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Honeycomb Fastening
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English
Abstract
Attachment of honeycomb sandwich structure has been an important design consideration in the aerospace field since the early 50's when bonded sandwich was first used extensively as covering for the wings and tail of the supersonic B-58. Since then, virtually all military and an increasing number of commercial aircraft and space vehicles utilize honeycomb sandwich as primary structure. This paper illustrates the basic approaches to sandwich panel attachment and the variety of typical solutions. Successful honeycomb fastening design concepts from B-58, B-57F, and F-111 production programs at General Dynamics are illustrated. Sealing of sandwich joints for use as integral fuel tanks and application of specialty fasteners for honeycomb sandwich are discussed. Structural efficiency of “fastened” stepped-down edge concepts versus full-depth panel edges is compared. A full-depth panel edge design with a stud and plug with spliceplate is currently an attractive design for fastening both metallic and composite-faced sandwich.
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Authors
Citation
Walker, C., "Honeycomb Fastening," SAE Technical Paper 700850, 1970, https://doi.org/10.4271/700850.Also In
References
- Hayward G. H. “Bonded Sandwich Structure.” Fort Worth Div. of General Dynamics Corp., Advanced Design Group 1969
- “Design Standards for Integral Fuel Tanks, F-111 Airplanes.” Fort Worth Div. of General Dynamics Corp. Report FZM-12-273B 1966
- Walker C. H. “Improved Sandwich Panel Design and Joint Evaluation Study.” Fort Worth Div. of General Dynamics Corp. Report ERR-FW-541 Jan. 1967
- Walker C. H. “Sandwich Panel Edge and Joint Design Efficiency Improvement Study.” Fort Worth Div. of General Dynamics Corp. Report ERR-FW-968 Dec. 1969
- Third Quarterly Progress Report “Advanced Composite Technology Fuselage Program.” Fort Worth Div. of General Dynamics Corp, Feb. 1970
- Fourth Quarterly Progress Report “Advanced Composite Technology Fuselage Program.” Fort Worth Div. of General Dynamics Corp. May 1970