HYBRID ELECTRIC AIRCRAFT
An aircraft propulsion system. The system comprises an internal combustion engine configured to drive a first propulsor and an electric generator. The system further comprises an electric motor or motors each configured to be powered by electric power provided by the generator, and configured to dri...
Gespeichert in:
| Hauptverfasser: | , |
|---|---|
| Format: | Patent |
| Sprache: | eng |
| Schlagworte: | |
| Online-Zugang: | Volltext bestellen |
| Tags: |
Tag hinzufügen
Keine Tags, Fügen Sie den ersten Tag hinzu!
|
| container_end_page | |
|---|---|
| container_issue | |
| container_start_page | |
| container_title | |
| container_volume | |
| creator | CHUNG, Jae-Hoon RAFFAELLI, Lorenzo |
| description | An aircraft propulsion system. The system comprises an internal combustion engine configured to drive a first propulsor and an electric generator. The system further comprises an electric motor or motors each configured to be powered by electric power provided by the generator, and configured to drive the first propulsor and/or a second propulsor. An electrical energy storage unit is provided, and is configured to store electrical energy supplied from the generator and supply electrical power to the electric motor. At maximum take-off power, the electric motor provides between 5% and 20% of total maximum aircraft propulsive take-off power. |
| format | Patent |
| fullrecord | <record><control><sourceid>epo_EVB</sourceid><recordid>TN_cdi_epo_espacenet_US2020017225A1</recordid><sourceformat>XML</sourceformat><sourcesystem>PC</sourcesystem><sourcerecordid>US2020017225A1</sourcerecordid><originalsourceid>FETCH-epo_espacenet_US2020017225A13</originalsourceid><addsrcrecordid>eNrjZJDwiHQK8nRRcPVxdQ4J8nRWcPQMcg5ydAvhYWBNS8wpTuWF0twMym6uIc4euqkF-fGpxQWJyal5qSXxocFGBkYGBobmRkamjobGxKkCAGawIHY</addsrcrecordid><sourcetype>Open Access Repository</sourcetype><iscdi>true</iscdi><recordtype>patent</recordtype></control><display><type>patent</type><title>HYBRID ELECTRIC AIRCRAFT</title><source>esp@cenet</source><creator>CHUNG, Jae-Hoon ; RAFFAELLI, Lorenzo</creator><creatorcontrib>CHUNG, Jae-Hoon ; RAFFAELLI, Lorenzo</creatorcontrib><description>An aircraft propulsion system. The system comprises an internal combustion engine configured to drive a first propulsor and an electric generator. The system further comprises an electric motor or motors each configured to be powered by electric power provided by the generator, and configured to drive the first propulsor and/or a second propulsor. An electrical energy storage unit is provided, and is configured to store electrical energy supplied from the generator and supply electrical power to the electric motor. At maximum take-off power, the electric motor provides between 5% and 20% of total maximum aircraft propulsive take-off power.</description><language>eng</language><subject>AIRCRAFT ; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT ; AVIATION ; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER ; COSMONAUTICS ; DYNAMO-ELECTRIC MACHINES ; ELECTRICITY ; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT ; FLYING SUITS ; GENERATION ; PARACHUTES ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>2020</creationdate><oa>free_for_read</oa><woscitedreferencessubscribed>false</woscitedreferencessubscribed></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><linktohtml>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20200116&DB=EPODOC&CC=US&NR=2020017225A1$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20200116&DB=EPODOC&CC=US&NR=2020017225A1$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>CHUNG, Jae-Hoon</creatorcontrib><creatorcontrib>RAFFAELLI, Lorenzo</creatorcontrib><title>HYBRID ELECTRIC AIRCRAFT</title><description>An aircraft propulsion system. The system comprises an internal combustion engine configured to drive a first propulsor and an electric generator. The system further comprises an electric motor or motors each configured to be powered by electric power provided by the generator, and configured to drive the first propulsor and/or a second propulsor. An electrical energy storage unit is provided, and is configured to store electrical energy supplied from the generator and supply electrical power to the electric motor. At maximum take-off power, the electric motor provides between 5% and 20% of total maximum aircraft propulsive take-off power.</description><subject>AIRCRAFT</subject><subject>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</subject><subject>AVIATION</subject><subject>CONVERSION OR DISTRIBUTION OF ELECTRIC POWER</subject><subject>COSMONAUTICS</subject><subject>DYNAMO-ELECTRIC MACHINES</subject><subject>ELECTRICITY</subject><subject>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</subject><subject>FLYING SUITS</subject><subject>GENERATION</subject><subject>PARACHUTES</subject><subject>PERFORMING OPERATIONS</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2020</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZJDwiHQK8nRRcPVxdQ4J8nRWcPQMcg5ydAvhYWBNS8wpTuWF0twMym6uIc4euqkF-fGpxQWJyal5qSXxocFGBkYGBobmRkamjobGxKkCAGawIHY</recordid><startdate>20200116</startdate><enddate>20200116</enddate><creator>CHUNG, Jae-Hoon</creator><creator>RAFFAELLI, Lorenzo</creator><scope>EVB</scope></search><sort><creationdate>20200116</creationdate><title>HYBRID ELECTRIC AIRCRAFT</title><author>CHUNG, Jae-Hoon ; RAFFAELLI, Lorenzo</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_US2020017225A13</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng</language><creationdate>2020</creationdate><topic>AIRCRAFT</topic><topic>ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT</topic><topic>AVIATION</topic><topic>CONVERSION OR DISTRIBUTION OF ELECTRIC POWER</topic><topic>COSMONAUTICS</topic><topic>DYNAMO-ELECTRIC MACHINES</topic><topic>ELECTRICITY</topic><topic>EQUIPMENT FOR FITTING IN OR TO AIRCRAFT</topic><topic>FLYING SUITS</topic><topic>GENERATION</topic><topic>PARACHUTES</topic><topic>PERFORMING OPERATIONS</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>CHUNG, Jae-Hoon</creatorcontrib><creatorcontrib>RAFFAELLI, Lorenzo</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>CHUNG, Jae-Hoon</au><au>RAFFAELLI, Lorenzo</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>HYBRID ELECTRIC AIRCRAFT</title><date>2020-01-16</date><risdate>2020</risdate><abstract>An aircraft propulsion system. The system comprises an internal combustion engine configured to drive a first propulsor and an electric generator. The system further comprises an electric motor or motors each configured to be powered by electric power provided by the generator, and configured to drive the first propulsor and/or a second propulsor. An electrical energy storage unit is provided, and is configured to store electrical energy supplied from the generator and supply electrical power to the electric motor. At maximum take-off power, the electric motor provides between 5% and 20% of total maximum aircraft propulsive take-off power.</abstract><oa>free_for_read</oa></addata></record> |
| fulltext | fulltext_linktorsrc |
| identifier | |
| ispartof | |
| issn | |
| language | eng |
| recordid | cdi_epo_espacenet_US2020017225A1 |
| source | esp@cenet |
| subjects | AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION CONVERSION OR DISTRIBUTION OF ELECTRIC POWER COSMONAUTICS DYNAMO-ELECTRIC MACHINES ELECTRICITY EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GENERATION PARACHUTES PERFORMING OPERATIONS TRANSPORTING |
| title | HYBRID ELECTRIC AIRCRAFT |
| url | https://sfx.bib-bvb.de/sfx_tum?ctx_ver=Z39.88-2004&ctx_enc=info:ofi/enc:UTF-8&ctx_tim=2024-12-27T06%3A48%3A50IST&url_ver=Z39.88-2004&url_ctx_fmt=infofi/fmt:kev:mtx:ctx&rfr_id=info:sid/primo.exlibrisgroup.com:primo3-Article-epo_EVB&rft_val_fmt=info:ofi/fmt:kev:mtx:patent&rft.genre=patent&rft.au=CHUNG,%20Jae-Hoon&rft.date=2020-01-16&rft_id=info:doi/&rft_dat=%3Cepo_EVB%3EUS2020017225A1%3C/epo_EVB%3E%3Curl%3E%3C/url%3E&disable_directlink=true&sfx.directlink=off&sfx.report_link=0&rft_id=info:oai/&rft_id=info:pmid/&rfr_iscdi=true |