SWING WING TIP SYSTEM, ASSEMBLY AND METHOD WITH DUAL LOAD PATH STRUCTURE
PROBLEM TO BE SOLVED: To provide a system which realizes both fail-safe load paths and aircraft wingspan increase/decrease to satisfy both size restrictions, e.g., in an airport, and performance enhancement of aircraft.SOLUTION: A swing wing tip system 80 is provided. The swing wing tip system has a...
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| creator | RYAN W KOSKO GREGORY M SANTINI SAKURAI SEIYA |
| description | PROBLEM TO BE SOLVED: To provide a system which realizes both fail-safe load paths and aircraft wingspan increase/decrease to satisfy both size restrictions, e.g., in an airport, and performance enhancement of aircraft.SOLUTION: A swing wing tip system 80 is provided. The swing wing tip system has a swing wing tip assembly 82 with an unfixed wing tip portion 76 movably connected to a fixed wing portion 78 of a wing. The swing wing tip assembly has a dual load path structure configured to transfer load from the unfixed wing tip portion to the fixed wing portion. The dual load path structure has dual wing skin plates, and a rotation joint 84 coupled between the dual wing skin plates and configured to rotationally couple the unfixed wing tip portion to the fixed wing portion. The rotation joint has a dual rotation pin element 88 having a center rotation axis 90 and dual rotation elements 86 configured to rotate about the center rotation axis. The swing wing tip system has an actuator assembly 98 coupled to the rotation joint, and a controller system coupled to the actuator assembly.
【課題】航空機の性能向上と空港等のサイズ制限を両立させるための航空機翼長増減とフェールセーフ荷重経路を共に実現するシステムを提供する。【解決手段】スイング翼端システム８０が提供される。スイング翼端システムは、翼の固定翼部７８に移動可能に接続された非固定翼端部７６を有するスイング翼端アセンブリ８２を有する。スイング翼端アセンブリは、非固定翼端部から固定翼部へ荷重を移す二重荷重経路構造を有する。二重荷重経路構造は、二重翼板プレートと、二重翼板プレート間に連結され、非固定翼端部を固定翼部に回転可能に連結させる回転接合部８４とを有する。回転接合部は、中央回転軸９０を有する二重回転ピン要素８８と、中央回転軸周囲で回転するように構成された二重回転要素８６とを有する。スイング翼端システムは、回転接合部に連結されたアクチュエータアセンブリ９８と、それに連結されたコントローラシステムとを有する。【選択図】図４Ａ |
| format | Patent |
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【課題】航空機の性能向上と空港等のサイズ制限を両立させるための航空機翼長増減とフェールセーフ荷重経路を共に実現するシステムを提供する。【解決手段】スイング翼端システム８０が提供される。スイング翼端システムは、翼の固定翼部７８に移動可能に接続された非固定翼端部７６を有するスイング翼端アセンブリ８２を有する。スイング翼端アセンブリは、非固定翼端部から固定翼部へ荷重を移す二重荷重経路構造を有する。二重荷重経路構造は、二重翼板プレートと、二重翼板プレート間に連結され、非固定翼端部を固定翼部に回転可能に連結させる回転接合部８４とを有する。回転接合部は、中央回転軸９０を有する二重回転ピン要素８８と、中央回転軸周囲で回転するように構成された二重回転要素８６とを有する。スイング翼端システムは、回転接合部に連結されたアクチュエータアセンブリ９８と、それに連結されたコントローラシステムとを有する。【選択図】図４Ａ</description><language>eng ; jpn</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; COSMONAUTICS ; HELICOPTERS ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>2015</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=20150420&DB=EPODOC&CC=JP&NR=2015074444A$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,308,780,885,25563,76318</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20150420&DB=EPODOC&CC=JP&NR=2015074444A$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>RYAN W KOSKO</creatorcontrib><creatorcontrib>GREGORY M SANTINI</creatorcontrib><creatorcontrib>SAKURAI SEIYA</creatorcontrib><title>SWING WING TIP SYSTEM, ASSEMBLY AND METHOD WITH DUAL LOAD PATH STRUCTURE</title><description>PROBLEM TO BE SOLVED: To provide a system which realizes both fail-safe load paths and aircraft wingspan increase/decrease to satisfy both size restrictions, e.g., in an airport, and performance enhancement of aircraft.SOLUTION: A swing wing tip system 80 is provided. The swing wing tip system has a swing wing tip assembly 82 with an unfixed wing tip portion 76 movably connected to a fixed wing portion 78 of a wing. The swing wing tip assembly has a dual load path structure configured to transfer load from the unfixed wing tip portion to the fixed wing portion. The dual load path structure has dual wing skin plates, and a rotation joint 84 coupled between the dual wing skin plates and configured to rotationally couple the unfixed wing tip portion to the fixed wing portion. The rotation joint has a dual rotation pin element 88 having a center rotation axis 90 and dual rotation elements 86 configured to rotate about the center rotation axis. The swing wing tip system has an actuator assembly 98 coupled to the rotation joint, and a controller system coupled to the actuator assembly.
【課題】航空機の性能向上と空港等のサイズ制限を両立させるための航空機翼長増減とフェールセーフ荷重経路を共に実現するシステムを提供する。【解決手段】スイング翼端システム８０が提供される。スイング翼端システムは、翼の固定翼部７８に移動可能に接続された非固定翼端部７６を有するスイング翼端アセンブリ８２を有する。スイング翼端アセンブリは、非固定翼端部から固定翼部へ荷重を移す二重荷重経路構造を有する。二重荷重経路構造は、二重翼板プレートと、二重翼板プレート間に連結され、非固定翼端部を固定翼部に回転可能に連結させる回転接合部８４とを有する。回転接合部は、中央回転軸９０を有する二重回転ピン要素８８と、中央回転軸周囲で回転するように構成された二重回転要素８６とを有する。スイング翼端システムは、回転接合部に連結されたアクチュエータアセンブリ９８と、それに連結されたコントローラシステムとを有する。【選択図】図４Ａ</description><subject>AEROPLANES</subject><subject>AIRCRAFT</subject><subject>AVIATION</subject><subject>COSMONAUTICS</subject><subject>HELICOPTERS</subject><subject>PERFORMING OPERATIONS</subject><subject>TRANSPORTING</subject><fulltext>true</fulltext><rsrctype>patent</rsrctype><creationdate>2015</creationdate><recordtype>patent</recordtype><sourceid>EVB</sourceid><recordid>eNrjZPAIDvf0c1cAEyGeAQrBkcEhrr46Co7Bwa6-Tj6RCo5-Lgq-riEe_i5ARSEeCi6hjj4KPv6OLgoBjkBucEhQqHNIaJArDwNrWmJOcSovlOZmUHJzDXH20E0tyI9PLS5ITE7NSy2J9wowMjA0NTA3AQJHY6IUAQBRVy0w</recordid><startdate>20150420</startdate><enddate>20150420</enddate><creator>RYAN W KOSKO</creator><creator>GREGORY M SANTINI</creator><creator>SAKURAI SEIYA</creator><scope>EVB</scope></search><sort><creationdate>20150420</creationdate><title>SWING WING TIP SYSTEM, ASSEMBLY AND METHOD WITH DUAL LOAD PATH STRUCTURE</title><author>RYAN W KOSKO ; GREGORY M SANTINI ; SAKURAI SEIYA</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-epo_espacenet_JP2015074444A3</frbrgroupid><rsrctype>patents</rsrctype><prefilter>patents</prefilter><language>eng ; jpn</language><creationdate>2015</creationdate><topic>AEROPLANES</topic><topic>AIRCRAFT</topic><topic>AVIATION</topic><topic>COSMONAUTICS</topic><topic>HELICOPTERS</topic><topic>PERFORMING OPERATIONS</topic><topic>TRANSPORTING</topic><toplevel>online_resources</toplevel><creatorcontrib>RYAN W KOSKO</creatorcontrib><creatorcontrib>GREGORY M SANTINI</creatorcontrib><creatorcontrib>SAKURAI SEIYA</creatorcontrib><collection>esp@cenet</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>RYAN W KOSKO</au><au>GREGORY M SANTINI</au><au>SAKURAI SEIYA</au><format>patent</format><genre>patent</genre><ristype>GEN</ristype><title>SWING WING TIP SYSTEM, ASSEMBLY AND METHOD WITH DUAL LOAD PATH STRUCTURE</title><date>2015-04-20</date><risdate>2015</risdate><abstract>PROBLEM TO BE SOLVED: To provide a system which realizes both fail-safe load paths and aircraft wingspan increase/decrease to satisfy both size restrictions, e.g., in an airport, and performance enhancement of aircraft.SOLUTION: A swing wing tip system 80 is provided. The swing wing tip system has a swing wing tip assembly 82 with an unfixed wing tip portion 76 movably connected to a fixed wing portion 78 of a wing. The swing wing tip assembly has a dual load path structure configured to transfer load from the unfixed wing tip portion to the fixed wing portion. The dual load path structure has dual wing skin plates, and a rotation joint 84 coupled between the dual wing skin plates and configured to rotationally couple the unfixed wing tip portion to the fixed wing portion. The rotation joint has a dual rotation pin element 88 having a center rotation axis 90 and dual rotation elements 86 configured to rotate about the center rotation axis. The swing wing tip system has an actuator assembly 98 coupled to the rotation joint, and a controller system coupled to the actuator assembly.
【課題】航空機の性能向上と空港等のサイズ制限を両立させるための航空機翼長増減とフェールセーフ荷重経路を共に実現するシステムを提供する。【解決手段】スイング翼端システム８０が提供される。スイング翼端システムは、翼の固定翼部７８に移動可能に接続された非固定翼端部７６を有するスイング翼端アセンブリ８２を有する。スイング翼端アセンブリは、非固定翼端部から固定翼部へ荷重を移す二重荷重経路構造を有する。二重荷重経路構造は、二重翼板プレートと、二重翼板プレート間に連結され、非固定翼端部を固定翼部に回転可能に連結させる回転接合部８４とを有する。回転接合部は、中央回転軸９０を有する二重回転ピン要素８８と、中央回転軸周囲で回転するように構成された二重回転要素８６とを有する。スイング翼端システムは、回転接合部に連結されたアクチュエータアセンブリ９８と、それに連結されたコントローラシステムとを有する。【選択図】図４Ａ</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AEROPLANES AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS TRANSPORTING |
| title | SWING WING TIP SYSTEM, ASSEMBLY AND METHOD WITH DUAL LOAD PATH STRUCTURE |
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