An aircraft electrical actuator arrangement
An aircraft (40) electrical actuator arrangement comprises a plurality of electrical actuators (11) coupled to an electrical power distribution network, the electrical power distribution network has a master power converter (1) to convert electrical power from the electrical power distribution netwo...
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| creator | Malkin, Peter Trainer, David Reginald |
| description | An aircraft (40) electrical actuator arrangement comprises a plurality of electrical actuators (11) coupled to an electrical power distribution network, the electrical power distribution network has a master power converter (1) to convert electrical power from the electrical power distribution network for supply to each electrical actuator (11). The electrical actuators (11) comprise an environmental control system actuator (68), an aileron actuator (78), a flap actuator (70), a slat actuator (72), a landing gear actuator (76), a thrust reverser actuator (74), a brake actuator (80) and a taxiing actuator (82). A controller is coupled to the master power converter (1). The controller is arranged to allow the supply of electrical power from the master power converter (1) to the environmental control system actuator (68) during a first mode of operation of the aircraft (40). The controller is arranged to allow the supply of electrical power from the master power converter (1) to at least one of the aileron, the flap, the slat, the landing gear, the thrust reverser, the brake actuator or the taxiing actuator (78, 70,72, 76, 74, 80, 82) during a second mode of operation of the aircraft (40). |
| format | Patent |
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The electrical actuators (11) comprise an environmental control system actuator (68), an aileron actuator (78), a flap actuator (70), a slat actuator (72), a landing gear actuator (76), a thrust reverser actuator (74), a brake actuator (80) and a taxiing actuator (82). A controller is coupled to the master power converter (1). The controller is arranged to allow the supply of electrical power from the master power converter (1) to the environmental control system actuator (68) during a first mode of operation of the aircraft (40). The controller is arranged to allow the supply of electrical power from the master power converter (1) to at least one of the aileron, the flap, the slat, the landing gear, the thrust reverser, the brake actuator or the taxiing actuator (78, 70,72, 76, 74, 80, 82) during a second mode of operation of the aircraft (40).</description><language>eng ; fre ; ger</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER ; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER ; COSMONAUTICS ; ELECTRICITY ; GENERATION ; HELICOPTERS ; PERFORMING OPERATIONS ; SYSTEMS FOR STORING ELECTRIC ENERGY ; TRANSPORTING</subject><creationdate>2017</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=20171101&DB=EPODOC&CC=EP&NR=2236413A3$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25564,76547</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20171101&DB=EPODOC&CC=EP&NR=2236413A3$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>Malkin, Peter</creatorcontrib><creatorcontrib>Trainer, David Reginald</creatorcontrib><title>An aircraft electrical actuator arrangement</title><description>An aircraft (40) electrical actuator arrangement comprises a plurality of electrical actuators (11) coupled to an electrical power distribution network, the electrical power distribution network has a master power converter (1) to convert electrical power from the electrical power distribution network for supply to each electrical actuator (11). The electrical actuators (11) comprise an environmental control system actuator (68), an aileron actuator (78), a flap actuator (70), a slat actuator (72), a landing gear actuator (76), a thrust reverser actuator (74), a brake actuator (80) and a taxiing actuator (82). A controller is coupled to the master power converter (1). The controller is arranged to allow the supply of electrical power from the master power converter (1) to the environmental control system actuator (68) during a first mode of operation of the aircraft (40). The controller is arranged to allow the supply of electrical power from the master power converter (1) to at least one of the aileron, the flap, the slat, the landing gear, the thrust reverser, the brake actuator or the taxiing actuator (78, 70,72, 76, 74, 80, 82) during a second mode of operation of the aircraft (40).</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER</subject><subject>CONVERSION OR DISTRIBUTION OF ELECTRIC POWER</subject><subject>COSMONAUTICS</subject><subject>ELECTRICITY</subject><subject>GENERATION</subject><subject>HELICOPTERS</subject><subject>PERFORMING OPERATIONS</subject><subject>SYSTEMS FOR STORING ELECTRIC ENERGY</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2017</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZNB2zFNIzCxKLkpMK1FIzUlNLinKTE7MUUhMLilNLMkvUkgsKkrMS0_NTc0r4WFgTUvMKU7lhdLcDApuriHOHrqpBfnxqcUFicmpeakl8a4BRkbGZiaGxo7GxkQoAQAgFyky</recordid><startdate>20171101</startdate><enddate>20171101</enddate><creator>Malkin, Peter</creator><creator>Trainer, David Reginald</creator><scope>EVB</scope></search><sort><creationdate>20171101</creationdate><title>An aircraft electrical actuator arrangement</title><author>Malkin, Peter ; Trainer, David Reginald</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_EP2236413A33</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; fre ; ger</language><creationdate>2017</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER</topic><topic>CONVERSION OR DISTRIBUTION OF ELECTRIC POWER</topic><topic>COSMONAUTICS</topic><topic>ELECTRICITY</topic><topic>GENERATION</topic><topic>HELICOPTERS</topic><topic>PERFORMING OPERATIONS</topic><topic>SYSTEMS FOR STORING ELECTRIC ENERGY</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>Malkin, Peter</creatorcontrib><creatorcontrib>Trainer, David Reginald</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Malkin, Peter</au><au>Trainer, David Reginald</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>An aircraft electrical actuator arrangement</title><date>2017-11-01</date><risdate>2017</risdate><abstract>An aircraft (40) electrical actuator arrangement comprises a plurality of electrical actuators (11) coupled to an electrical power distribution network, the electrical power distribution network has a master power converter (1) to convert electrical power from the electrical power distribution network for supply to each electrical actuator (11). The electrical actuators (11) comprise an environmental control system actuator (68), an aileron actuator (78), a flap actuator (70), a slat actuator (72), a landing gear actuator (76), a thrust reverser actuator (74), a brake actuator (80) and a taxiing actuator (82). A controller is coupled to the master power converter (1). The controller is arranged to allow the supply of electrical power from the master power converter (1) to the environmental control system actuator (68) during a first mode of operation of the aircraft (40). The controller is arranged to allow the supply of electrical power from the master power converter (1) to at least one of the aileron, the flap, the slat, the landing gear, the thrust reverser, the brake actuator or the taxiing actuator (78, 70,72, 76, 74, 80, 82) during a second mode of operation of the aircraft (40).</abstract><oa>free_for_read</oa></addata></record> |
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| language | eng ; fre ; ger |
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| subjects | AEROPLANES AIRCRAFT AVIATION CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTINGELECTRIC POWER CONVERSION OR DISTRIBUTION OF ELECTRIC POWER COSMONAUTICS ELECTRICITY GENERATION HELICOPTERS PERFORMING OPERATIONS SYSTEMS FOR STORING ELECTRIC ENERGY TRANSPORTING |
| title | An aircraft electrical actuator arrangement |
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