Repair Technology for Boron/Epoxy Composites.
Abstract
This report describes work done to fully characterize a repair technology for first- generation boron/epoxy composite aircraft structure with particular emphasis on empennage components. Also presented are 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 are then damaged by ballistic and foreign object impact, lightning strike, and production conditions. The damage is assessed, repaired, and evaluated by both destructive and non-destructive testing. Effective repair procedures are optimized and tested under various loading and environmental conditions to establish the criteria needed for the development of universal repair. The repair techniques are summarized in a repair manual for both field and depot usage. The requisite fabrication and quality control methodology is established for the selected repair and a complete repair kit which requires only an external power source is provided. Finally a motion picture training film is provided describing the developed repair technology. (Author, modified-PL)
Document Details
- Document Type
- Technical Report
- Publication Date
- Feb 01, 1972
- Accession Number
- AD0776756
Entities
People
- G. Lubin
Organizations
- Grumman