{"id":18570,"date":"2024-11-19T13:49:54","date_gmt":"2024-11-19T13:49:54","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=18570"},"modified":"2024-11-19T13:49:55","modified_gmt":"2024-11-19T13:49:55","slug":"dynamic-load-alleviation-of-flexible-aircraft-in-wake-vortex-encounters","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/11\/19\/dynamic-load-alleviation-of-flexible-aircraft-in-wake-vortex-encounters\/","title":{"rendered":"DYNAMIC LOAD ALLEVIATION OF FLEXIBLE AIRCRAFT IN WAKE VORTEX ENCOUNTERS"},"content":{"rendered":"\n<p><strong>Henrik Hesse, Rafael Palacios<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: IFASD-2015-133<\/strong><\/p>\n\n\n\n<p>This paper introduces an integrated approach for \ufb02exible-aircraft time-domain aeroelastic simulation and controller design suitable for wake encounter situations. The dynamic response of the vehicle, which may be subject to large wing deformations in trimmed \ufb02ight, is described by a geometrically-nonlinear composite-beam \ufb01nite-element model. The aerodynamics is modeled using the unsteady vortex lattice method and includes the arbitrary time-domain downwash distributions of a wake encounter. A consistent linearization in the structural degrees of freedom enables the use of balancing methods to reduce the problem size while retaining the nonlinear terms in the rigid-body equations. Numerical studies on a very \ufb02exible aircraft demonstrate the reduced-order modeling approach for load calculations in wake vortex encounters over a large parameter space. Closed-loop results \ufb01nally explore the potential of combining feedforward\/feedback H\u221e control and conventional control surfaces for load alleviation.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/11\/IFASD-2015-133.pdf\">Read the full paper here<\/a><\/p>\n\n\n\n<p><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Henrik Hesse, Rafael Palacios<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: IFASD-2015-133<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[2413,2429],"tags":[2674,2675,2373,2676],"class_list":["post-18570","post","type-post","status-publish","format-standard","hentry","category-1-ifasd-2015","category-loads-alleviation","tag-aeroelastic-control","tag-exible-aircraft-dynamics","tag-load-alleviation","tag-wake-encounter","category-2413","category-2429","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/18570","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/users\/2"}],"replies":[{"embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/comments?post=18570"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/18570\/revisions"}],"predecessor-version":[{"id":18572,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/18570\/revisions\/18572"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=18570"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=18570"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=18570"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}