Repair Techniques for Celion/LARC-160 Graphite/Polyimide Composite Structures.
Abstract
Operational feasibility of the next generation of reusable space vehicles requires the development of a structural material system that is significantly lighter than the conventional aluminum structure presently employed on the Space Shuttle orbiter. Utilization of graphite filament reinforced polyimide matrix composite material, capable of 600 F service, can achieve this goal. The large stiffness-to-weight and strength-to-weight ratios of graphite composite in combination with the 6OO F structural capability of the polyimide matrix can reduce the total structure/TPS weight by 20-30 percent. In order for the graphite/polyimide (GR/PI) material system to be acceptable for use in advanced space transportation systems, it is necessary that manufactured components be maintained in a safe and economical manner. It is inevitable that with planned usage of OR/PI structural components, damage will occur either in the form of intrinsic flaw growth or mechanical damage. Research and development programs were initiated to develop repair processes and techniques specific to Celion/LARC-l60 OR/PI structure. The study was directed toward highly loaded and lightly loaded compression critical structures for factory type repair. Repair processes included cocure and secondary bonding techniques applied under vacuum plus positive autoclave pressure. Viable repair designs and processes were developed for flat laminates, honeycomb sandwich panels, and hat-stiffened skin-stringer panels. The repair methodology was verified through structural element compression tests at room temperature and 3l5 C (600 F).
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1984
- Accession Number
- ADA305211
Entities
People
- J. S. Jones
- S. R. Graves