron Anderson, X. Yi, Nathaniel J. Renner, K. Haran","doi":"10.2514/6.2020-3584","DOIUrl":"https://doi.org/10.2514/6.2020-3584","url":null,"abstract":"This paper discusses the manufacturing process and qualification procedures of a slotless stator for a 1-MW high-speed permanent magnet synchronous machine. The motor, targeted to reach 13 kW/kg, is assembled with form-wound air-core armature windings which utilize litz wire as the conductor. A prototype is being developed and a full-power test will be done in the near future. The insulation, mechanical and thermal qualification test procedures of the stator are discussed in detail. Results showed that the manufacturing process and tolerances significantly affect the machine performance. Various assembly challenges of this slotless stator and their impacts on performance targets are illustrated.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"11 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":"128013659","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}

{"title":"Battery Evaluation Profiles for X-57 and Future Urban Electric Aircraft","authors":"J. Chin, Eliot D. Aretskin-Hariton, Daniel Ingraham, Dustin L. Hall, Sydney L. Schnulo, J. Gray, E. Hendricks","doi":"10.2514/6.2020-3567","DOIUrl":"https://doi.org/10.2514/6.2020-3567","url":null,"abstract":"Battery energy density is one of the most critical design parameters for sizing all-electric aircraft, but it’s easily overestimated. Establishing the effective, usable energy density is con-fused by varying degrees of margin needed to account for structural and thermal management between different cell chemistry and pack designs. A better methodology is needed to fairly compare emerging battery technologies for electric aircraft. Currently, there is a loss of critical information when vehicle trade studies are performed using \"nominal\" published cell-level performance metrics. Aircraft power demands rarely match these nominal power profiles, and aircraft designers lack the ability to accurately simulate the battery performance and temperature off-nominally unless the battery chemistry is well established. Conversely, battery suppliers are unable to publish more realistic performance metrics due to a lack of generalized reference cases. This can lead to poor assumptions. For example, aircraft studies may assume a fixed discharge efficiency of a battery, when in reality the usable energy in a pack is dependent on the power and thermal profile. Information needed to properly assess weight penalties for thermal management is also typically poorly characterized when assessing candidate batteries.This paper serves to better inform battery development, and, similarly, provide aircraft designers with more realistic assumptions for applying knockdown margins in their designs. Detailed power and thermal performance estimates are described, which also provide a starting point for sizing power and thermal budgets using experimentally derived battery models. Results show that the average X-57 aircraft battery-to-shaft efficiency is 77.3% for a particular optimized mission. Considering a 25% reserve on the battery capacity, only close to half of the original 55.3kWh ‘nominal’ pack energy can be converted to useful work during a mission. Further estimates on a clean-sheet quad-rotor optimization show an average 82.7% battery-to-shaft efficiency, using 98% peak efficiency inverters and 97.4% peak efficiency motors. Although higher battery efficiencies are possible using larger packs, the resulting weight penalty negates improvement in vehicle performance. These trade-offs and resulting power profiles are provided as a starting point to better assess future battery designs.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"68 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":"133576593","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}

{"title":"High-Efficiency Turboelectric Propulsion Drive based on Medium-Voltage SiC Indirect Matrix Converter","authors":"Benjamin Luckett, Jiangbiao He, R. Dyson","doi":"10.2514/6.2020-3597","DOIUrl":"https://doi.org/10.2514/6.2020-3597","url":null,"abstract":"Turboelectric propulsion is one of the most promising technologies to reduce fuel burn for large aircraft, compared to all-electric propulsion technologies which have limited power density with batteries. However, the conventional two-stage voltage source back-to-back power converter between the ac-power from a generator and the desired ac power for a propulsion motor typically exhibits low efficiency and low power density. In this paper, an indirect matrix converter (IMC) based on Silicon Carbide MOSFETs is investigated for direct ac-ac power conversion between the generator and the propulsion motor. The IMC does not require any bulky dc-link capacitor bank or inductors, and the output current is more sinusoidal, eliminating the need of a lossy sinewave or dv/dt filter. Moreover, to reduce the cable weight and system copper losses in aircraft electrical systems, medium-voltage dc of 2~3 kV is adopted to develop the IMC. Simulation results are presented to evaluate the performance of the IMC based aircraft turboelectric propulsion drive.","PeriodicalId":403355,"journal":{"name":"2020 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"214 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":"116158794","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}