The primary objective of this program was to fully characterize a repair technology for first-generation boron/epoxy composite aircraft structure with particular emphasis on empennage components. The program included the fabrication and quality assurance of plain, stiffened, and honeycomb sandwich panels designed for loading intensities up to 20,000 pounds per inch. These structures were then damaged by ballistic and foreign object impact, lightning strike, and production conditions. The damage was assessed, repaired, and evaluated by both destructive and non-destructive testing. Effective repair procedures were optimized and tested under various loading and environmental conditions to establish the criteria needed for the development of universal repair. The repair techniques were summarized in a repair manual for both field and depot usage. The requisite fabrication and quality control methodology was established for the selected repair and a complete repair kit which requires only an external power source was provided. Finally, a motion picture training film was provided describing the developed repair technology. (Author)
Repair Technology for Boron/Epoxy Composites
1972
289 pages
Report
No indication
English
Repair technology for boron/epoxy composites
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