Feasibility Of Joining Advanced Composite Flight Vehicle Structures

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Report Number: AFML TR 68-391
Author(s): Kutscha, D., Hofer, K. E., Jr
Corporate Author(s): IIT Research Institute, Mechanics of Materials Research Division
Laboratory: Air Force Materials Laboratory
Date of Publication: 1969-01
Pages: 501
Contract: AF 33(615)-3962
DoD Project: 7381
DoD Task: 738106
Identifier: AD0690616

A combined analytical-experimental study was carried out to establish the feasibility of developing rational design techniques for bonded and mechanical joints in advanced composite structures. Available stress analyses were compared for their predictions of maximum stresses in joints and these results were compared to experimental data. The static strengths were measured for three adhesives bonded to fiberglass, steel, and titanium, and the fatigue strengths were measured for the optimum joint designs. The load distribution and joint strength was studied for fiberglass bolted joints. Recommendations were made for specific additional work required both in joints analysis and characterization of materials.

Provenance: Lockheed Martin Missiles & Fire Control

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