Study made at North American Aviation, Inc; wing structure weight plus insulation is computed for delta-winged aircraft cruising at 70, 000 ft, thermal stability limits of JP-6 fuel being such that they require thermal protection from aerodynamic heating; spanwise and chordwise bending, transverse and torsional shear, and internal pressure loadings are considered; integrally stiffened wings, using A M-355 steel, all-beta titanium alloy, and beryllium, are compared with PH15-7Mo steel brazed honeycomb sandwich wing.
Mach 3 wing structures stiffened skin versus sandwich
SAE -- Paper
SAE Meeting ; 1960 Sandwich construction
1960
47 pages
Conference paper
English
© Metadata Copyright Elsevier B. V. All rights reserved.
Mach 3 Wing Structures Stiffened Skin versus Sandwich
SAE Technical Papers | 1961
|Bonding Technique for Stiffened-Skin Structures
NTRS | 1985
|