Sandwich Construction

W.G. Heath, Dip.Ae. (Hull), A.F.R.Ae.S. (Assistant Chief Structural Engineer, A. V. Roe and Co. Ltd., Greengate, Manchester.)

Aircraft Engineering and Aerospace Technology

ISSN: 0002-2667

Publication date: 1 July 1960


An extensive bibliography exists on sandwich construction; it is felt, however, that few of the available papers are readily adaptable for use in aircraft design offices. This paper, whilst based on an existing theory, extends it to include panels with faces of unequal thicknesses and aeolotropic cores such as honeycomb. The various modes of failure are described, and comparisons are drawn between the equilibrium equations and those derived in the theory of solid plates. A very simple equation for the overall instability of a sandwich panel is obtained, based on the concept of ‘width reduction factors’ which make allowance for core flexibility and unequal face thicknesses. Methods are described for presenting these reduction factors' and other important parameters in the form of data sheets, of which examples are given. The panels which are discussed are assumed to be flat, and compressed by a load uniformly distributed across their ends. The edges, which are simply‐supported, are taken to be long in relation to the panel width.


Heath, W. (1960), "Sandwich Construction", Aircraft Engineering and Aerospace Technology, Vol. 32 No. 7, pp. 186-191.

Download as .RIS




Copyright © 1960, MCB UP Limited

Please note you might not have access to this content

You may be able to access this content by login via Shibboleth, Open Athens or with your Emerald account.
If you would like to contact us about accessing this content, click the button and fill out the form.
To rent this content from Deepdyve, please click the button.