Experimental Observations for Determining the Maximum Torque Values to Apply to Composite Components Mechanically Joined With Fasteners (MSFC Center D

By: Administration (Nasa), National Aeronaut

Aerospace structures utilize innovative, lightweight composite materials for exploration activities. These structural components, due to various reasons including size limitations, manufacturing facilities, contractual obligations, or particular design requirements, will have to be joined. The common methodologies for joining composite components are the adhesively bonded and mechanically fastened joints and, in certain instances, both methods are simultaneously incorporated into the design. Guidelines and recommendations exist for engineers to develop design criteria and analyze and test composites. However, there are no guidelines or recommendations based on analysis or test data to specify a torque or torque range to apply to metallic mechanical fasteners used to join composite components. Utilizing the torque tension machine at NASA s Marshall Space Flight Center, an initial series of tests were conducted to determine the maximum torque that could be applied to a composite specimen. Acoustic emissions were used to nondestructively assess the specimens during the tests and thermographic imaging after the tests. Thomas, F. P. Marshall Space Flight Center NASA/TM-2006-214323, M-1157 COMPOSITE MATERIALS; FASTENERS; THERMOGRAPHY; ACOUSTIC EMISSION; DESIGN ANALYSIS; AIRCRAFT STRUCTURES; BONDED JOINTS; TORQUE; ADHESIVE BONDING; NONDESTRUCTIVE TESTS; ENGINEERS; IMAGING TECHNIQUES; STRUCTURAL DESIGN

• Format: Paperback
• Language: English
• ISBN: B08F65S6ST
• ISBN13: 9798672742632
• Release Date: January 1
• Publisher: Independently Published
• Length: 40 Pages
• Weight: 0.26 lbs.
• Dimensions: 0.1" x 8.5" x 11.0"