A fluxless brazing process has been developed that minimizes degradation of the mechanical properties of Borsic/aluminum composites. The process, which employs 718 aluminum alloy braze, is being used to fabricate full scale Borsic/aluminum-titanium honeycomb-core panels for Mach 3 flight testing on the YF-12 aircraft and ground testing in support of the Supersonic Cruise Aircraft Research (SCAR) Program. The manufacturing development and results of shear tests on full scale panels are presented. Nondestructive evaluation of brazed Borsic/aluminum honeycomb wing panel; the variables include shear strain, loads (forces), brazing temperature, and brazing time (min); 3 figures and no tables.
Brazed Borsic/Aluminum Structural Panels
1977
24 pages
Report
No indication
English
Composite Materials , Aircraft , Airframe materials , Aluminum alloys , Boron , Brazing , Yf-12 aircraft , Supersonic aircraft , Honeycomb structures , Metal matrix composites , Production engineering , Titanium , Loads (Forces) , Metal-metal bonding , Shear strain , Temperature effects , Time , Borsic reinforced composites , Aluminum matrix composites
Brazed Borsic/aluminum structural panels
NTRS | 1977
|Brazed borsic/aluminum structural panels
TIBKAT | 1977
|