Experimental Results From Stitched Composite Multi-Bay Fuselage Panels Tested Under Uni-Axial Compression

By National Aeronautics and Space Administration

The experimental results from two stitched VARTM composite panels tested under uni-axial compression loading are presented. The curved panels are divided by frames and stringers into five or six bays with a column of three bays along the compressive loading direction. The frames are supported at the ends to resist out-of-plane translation. Back-to-back strain gages are used to record the strain and displacement transducers were used to record the out-of-plane displacements. In addition a full-field measurement technique that utilizes a camera-based-stero-vision system was used to record displacements. The panels were loaded in increments to determine the first bay to buckle. Loading was discontinued at limit load and the panels were removed from the test machine for impact testing. After impacting at 20 ft-lbs to 25 ft-lbs of energy with a spherical indenter, the panels were loaded in compression until failure. Impact testing reduced the axial stiffness 4 percent and less than 1 percent. Postbuckled axial panel stiffness was 52 percent and 70 percent of the pre-buckled stiffness. Baker, Donald J. Langley Research Center NASA/TM-2004-213262, ARL-TR-3233, L-19031 WU 23-719-55-TA COMPOSITE STRUCTURES; COMPRESSION LOADS; CURVED PANELS; FUSELAGES; STRUCTURAL ENGINEERING; AXIAL STRAIN; IMPACT TESTS; STIFFNESS; STRAIN GAGES; STRAIN DISTRIBUTION; DISPLACEMENT; STEREOSCOPIC VISION

• Format: Paperback
• Language: English
• ISBN: B08F6TVZZJ
• ISBN13: 9798673297766
• Release Date: January 1
• Publisher: Independently Published
• Length: 32 Pages
• Weight: 0.22 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"