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UID:0-1185@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20250901T133000

DTEND;TZID=Asia/Jerusalem:20250901T143000

DTSTAMP:20250828T063103Z

URL:https://aerospace.technion.ac.il/events/seminar-slot-2025-10-29-3/

SUMMARY:Preliminary Structural Design Tool for Flexible Slender Bodies with
  Aeroelastic Constraints
DESCRIPTION:Lecturer:Yaara Karniel \n Faculty:The Stephen B. Klein Faculty 
 of Aerospace Engineering at the Technion \n Institute:Technion – Israel 
 Institute of Technology\n Location:Classroom 165\, ground floor\, Library\
 , Aerospace Eng.\n Zoom: https://technion.zoom.us/j/93549691766\n Abstract
 : Slender aerospace vehicles\, such as missiles and rockets\, are inherent
 ly flexible and therefore deform under aerodynamic loading. With new\, adv
 anced light-weight materials\, modern designs are becoming increasingly mo
 re flexible\, making aeroelastic effects a critical factor in performance 
 and stability. For slender bodies\, aerodynamic forces can bend the vehicl
 e into a characteristic “smiling” shape\, shifting the aerodynamic cen
 ter of pressure forward and reducing static stability. Remarkably\, even m
 odest elastic deformations can render an otherwise stable vehicle unstable
 \, stressing the necessity of accounting for static aeroelastic stability 
 from the earliest design stages.\n\nConventional design methodologies foll
 ow a hierarchical sequence in which the aerodynamic shape is determined fi
 rst\, followed by structural design\, which is directed primarily by stres
 s considerations. Aeroelastic effects\, however\, are often overlooked unt
 il later phases\, when structural parameters are fixed and design revision
 s become costly.\n\nThis study presents a novel preliminary design methodo
 logy that integrates aeroelastic stability analysis at the earliest stage\
 , when only the vehicle geometry is available\, and no detailed structural
  design exists. The proposed framework represents deformations as a combin
 ation of generalized beam mode shapes\, adapted to capture discontinuities
  in material and geometry\, along with rigid-body contributions. Aerodynam
 ic loading is modeled using a potential-flow panel method\, enabling compu
 tation of the elastically deformed shape and its effect on static stabilit
 y. Pareto-front analysis connects structural design parameters to overall 
 weight and stability margin\, providing designers with valuable trade-off 
 insight. A Genetic Algorithm–based optimization then identifies structur
 al configurations that achieve minimum weight while meeting prescribed sta
 bility requirements.\n\n Details: \n 
CATEGORIES:Seminars,סמינרים
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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