Aerospace vehicle flow body systems and associated methods
Flow body systems and associated methods, including aerospace vehicle control surface systems are disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes a first flow body that can be coupleable to an aerospace vehicle. The system can further includ...
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| creator | MARTIN F STEPHENSON SELYA SAKURAI JAMES E FINNILA |
| description | Flow body systems and associated methods, including aerospace vehicle control surface systems are disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes a first flow body that can be coupleable to an aerospace vehicle. The system can further included a second flow body that includes a chord line and can be rotatably coupled to the first flow body at a hinge point positioned away from the chord line. The hinge point can have a hinge axis. The hinge line can extend through the hinge point, but being nonparallel with the hinge axis. The system can still further include at least one self-aligning mechanism coupled between the first flow body and the second flow body. The at least one self-aligning mechanism can be positioned to allow the second flow body to rotate about the hinge line and the hinge axis. |
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One aspect of the invention is directed toward an aerospace vehicle system that includes a first flow body that can be coupleable to an aerospace vehicle. The system can further included a second flow body that includes a chord line and can be rotatably coupled to the first flow body at a hinge point positioned away from the chord line. The hinge point can have a hinge axis. The hinge line can extend through the hinge point, but being nonparallel with the hinge axis. The system can still further include at least one self-aligning mechanism coupled between the first flow body and the second flow body. The at least one self-aligning mechanism can be positioned to allow the second flow body to rotate about the hinge line and the hinge axis.</description><language>eng</language><subject>AEROPLANES ; AIRCRAFT ; AVIATION ; COSMONAUTICS ; HELICOPTERS ; PERFORMING OPERATIONS ; TRANSPORTING</subject><creationdate>2007</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=20071003&DB=EPODOC&CC=GB&NR=2428996B$$EHTML$$P50$$Gepo$$Hfree_for_read</linktohtml><link.rule.ids>230,309,781,886,25569,76552</link.rule.ids><linktorsrc>$$Uhttps://worldwide.espacenet.com/publicationDetails/biblio?FT=D&date=20071003&DB=EPODOC&CC=GB&NR=2428996B$$EView_record_in_European_Patent_Office$$FView_record_in_$$GEuropean_Patent_Office$$Hfree_for_read</linktorsrc></links><search><creatorcontrib>MARTIN F STEPHENSON</creatorcontrib><creatorcontrib>SELYA SAKURAI</creatorcontrib><creatorcontrib>JAMES E FINNILA</creatorcontrib><title>Aerospace vehicle flow body systems and associated methods</title><description>Flow body systems and associated methods, including aerospace vehicle control surface systems are disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes a first flow body that can be coupleable to an aerospace vehicle. The system can further included a second flow body that includes a chord line and can be rotatably coupled to the first flow body at a hinge point positioned away from the chord line. The hinge point can have a hinge axis. The hinge line can extend through the hinge point, but being nonparallel with the hinge axis. The system can still further include at least one self-aligning mechanism coupled between the first flow body and the second flow body. 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One aspect of the invention is directed toward an aerospace vehicle system that includes a first flow body that can be coupleable to an aerospace vehicle. The system can further included a second flow body that includes a chord line and can be rotatably coupled to the first flow body at a hinge point positioned away from the chord line. The hinge point can have a hinge axis. The hinge line can extend through the hinge point, but being nonparallel with the hinge axis. The system can still further include at least one self-aligning mechanism coupled between the first flow body and the second flow body. The at least one self-aligning mechanism can be positioned to allow the second flow body to rotate about the hinge line and the hinge axis.</abstract><oa>free_for_read</oa></addata></record> |
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| subjects | AEROPLANES AIRCRAFT AVIATION COSMONAUTICS HELICOPTERS PERFORMING OPERATIONS TRANSPORTING |
| title | Aerospace vehicle flow body systems and associated methods |
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