Advanced fabrication processes and adhesive bonding methods have been developed for the fabrication of full scale fiberglass-polyimide honeycomb stiffened HTS-1 graphite/PMR-15 polyimide panels that meet the design criteria for an upper wing panel of the NASA YF-12 aircraft. Detailed manufacturing, bonding, and autoclave cure procedures are presented. Nondestructive test methods including pulse echo and through-transmission ultrasonic C-scan and laser holography were developed to detect flaws in components and the completed panels. Panels were tested in shear at room temperature and 533 K (500 F) following a variety of thermal exposures to obtain load, deflection and failure analysis data.
Graphite polyimide fabrication research for supersonic cruise aircraft
National Symposium and Exhibition on The 1980''s - Payoff decade for advenced materials ; 1980 ; San Diego, CA
1980-01-01
Miscellaneous
No indication
English
Fabrication research for supersonic cruise aircraft
Tema Archive | 1979
|Fabrication research for supersonic cruise aircraft
NTRS | 1979
|III. Supersonic Cruise Aircraft
NTRS | 1960
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