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Buckling Testing and Analysis of Honeycomb Sandwich Panel Arc Segments of a Full-Scale Fairing Barrel Part 1: 8-Ply In-Autoclave Facesheets. Part 1; 8-Ply In-Autoclave Facesheets
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Author and Affiliation:
Myers, David E.(NASA Glenn Research Center, Cleveland, OH, United States);
Pineda, Evan J.(NASA Glenn Research Center, Cleveland, OH, United States);
Zalewski, Bart F.(ZIN Technologies, Inc., Middleburg Heights, OH, United States);
Kosareo, Daniel N.(Vantage Partners, LLC, Brook Park, OH, United States);
Kellas, Sotiris(NASA Langley Research Center, Hampton, VA, United States)
Abstract: Four honeycomb sandwich panels, representing 1/16th arc segments of a 10-m diameter barrel section of the heavy lift launch vehicle, were manufactured under the NASA Composites for Exploration program and the NASA Space Launch Systems program. Two configurations were chosen for the panels: 6-ply facesheets with 1.125 in. honeycomb core and 8-ply facesheets with 1.000 in. honeycomb core. Additionally, two separate carbon fiber/epoxy material systems were chosen for the facesheets: inautoclave IM7/977-3 and out-of-autoclave T40-800b/5320-1. Smaller 3.00- by 5.00-ft panels were cut from the 1/16th barrel sections. These panels were tested under compressive loading at the NASA Langley Research Center. Furthermore, linear eigenvalue and geometrically nonlinear finite element analysis was performed to predict the compressive response of the 3.00- by 5.00-ft panels. This manuscript summarizes the experimental and analytical modeling efforts pertaining to the panel composed of 8-ply, IM7/977-3 facesheets (referred to Panel A). To improve the robustness of the geometrically nonlinear finite element model, measured surface imperfections were included in the geometry of the model. Both the linear and nonlinear models yield good qualitative and quantitative predictions. Additionally, it was predicted correctly that the panel would fail in buckling prior to failing in strength. Furthermore, several imperfection studies were performed to investigate the influence of geometric imperfections, fiber misalignments, and three-dimensional (3 D) effects on the compressive response of the panel.
Publication Date: Apr 01, 2013
Document ID:
20130013468
(Acquired May 20, 2013)
Subject Category: STRUCTURAL MECHANICS
Report/Patent Number: NASA/TM-2013-217822/PT1, E-18570
Document Type: Technical Report
Contract/Grant/Task Num: WBS 432938.11.01.03.02.01.06
Financial Sponsor: NASA Glenn Research Center; Cleveland, OH, United States
Organization Source: NASA Glenn Research Center; Cleveland, OH, United States
Description: 46p; In English; Original contains color and black and white illustrations
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright; Distribution as joint owner in the copyright
NASA Terms: BUCKLING; CARBON FIBER REINFORCED PLASTICS; COMPRESSIVE STRENGTH; COMPUTATIONAL MECHANICS; EPOXY MATRIX COMPOSITES; FINITE ELEMENT METHOD; HEAVY LIFT LAUNCH VEHICLES; HONEYCOMB STRUCTURES; LOAD CARRYING CAPACITY; PANELS; SANDWICH STRUCTURES
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