A successful brazing process was developed and evaluated for fabricating full-scale titanium-clad Borsic/aluminum skin-stringer panels. A panel design was developed consisting of a hybrid composite skin reinforced with capped honeycomb-core stringers. Six panels were fabricated for inclusion in the program which included laboratory testing of panels at ambient temperatures and 533 K (500 F) and flight service evaluation on the NASA Mach 3 YF-12 airplane. All panels tested met or exceeded stringent design requirements and no deleterious effects on panel properties were detected followng flight service evaluation on the YF-12 airplane.
Fabrication and Evaluation of Brazed Titanium-Clad Borsic/Aluminum Skin-Stringer Panels
1980
41 pages
Report
No indication
English
Aircraft , Manufacturing Processes & Materials Handling , Manufacturing, Planning, Processing & Control , Engineering Materials , Airframe materials , Borsic (Tradename) , Brazing , Fabrication , Honeycomb structures , Stringers , Aluminum , Composite materials , Panels , Shear strength , Skin (Structural member) , Titanium , Yf-12 aircraft
Brazed Borsic/aluminum structural panels
NTRS | 1977
|Brazed borsic/aluminum structural panels
TIBKAT | 1977
|Brazed Borsic/Aluminum Structural Panels
NTIS | 1977
|