2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)最新文献

{"title":"The Characteristics of Film Capacitors at Room Temperature and in Liquid Nitrogen","authors":"Chanyeop Park, Jia Wei, Siddarth Singh, S. Narra, L. Graber, M. Imperatore","doi":"10.2514/6.2018-5014","DOIUrl":"https://doi.org/10.2514/6.2018-5014","url":null,"abstract":"One of the key candidate technologies for future electric aircrafts is high-temperature superconductivity (HTS), which could drastically increases the power density by reducing volume and weight of power systems and devices. HTS devices require cryogenic operating temperature. Over the past several decades, HTS motors, generators, and cables technologies have been successfully demonstrated. However, the cryogenic operation of power electronics technology requires further research and development. Among the key components of power electronics devices, capacitors, an indispensable component, are one of the greatest challenges for successfully operating the cryogenic power electronics devices. The purpose of the study is exploring the behavior of various types of film capacitors at cryogenic temperatures. Here, we used liquid nitrogen to obtain 77 K as it is the representative cryogenic temperature. Both the capacitance and voltage rating of film capacitors were compared at room temperature and in liquid nitrogen.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"6 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":"114950029","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 and Simulation of a Commercial Hybrid Electric Aircraft Thermal Management System","authors":"J. Rheaume, Charles E. Lentsii","doi":"10.2514/6.2018-4994","DOIUrl":"https://doi.org/10.2514/6.2018-4994","url":null,"abstract":"The baseline design of the Thermal Management System (TMS) of a parallel, hybrid electric aircraft engine for a commercial, single aisle aircraft with batteries for energy storage has been completed. The Hybrid Electric Propulsion (HEP) system features a low spool motor to assist the propulsor, its attendant motor drive, propulsion batteries, and supplementary batteries to cover TMS electric loads during electric augmentation on takeoff and climb. The TMS further includes the heat loads sunk to engine oil including bearings, the fan drive system, and the accessory gearbox. The model was executed under hot day conditions (ISA + 15) over the mission sizing points when electric augmentation is active. REHEATS, a proprietary, object-oriented modeling tool created at the United Technologies Research Center, was used to model the TMS and find the solution with minimal fuel consumption. This study establishes a baseline for comparison of energy storage using batteries for future comparison. The results predict that the TMS of a HEP aircraft increases fuel consumption by 3.4% during takeoff, climb, and cruise.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"37 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":"115996968","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":"Hybrid Electric Aircraft Battery Heat Acquisition System","authors":"Ravi Annapragada, Aritra Sur, R. Mahmoudi, M. Macdonald, C. Lents","doi":"10.2514/6.2018-4992","DOIUrl":"https://doi.org/10.2514/6.2018-4992","url":null,"abstract":"The electric drive train or electric energy & power storage, conversion and distribution (ESC&D) system of a hybrid electric aircraft, even at high efficiency, will reject significant heat at relatively low temperature. Thus effective thermal management of the ESC&D system is critical to realizing the potential benefits of a hybrid electric aircraft as the thermal management system (TMS) can add excessive weight (heat exchangers and pumps) and impose excessive parasitic power consumption (pumps and fans) and drag (engine fan stream air and ram air) on the aircraft. A 5MW parallel hybrid configuration [1] supplies a representative set of requirements for the development of TMS technology. The ESC&D system is comprised of a 1780 kWhr battery system, 2×2.2 MW motor drives, 2×2.1 MW motors and the associated power panels and feeders. A study has been completed to develop the lowest weight, highest performance (least amount of thermal resistance) approach for acquiring cell level battery heat such that it can be cooled by an aircraft TMS supplied coolant. The baseline battery heat acquisition (HA) system, based on SOA automotive electric vehicle packaging is approximately the same weight as the battery cells themselves, thus doubles the weight of the battery package. Alternative approaches currently under study, have the promise of reducing this weight by >60%.","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":"130575585","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":"Case Studies in Initial Sizing for Hybrid-Electric General Aviation Aircraft","authors":"D. Finger, Carsten Braurr, C. Bil","doi":"10.2514/6.2018-5005","DOIUrl":"https://doi.org/10.2514/6.2018-5005","url":null,"abstract":"This paper showcases the potential influence of hybrid-electric propulsion systems on the performance of general aviation aircraft. Using the Cirrus SR-22 as a baseline, parallel- and serial-hybrid propulsion configurations are explored. For these case studies a high level approach is chosen, using an innovative initial sizing methodology to determine weight or energy consumption of new aircraft concepts. Mission parameters and aerodynamic performance are varied and the impact on aircraft fuel and energy consumption, as well as on take-off mass is studied. The studies' results indicate that hybrid-electric aircraft consume less energy than conventionally propelled designs for certain missions. However, the aircraft's design point, in terms of wing loading and installed power must be changed: Hybrid-electric aircraft should be sized with a higher power-to-weight ratio and a higher wing loading than their conventional counterparts.","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":"126213821","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":"Investigation of a Cooling System for A Hybrid Airplane","authors":"R. Kabir, K. Kaddoura, F. McCluskey, J. Kizito","doi":"10.2514/6.2018-4991","DOIUrl":"https://doi.org/10.2514/6.2018-4991","url":null,"abstract":"Airplane cooling process can be performed with the help of two different techniques. One is global cooling system and the other is local cooling system. The goal of present paper is to investigate both cooling systems which may be good candidates for a future hybrid airplane. In the parametric study of global cooling section, the present research determines the parameters which affect air mass flow rate required to provide the necessary cooling for the electrical components necessary to make a hybrid plane a reality. The analysis is performed for a cooling process based on an open cycle Reverse Brayton cycle or at times called an air refrigeration system. The main components of the cooling system will be a compressor, a heat exchanger and a turbine. Outside air will be drawn and pressurized to a certain pressure using a compressor, and the compressed air will be forced through a heat exchanger to reduce its temperature as low as possible to provide necessary cooling. After that, the air will expand through an expansion device (most cases a turbine) to reduce pressure and temperature to a cycle minimum. Finally, the processed air will now be available to cool the electrical components. We will analyze the above-mentioned options to determine the most economical and or feasible systems by comparing the processed air efficiency with the ram air that may also be used for cooling purposes. The novelty of the present work lies on the concept that, the cooling fluid is air and does not have a weight penalty for the airplane. The later section we discuss an example of a local cooling system. A classic local cooling technique discussed is based on a heat pipe technology. Theoretically, heat pipes can transport heat from a heat source and release it to an ambient heat sink. The paper investigates the thermal performance of thermosiphons of different percentage fills. By detecting various thermal parameters of the manufactured thermosiphons, a general relation between the thermal performance and the percentage fill is drawn. Thermal parameters analyzed include thermal resistance, heat transfer coefficient, and Nusselt number. The present paper shows that as the amount of working fluid increases in a heat pipe, the thermal performance improves till it reaches a limit at 50% fill. As the percentage fill increases beyond 50%, the thermal performance of a thermosiphon remains constant.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"275 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":"131748722","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":"Development of a Conceptual Design Model for Aircraft Electric Propulsion with Efficient Gradients","authors":"Benjamin J. Brelje, J. Martins","doi":"10.2514/6.2018-4979","DOIUrl":"https://doi.org/10.2514/6.2018-4979","url":null,"abstract":"Research on electric aircraft propulsion has greatly expanded in the last decade, revealing new insights on the unique features of the electric aircraft design problem, and identifying shortcomings in existing analysis techniques and tools. In this paper, we survey currently-available analysis codes for aircraft with electric propulsion. We introduce a new conceptual design and optimization toolkit-OpenConcept-built for aircraft incorporating electric propulsion. Open Concept consists of three parts: a library of simple, conceptual-level models of common electric propulsion components; a set of analysis routines necessary for aircraft sizing and optimization; and several example aircraft models. All of Open Concept's codes have been analytically differentiated, enabling the use of OpenMDAO 2's efficient Newton solver, as well as gradient-based optimization methods. Open Concept supports parametric cost modeling and waste heat management at the component level, enabling realistic thermal and economic constraints in optimization studies. We present a case study involving the electrification of existing turboprop airplanes. We model the Daher TBM 850 and Beechcraft King Air C90GT in Open Concept, and validate the sizing, weights, fuel burn, and takeoff field length analyses. We then define a series hybrid electric propulsion architecture for the King Air, and perform a retrofit study. Finally, we perform multidisciplinary design optimization to minimize both fuel burn and trip cost for varying design ranges and assumed battery specific energy levels. We ran more than 750 multidisciplinary optimization cases with full mission analysis. Each optimization runs in approximately 2 minutes on a typical notebook PC. We demonstrate that Open Concept is a flexible and efficient way of performing conceptual-level analysis of aircraft with unconventional propulsion architectures.","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":"130853313","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":"Exploration of Additive Manufacturing for HTS Cable Components for Electric Aircrafts","authors":"P. Cheetham, R. Nowell, Aws Al-Taie, James McAulev, Chul Han Kim, L. Graber, S. Pamidi","doi":"10.2514/6.2018-5027","DOIUrl":"https://doi.org/10.2514/6.2018-5027","url":null,"abstract":"High temperature Superconducting (HTS) technology has the potential to deliver the required power densities necessary for electric aircrafts. A promising HTS cable design for electric aircraft applications that we have been investigating is the Superconducting Gas-Insulated Transmission Line (S-GIL). The S-GIL requires insulator spacers that are compatible with cryogenic temperatures as well as the high electrical and mechanical stresses. One of the major mechanical stresses currently limiting the design options is the compatibility of insulation materials and designs for cryogenic temperatures and associated thermal shocks. This paper discusses the investigation of using various 3D printed materials to fabricate prototype insulator spacer designs for the S-GIL and evaluate their compatibility with the required cryogenic operating conditions. The studies demonstrated that several materials and designs selected show suitability to operate at cryogenic temperature and we plan to proceed with further mechanical and electrical characterization of the 3D printed components.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"46 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":"114436732","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":"Applications for Hybrid Electric Power and Energy Supplementation on a Single-Aisle Airliner","authors":"Reed A. Danis, J. Freeman, Benjamin T. Schiltgcn","doi":"10.2514/6.2018-5021","DOIUrl":"https://doi.org/10.2514/6.2018-5021","url":null,"abstract":"In the realm of hybrid electric aircraft propulsion, two power and energy management concepts utilizing primary gas turbine engines and supplementary battery packs are defined and evaluated: “boost” is the use of supplemental power to alleviate design requirements of the engine and other parts of the propulsion system, and “offset” is the use of supplemental energy to achieve net reductions in fuel consumption and/or harmful gaseous emissions such as CO2 and NOx. This paper explores several applications of batteries for boost and offset power as applied to the ECO-150 vision vehicle. While the potential benefits are apparent and tangible, the battery mass required to realize them often dominates the tradeoff. Maximizing the net benefits from battery power supplementation requires a careful application of when and how battery power is used throughout the design mission, as well as an in-depth understanding of how incorporating supplemental battery power affects propulsion system sizing trends.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"39 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":"126563235","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 High-Fidelity, Low-Latency, FPGA-Based, Real-Time Development Platform for Advanced Aircraft Power Systems","authors":"Zhenhua Jiang, Hao Huang, Syed Hossain","doi":"10.2514/6.2018-5019","DOIUrl":"https://doi.org/10.2514/6.2018-5019","url":null,"abstract":"This paper presents recently-developed capabilities of a real-time development platform and its application in simulating and testing an advanced aircraft power system in real time. This platform is based upon FPGA (Field Programmable Gate Array - a reconfigurable, parallel computing device) that handles on-chip computation in real time with latency of 32 FPGA clock cycles (potentially within 200 nanoseconds). The component models solved by the innovative computational solvers are based on the first principles and can capture very fast electromagnetic transient processes happening in more-electric aircraft power systems. Discussed here in detail is a generalized, reconfigurable, real-time computational model for simulating the electro-magnetic and electro-mechanical dynamics occurring in a variety of electric machines. This real-time electric machine model is to solve systems of differential and algebraic equations in parallel on FPGA, and the main components include parallel and pipelined computational modules for input data sampling, mechanical dynamics calculation, abc-to-dq transformation, flux and current calculations, torque or horsepower calculations, dq-to-abc transformation, and data output, all of which are controlled by a synchronization signal with 32 clock cycles. The presented model can be used for power hardware-in-the-loop testing through the sensing, amplification and communication interfaces with external equipment, and can be easily reconfigured to emulate different types of electric machines such as synchronous machines, induction machines, and permanent-magnet machines, by setting up proper parameters for the real-time model. Simulation studies demonstrate that the real-time results for different types of generators, configured by using the same electric machine simulation model, agree well with the offline results obtained for those different generators using other standard tools. An advanced aircraft power system including an advanced engine starter/ generator (AESG) has been studied on the real-time development platform to validate the computational accuracy, by comparing the real-time results with offline simulation results using classical tools. The real-time power system model exhibits a great agreement in output variables with the offline simulation model.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"19 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":"126596887","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":"On-Board Battery Monitoring and Prognostics for Electric-Propulsion Aircraft","authors":"Chetan S. Kulkarni, J. Schumann, Indranil Roychoudhury","doi":"10.2514/6.2018-5034","DOIUrl":"https://doi.org/10.2514/6.2018-5034","url":null,"abstract":"The reliability of the propulsion system of an aircraft is paramount for the aircraft safety and hence the aircraft health must be monitored continuously. In contrast to fuel-operated aircraft, electric battery-operated propulsion system poses specific problems, such as, the remaining battery power does not linearly decrease and cannot be measured directly. In this paper, we describe a combined monitoring and prognostics architecture that can continuously monitor all components of the electric propulsion system with respect to safety and performance properties as well as state of charge and rest of useful life for the battery. Our system combines a detailed electrochemical battery model for Li-ion batteries with a powerful prognostics engine based upon an Unscented Kalman Filter with the R2U2 monitoring device, which provides efficient observers for metric temporal logic and Bayesian reasoning. R2U2 is a real-time, REALIZABLE, RESPONSIVE, UNOBTRUSIVE UNIT, which continuously monitors sensor readings, outputs of the prognostics engine, as well as the flight software status for safety, performance, and security properties. We illustrate our architecture with two case studies, one reporting actual flight tests with an X8+ octo-copter and the other a software-in-the-loop simulation with an unmanned Edge 540 electric aircraft model.","PeriodicalId":276296,"journal":{"name":"2018 AIAA/IEEE Electric Aircraft Technologies Symposium (EATS)","volume":"17 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":"132658079","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}