Design and Evaluation of Composite Fuselage Panels Subjected to Combined Loading Conditions
Author:
Affiliation:
1. NASA Langley Research Center, Hampton, Virginia 23681-001
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.18994
Reference6 articles.
1. Fuselage response simulation of stiffened panels using a pressure-box test machine
2. D-box fixture for testing stiffened panels in compression and pressure
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