N.F. Harpur

With the advent of supersonic manned aircraft designed to cruise at Mach numbers of 2, or thereabouts, the structure temperatures arising from kinetic heating effects begin to have a significant influence on the properties of the aluminium alloys, conventionally used for the primary structure. At higher speeds still, these aluminium alloy materials, unless cooled, suffer such deterioration in properties that it becomes desirable to change to other materials such as titanium or steel. Such a change gives rise to new problems of design, manufacture and assembly associated with the physical properties of the new materials. This paper describes some of the problems associated with: (a) the use of aluminium alloys at the highest practicable operating temperatures, (b) the use of other materials, principally steel, at still higher tern per a tures. In the first case these problems are primarily associated with the determination of the strength and other properties required for design taking into account the effects of heating over long periods. In the second case, these problems are associated not only with the determination of these same properties for design, but also with the processing and assembly of the airframe components. The latter are the major sources of difficulty until such temperatures are reached that the properties of steels begin to deteriorate significantly.

WGL-Tagung, Hamburg 1959

Conference Paper

englisch

A4, 8 Seiten

Jahrbuch der Wissenschaftlichen Gesellschaft für Luftfahrt, 1959; S.357-364; 1959; Braunschweig : Vieweg

NA

Das Dokument enthält eine zusätzliche Seite über die anschließende Diskussion

werkstoffe

Bestellbar

1960