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UID:0-503@aerospace.technion.ac.il

DTSTART;TZID=Asia/Jerusalem:20151230T163000

DTEND;TZID=Asia/Jerusalem:20151230T173000

DTSTAMP:20230603T192352Z

URL:https://aerospace.technion.ac.il/events/investigation-of-the-behavior-
 of-damaged-aluminum-panel-under-shear-loads-reinforced-by-composite-patche
 s-a-new-engineering-approach/

SUMMARY:Investigation of the Behavior of Damaged Aluminum Panel Under Shear
  Loads\, Reinforced by Composite Patches – A New Engineering Approach
DESCRIPTION:Lecturer:Yuri Simanovskii\n Faculty:Department of Aerospace Eng
 ineering\n Institute:Technion – Israel Institute of Technology\n Locatio
 n:Classroom 165\, ground floor\, Library\, Aerospace Eng.\n Zoom: \n Abstr
 act: \n Details: \n Aging metallic aircraft\, manufactured in the early 70
 's\, are still being operated around the world\, and are subjected to new 
 types of damage\, appearing in new locations on the aircraft. In past year
 s\, the use of composites has increased for Aluminum aircraft components. 
 Various studies substantiated these repairs to be effective from durabilit
 y point of view and evaluated the effect of plies application sequence\, o
 rientation sequence\, effect of stress intensity factor and more. However\
 , all those studies focused on simple tensile loading.\nForward and center
  sections of a combat aircraft fuselage contain a skin\, which plays a maj
 or role in load transferring\, usually due to torsion originated by fusela
 ge bending. The present research aims at studying the effect of the above 
 mentioned parameters on composite repair patch for a panel\, subjected to 
 shear loads. The study is based on a new approach of finite element modeli
 ng\, consisting of 2D and 3D merged elements. Correspondingly\, the model 
 is parametrically analyzed for strength and buckling\, as a function of pa
 tch size\, overlaps\, and sequences of plies. The analysis is then substan
 tiated by a dedicated set of experiments on typical representative element
 s. Based on the test results\, the accuracy of the finite element model wa
 s evaluated and thus validating the method of patch repair.
CATEGORIES:Seminars
LOCATION:Classroom 165\, ground floor\, Library\, Aerospace Eng.

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DTSTART:20151025T010000

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