Titanium Development Program. Volume 5
Final technical rept. Dec 1957-May 1961
GENERAL DYNAMICS SAN DIEGO CA CONVAIR DIV
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Typical airframe structures, fuselage frames, wing leading edge, bleed air ducts, tail cone, shear panels and compression panels of Ti-4Al-3Mo-1V and Ti-13V-11Cr-3Al were subjected to test loads in increasing increments of 100 degrees from room temperature to maximum temperatures of 800 F and 900 F, depending on the part. Riveted and resistance welded construction was evaluated in the fuselage frame and wing leading edge.