Configuration and Sizing of a Test Fixture for Panels Under Combined Loads

By: Administration (Nasa), National Aeronaut

Future air and space structures are expected to utilize composite panels that are subjected to combined mechanical loads, such as bi-axial compression/tension, shear and pressure. Therefore, the ability to accurately predict the buckling and strength failures of such panels is important. While computational analysis can provide tremendous insight into panel response, experimental results are necessary to verify predicted performances of these panels to judge the accuracy of computational methods. However, application of combined loads is an extremely difficult task due to the complex test fixtures and set-up required. Presented herein is a comparison of several test set-ups capable of testing panels under combined loads. Configurations compared include a D-box, a segmented cylinder and a single panel set-up. The study primarily focuses on the preliminary sizing of a single panel test configuration capable of testing flat panels under combined in-plane mechanical loads. This single panel set-up appears to be best suited to the testing of both strength critical and buckling critical panels. Required actuator loads and strokes are provided for various square, flat panels. Lovejoy, Andrew E. Langley Research Center NASA/CR-2006-214520 COMPOSITE STRUCTURES; PANELS; SPACECRAFT STRUCTURES; BUCKLING; LARGE SPACE STRUCTURES; LOADS (FORCES); ANALYSIS (MATHEMATICS); SEGMENTS; FIXTURES; FAILURE

• Format: Paperback
• Language: English
• ISBN: B08FNV2NDW
• ISBN13: 9798674397939
• Release Date: January 1
• Publisher: Independently Published
• Length: 54 Pages
• Weight: 0.33 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"