{"id":18540,"date":"2024-11-19T13:17:31","date_gmt":"2024-11-19T13:17:31","guid":{"rendered":"https:\/\/aerospacerepository.org\/?p=18540"},"modified":"2024-11-19T13:17:31","modified_gmt":"2024-11-19T13:17:31","slug":"static-aeroelastic-stiffness-optimization-of-a-forward-swept-composite-wing-with-cfd-corrected-aero-loads","status":"publish","type":"post","link":"https:\/\/aerospacerepository.org\/index.php\/2024\/11\/19\/static-aeroelastic-stiffness-optimization-of-a-forward-swept-composite-wing-with-cfd-corrected-aero-loads\/","title":{"rendered":"STATIC AEROELASTIC STIFFNESS OPTIMIZATION OF A FORWARD SWEPT COMPOSITE WING WITH CFD CORRECTED AERO LOADS"},"content":{"rendered":"\n<p><strong>Johannes K.S. Dillinger, Mostafa M. Abdalla, Yasser M. Meddaikar, Thomas Klimmek<\/strong><\/p>\n\n\n\n<p><strong>DOI Number: N\/A<\/strong><\/p>\n\n\n\n<p><strong>Conference number: IFASD-2015-116<\/strong><\/p>\n\n\n\n<p>This paper presents an aero load correction strategy applicable to the static aeroelastic optimization of composite wings. The optimization framework consists of a successive convex subproblem iteration procedure, in which a gradient based optimizer consecutively solves a local approximation problem. Responses are approximated as a linear and\/or reciprocal function of the laminate membrane and bending sti\ufb00ness matrices A and D. Together with the laminate thicknesses h, they constitute the design variables in the optimization process. Internally, the design space is transformed from sti\ufb00ness matrices to lamination parameters, resulting in a continuous and convex optimization problem. Structural responses considered in the sti\ufb00ness optimization are strength, local buckling and mass; aileron e\ufb00ectiveness, divergence, and twist constitute the aeroelastic responses. Steady aeroelastic loads are calculated with a doublet lattice method (DLM) embedded in the applied \ufb01nite element solver, allowing for the generation of response sensitivities that incorporate the e\ufb00ects of displacement-dependent, aeroelastic loads. To incorporate \ufb02ow phenomena that cannot be reproduced with DLM, a higher order aerodynamic method is considered. The developed correction methods and their application are presented in this paper. The correction is twofold, \ufb01rstly aiming at a correction of DLM by means of camber and twist modi\ufb01cations applied directly to the doublet lattice mesh and secondly, by employing the capabilities of a higher order computational \ufb02uid dynamics (CFD) solver, like the DLR-based TAU code. To this end, DLM loads transferred to the structure are recti\ufb01ed by means of the supposedly superior CFD results. The aero load correction method is applied in the sti\ufb00ness optimization of a forward swept wing. First, a trim application without structural optimization is discussed, to demonstrate the convergence behavior of the correction forces. The results of a wing skin mass minimization with balanced and unbalanced laminates are presented. In particular, the di\ufb00erences between optimizations with and without aero correction are highlighted. Eventually, a stacking sequence optimization based on the continuous optimization results is demonstrated.<\/p>\n\n\n\n<p><a href=\"https:\/\/aerospacerepository.org\/wp-content\/uploads\/2024\/11\/IFASD-2015-116.pdf\">Read the full paper here<\/a><\/p>\n","protected":false},"excerpt":{"rendered":"<p><b>Johannes K.S. Dillinger, Mostafa M. Abdalla, Yasser M. Meddaikar, Thomas Klimmek<\/b><\/p>\n<p>DOI Number: N\/A<\/p>\n<p>Conference number: IFASD-2015-116<\/p>\n","protected":false},"author":2,"featured_media":0,"comment_status":"open","ping_status":"open","sticky":false,"template":"","format":"standard","meta":{"footnotes":""},"categories":[2413,2415],"tags":[2660,2659,1758,2658,2656,2657],"class_list":["post-18540","post","type-post","status-publish","format-standard","hentry","category-1-ifasd-2015","category-aeroelastic-optimisation","tag-aeroelastic-constraints","tag-cfd-correction","tag-composite","tag-doublet-lattice-method","tag-stacking-sequence-optimization","tag-stiness-optimization","category-2413","category-2415","description-off"],"_links":{"self":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/18540","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=18540"}],"version-history":[{"count":1,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/18540\/revisions"}],"predecessor-version":[{"id":18542,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/posts\/18540\/revisions\/18542"}],"wp:attachment":[{"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/media?parent=18540"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/categories?post=18540"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/aerospacerepository.org\/index.php\/wp-json\/wp\/v2\/tags?post=18540"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}