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)


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    Title :

    Repair Technology for Boron/Epoxy Composites


    Contributors:
    G. Lubin (author)

    Publication date :

    1972


    Size :

    289 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Repair technology for boron/epoxy composites

    Lubin, G. | Tema Archive | 1972





    Effects of fabrication defects on boron/epoxy composites

    Thies, D. / Sanders, L. / Neff, R. | Tema Archive | 1974