Accession Number:

ADA301715

Title:

Effects of Fabrication and Joining Processes on Compressive Strength of Boron/Aluminum and Borsic/Aluminum Structural Panels,

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Report Date:

1978-04-01

Pagination or Media Count:

56.0

Abstract:

Methods for forming and joining boronaluminum and Borsicaluminum to themselves and to titanium alloys have been studied at the NASA Langley Research Center. The present study was conducted to determine the effects of joining and fabrication methods on panel compressive strengths for composite skin and titanium skin panels with composite stringers. The stringers and panel skins were joined by high strength bolts, by spo welding, by diffusion bonding, by polyimide adhesive bonding, or by brazing. The test results show that hot and cold forming of metal-matrix composite stringers did not degrade fiber properties, whereas a eutectic consolidation and fabrication process did cause fiber degradation. Of the processes investigated for joining the metal-matrix stringers, the diffusion-bonded and adhesive-bonded panels developed the highest buckling loads and stresses. A program for predicting buckling loads BUCLASP2 consistently predicted higher buckling loads than were determined experimentally.

Subject Categories:

  • Metallurgy and Metallography

Distribution Statement:

APPROVED FOR PUBLIC RELEASE