The tooling concepts and manufacturing techniques developed to produce subelements and full-scale bonded test articles for two of the NASA Composites for Advanced Transportation Systems are examined as part of the structural development of graphite/polyimide composite material systems for the Space Shuttle Orbiter and other space transportation systems. The subassembly and the assembly bonding of the test articles were accomplished using self-tooling and low-cost aluminum tooling concepts in order to eliminate the need for complex and expensive tools. Processing procedures and tooling approaches were developed which permit controlled pressure application on specific bonding planes. Two test articles were fabricated using these techniques, an acoustic panel and a quarter segment of the Space Shuttle aft body flap.
Fabrication of bonded graphite/polyimide structures for advanced aerospace applications
Material and process advances ''82; Fourteenth National SAMPE Technical Conference ; 1982 ; Atlanta, GA
1982-01-01
Miscellaneous
No indication
English
Bonded and Bolted Graphite/Polyimide Composite Joints
NTRS | 1985
|Hot forming graphite/polyimide structures
NTRS | 1981
|