Electric Aircraft Fueled by Liquid Hydrogen and Liquefied Natural Gas
The paper is a review of the opportunities and challenges of cryogenic power devices of electric aircraft, and the ongoing research and development efforts of the government agencies and the industry. Liquid Hydrogen (LH2) and Liquefied Natural Gas (LNG) are compared to support high temperature supe...
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creator | Telikapalli, Srikar Swain, Roberto M. Cheetham, Peter Kim, Chul H. Pamidi, Sastry V. |
description | The paper is a review of the opportunities and challenges of cryogenic power devices of electric aircraft, and the ongoing research and development efforts of the government agencies and the industry. Liquid Hydrogen (LH2) and Liquefied Natural Gas (LNG) are compared to support high temperature superconducting (HTS) and normal metal devices, respectively. The power devices were assumed to operate at the normal boiling point of the fuel used. The efficiencies of the electrical devices are estimated based on state-of-the-art technology. The mass flow rates and total fuel requirements for both the cryogenic fuels required to maintain the operating temperatures of the devices were simulated using thermal network models. A twin-aisle, 300 passenger aircraft with a 5.5 h flight duration was used for the models. The results show that the required masses of LH2 and LNG are 744 kg and 13,638 kg, respectively for the cooling requirement. The corresponding volumes of LH2 and LNG required are 9,760 and 30,300 L, respectively. In both cases, the estimated mass of the fuel needed for the aircraft is more than what is needed to maintain the cryogenic environment of the power devices. It was concluded that an electric aircraft with LNG cooled normal metal devices is feasible. However, an aircraft with HTS devices and cooled with LH2 is more attractive if the ongoing R&D efforts on HTS devices and LH2 infrastructure are successful. The emission reductions would be substantially higher with LH2, particularly when H2 is produced using renewable energy sources. |
doi_str_mv | 10.1088/1757-899X/1241/1/012035 |
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Liquid Hydrogen (LH2) and Liquefied Natural Gas (LNG) are compared to support high temperature superconducting (HTS) and normal metal devices, respectively. The power devices were assumed to operate at the normal boiling point of the fuel used. The efficiencies of the electrical devices are estimated based on state-of-the-art technology. The mass flow rates and total fuel requirements for both the cryogenic fuels required to maintain the operating temperatures of the devices were simulated using thermal network models. A twin-aisle, 300 passenger aircraft with a 5.5 h flight duration was used for the models. The results show that the required masses of LH2 and LNG are 744 kg and 13,638 kg, respectively for the cooling requirement. The corresponding volumes of LH2 and LNG required are 9,760 and 30,300 L, respectively. In both cases, the estimated mass of the fuel needed for the aircraft is more than what is needed to maintain the cryogenic environment of the power devices. It was concluded that an electric aircraft with LNG cooled normal metal devices is feasible. However, an aircraft with HTS devices and cooled with LH2 is more attractive if the ongoing R&D efforts on HTS devices and LH2 infrastructure are successful. The emission reductions would be substantially higher with LH2, particularly when H2 is produced using renewable energy sources.</description><identifier>ISSN: 1757-8981</identifier><identifier>EISSN: 1757-899X</identifier><identifier>DOI: 10.1088/1757-899X/1241/1/012035</identifier><language>eng</language><publisher>Bristol: IOP Publishing</publisher><subject>Aircraft ; Boiling points ; Electronic devices ; Emission standards ; Emissions control ; Fly by wire control ; High temperature ; Liquefied natural gas ; Liquid hydrogen ; Mass flow rate ; Operating temperature ; Passenger aircraft ; R&D ; Renewable energy sources ; Research & development ; Thermal simulation</subject><ispartof>IOP conference series. 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Notwithstanding the ProQuest Terms and Conditions, you may use this content in accordance with the terms of the License.</rights><lds50>peer_reviewed</lds50><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c3115-1c4af917992b28b02a993ce0fb459bccaf09f069096e5062ba121b4fffbaaa443</citedby><cites>FETCH-LOGICAL-c3115-1c4af917992b28b02a993ce0fb459bccaf09f069096e5062ba121b4fffbaaa443</cites></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktopdf>$$Uhttps://iopscience.iop.org/article/10.1088/1757-899X/1241/1/012035/pdf$$EPDF$$P50$$Giop$$Hfree_for_read</linktopdf><link.rule.ids>314,780,784,27924,27925,38868,38890,53840,53867</link.rule.ids></links><search><creatorcontrib>Telikapalli, Srikar</creatorcontrib><creatorcontrib>Swain, Roberto M.</creatorcontrib><creatorcontrib>Cheetham, Peter</creatorcontrib><creatorcontrib>Kim, Chul H.</creatorcontrib><creatorcontrib>Pamidi, Sastry V.</creatorcontrib><title>Electric Aircraft Fueled by Liquid Hydrogen and Liquefied Natural Gas</title><title>IOP conference series. Materials Science and Engineering</title><addtitle>IOP Conf. Ser.: Mater. Sci. Eng</addtitle><description>The paper is a review of the opportunities and challenges of cryogenic power devices of electric aircraft, and the ongoing research and development efforts of the government agencies and the industry. Liquid Hydrogen (LH2) and Liquefied Natural Gas (LNG) are compared to support high temperature superconducting (HTS) and normal metal devices, respectively. The power devices were assumed to operate at the normal boiling point of the fuel used. The efficiencies of the electrical devices are estimated based on state-of-the-art technology. The mass flow rates and total fuel requirements for both the cryogenic fuels required to maintain the operating temperatures of the devices were simulated using thermal network models. A twin-aisle, 300 passenger aircraft with a 5.5 h flight duration was used for the models. The results show that the required masses of LH2 and LNG are 744 kg and 13,638 kg, respectively for the cooling requirement. The corresponding volumes of LH2 and LNG required are 9,760 and 30,300 L, respectively. In both cases, the estimated mass of the fuel needed for the aircraft is more than what is needed to maintain the cryogenic environment of the power devices. It was concluded that an electric aircraft with LNG cooled normal metal devices is feasible. However, an aircraft with HTS devices and cooled with LH2 is more attractive if the ongoing R&D efforts on HTS devices and LH2 infrastructure are successful. The emission reductions would be substantially higher with LH2, particularly when H2 is produced using renewable energy sources.</description><subject>Aircraft</subject><subject>Boiling points</subject><subject>Electronic devices</subject><subject>Emission standards</subject><subject>Emissions control</subject><subject>Fly by wire control</subject><subject>High temperature</subject><subject>Liquefied natural gas</subject><subject>Liquid hydrogen</subject><subject>Mass flow rate</subject><subject>Operating temperature</subject><subject>Passenger aircraft</subject><subject>R&D</subject><subject>Renewable energy sources</subject><subject>Research & development</subject><subject>Thermal simulation</subject><issn>1757-8981</issn><issn>1757-899X</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2022</creationdate><recordtype>article</recordtype><sourceid>O3W</sourceid><sourceid>ABUWG</sourceid><sourceid>AFKRA</sourceid><sourceid>AZQEC</sourceid><sourceid>BENPR</sourceid><sourceid>CCPQU</sourceid><sourceid>DWQXO</sourceid><recordid>eNqFkEtLxDAQgIMouK7-BgOePNRm0vSR47LUXWHVgwreQpImkqVua9Ie9t_bWlkRBE8zzHzz4EPoEsgNkKKIIU_zqOD8NQbKIIaYACVJeoRmh87xIS_gFJ2FsCUkyxkjM1SWtdGddxovnNde2g7f9qY2FVZ7vHEfvavwel_55s3ssNxVXzVj3QA8yK73ssYrGc7RiZV1MBffcY5ebsvn5TraPK7ulotNpBOANALNpOWQc04VLRShkvNEG2IVS7nSWlrCLck44ZlJSUaVBAqKWWuVlJKxZI6upr2tb4Y3Qie2Te93w0lBs4IymqcpHah8orRvQvDGita7d-n3AogYnYnRhhjNiNGZADE5Gyavp0nXtD-r75_K35xoKzuwyR_sfxc-AX7jesU</recordid><startdate>20220501</startdate><enddate>20220501</enddate><creator>Telikapalli, Srikar</creator><creator>Swain, Roberto M.</creator><creator>Cheetham, Peter</creator><creator>Kim, Chul H.</creator><creator>Pamidi, Sastry V.</creator><general>IOP Publishing</general><scope>O3W</scope><scope>TSCCA</scope><scope>AAYXX</scope><scope>CITATION</scope><scope>8FE</scope><scope>8FG</scope><scope>ABJCF</scope><scope>ABUWG</scope><scope>AFKRA</scope><scope>AZQEC</scope><scope>BENPR</scope><scope>BGLVJ</scope><scope>CCPQU</scope><scope>D1I</scope><scope>DWQXO</scope><scope>HCIFZ</scope><scope>KB.</scope><scope>L6V</scope><scope>M7S</scope><scope>PDBOC</scope><scope>PIMPY</scope><scope>PQEST</scope><scope>PQQKQ</scope><scope>PQUKI</scope><scope>PRINS</scope><scope>PTHSS</scope></search><sort><creationdate>20220501</creationdate><title>Electric Aircraft Fueled by Liquid Hydrogen and Liquefied Natural Gas</title><author>Telikapalli, Srikar ; Swain, Roberto M. ; Cheetham, Peter ; Kim, Chul H. ; Pamidi, Sastry V.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c3115-1c4af917992b28b02a993ce0fb459bccaf09f069096e5062ba121b4fffbaaa443</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2022</creationdate><topic>Aircraft</topic><topic>Boiling points</topic><topic>Electronic devices</topic><topic>Emission standards</topic><topic>Emissions control</topic><topic>Fly by wire control</topic><topic>High temperature</topic><topic>Liquefied natural gas</topic><topic>Liquid hydrogen</topic><topic>Mass flow rate</topic><topic>Operating temperature</topic><topic>Passenger aircraft</topic><topic>R&D</topic><topic>Renewable energy sources</topic><topic>Research & development</topic><topic>Thermal simulation</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Telikapalli, Srikar</creatorcontrib><creatorcontrib>Swain, Roberto M.</creatorcontrib><creatorcontrib>Cheetham, Peter</creatorcontrib><creatorcontrib>Kim, Chul H.</creatorcontrib><creatorcontrib>Pamidi, Sastry V.</creatorcontrib><collection>Institute of Physics Open Access Journal Titles</collection><collection>IOPscience (Open Access)</collection><collection>CrossRef</collection><collection>ProQuest SciTech Collection</collection><collection>ProQuest Technology Collection</collection><collection>Materials Science & Engineering Collection</collection><collection>ProQuest Central (Alumni Edition)</collection><collection>ProQuest Central UK/Ireland</collection><collection>ProQuest Central Essentials</collection><collection>ProQuest Central</collection><collection>Technology Collection</collection><collection>ProQuest One Community College</collection><collection>ProQuest Materials Science Collection</collection><collection>ProQuest Central Korea</collection><collection>SciTech Premium Collection</collection><collection>Materials Science Database</collection><collection>ProQuest Engineering Collection</collection><collection>Engineering Database</collection><collection>Materials Science Collection</collection><collection>Access via ProQuest (Open Access)</collection><collection>ProQuest One Academic Eastern Edition (DO NOT USE)</collection><collection>ProQuest One Academic</collection><collection>ProQuest One Academic UKI Edition</collection><collection>ProQuest Central China</collection><collection>Engineering Collection</collection><jtitle>IOP conference series. Materials Science and Engineering</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Telikapalli, Srikar</au><au>Swain, Roberto M.</au><au>Cheetham, Peter</au><au>Kim, Chul H.</au><au>Pamidi, Sastry V.</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Electric Aircraft Fueled by Liquid Hydrogen and Liquefied Natural Gas</atitle><jtitle>IOP conference series. Materials Science and Engineering</jtitle><addtitle>IOP Conf. Ser.: Mater. Sci. Eng</addtitle><date>2022-05-01</date><risdate>2022</risdate><volume>1241</volume><issue>1</issue><spage>12035</spage><pages>12035-</pages><issn>1757-8981</issn><eissn>1757-899X</eissn><abstract>The paper is a review of the opportunities and challenges of cryogenic power devices of electric aircraft, and the ongoing research and development efforts of the government agencies and the industry. Liquid Hydrogen (LH2) and Liquefied Natural Gas (LNG) are compared to support high temperature superconducting (HTS) and normal metal devices, respectively. The power devices were assumed to operate at the normal boiling point of the fuel used. The efficiencies of the electrical devices are estimated based on state-of-the-art technology. The mass flow rates and total fuel requirements for both the cryogenic fuels required to maintain the operating temperatures of the devices were simulated using thermal network models. A twin-aisle, 300 passenger aircraft with a 5.5 h flight duration was used for the models. The results show that the required masses of LH2 and LNG are 744 kg and 13,638 kg, respectively for the cooling requirement. The corresponding volumes of LH2 and LNG required are 9,760 and 30,300 L, respectively. In both cases, the estimated mass of the fuel needed for the aircraft is more than what is needed to maintain the cryogenic environment of the power devices. It was concluded that an electric aircraft with LNG cooled normal metal devices is feasible. However, an aircraft with HTS devices and cooled with LH2 is more attractive if the ongoing R&D efforts on HTS devices and LH2 infrastructure are successful. The emission reductions would be substantially higher with LH2, particularly when H2 is produced using renewable energy sources.</abstract><cop>Bristol</cop><pub>IOP Publishing</pub><doi>10.1088/1757-899X/1241/1/012035</doi><tpages>14</tpages><oa>free_for_read</oa></addata></record> |
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subjects | Aircraft Boiling points Electronic devices Emission standards Emissions control Fly by wire control High temperature Liquefied natural gas Liquid hydrogen Mass flow rate Operating temperature Passenger aircraft R&D Renewable energy sources Research & development Thermal simulation |
title | Electric Aircraft Fueled by Liquid Hydrogen and Liquefied Natural Gas |
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