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.


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    Title :

    Mach 3 wing structures stiffened skin versus sandwich


    Additional title:

    SAE -- Paper


    Contributors:

    Conference:

    SAE Meeting ; 1960 Sandwich construction



    Publication date :

    1960


    Size :

    47 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Mach 3 Wing Structures Stiffened Skin versus Sandwich

    Joanides, Jack C. / Lackman, Leslie M. / Mellin, Stanley C. | SAE Technical Papers | 1961




    Bonding Technique for Stiffened-Skin Structures

    Frickland, P. O. / Headrick, E. L. / Hasegawa, T. | NTRS | 1985