Hostname: page-component-586b7cd67f-rdxmf Total loading time: 0 Render date: 2024-11-28T15:29:24.994Z Has data issue: false hasContentIssue false
  • English
  • Français

Materials for Aircraft Structures Subjected to Kinetic Heating*

Published online by Cambridge University Press:  28 July 2016

A. J. Murphy
A. J. Murphy*
Affiliation:
College of Aeronautics
Get access Rights & Permissions [Opens in a new window]

Extract

The requirements of aeronautical engineers have been one of the greatest stimulants of metallurgical research and development during the present generation. Materials for the piston engine and the airframe had shared about equally the attention of the research metallurgist from the early twenties to about 1945. Then the gas turbine appropriated the major effort in metallurgical research because it was clear that progress with this propulsive unit was inescapably dependent upon the production of metals and alloys capable of giving reliable service at ever increasing temperatures. Here it was a question of evolving new materials having characteristics for which no appreciable demand existed before the advent of the gas turbine. The past five years have seen the airframe come back into the picture metallurgically, because of the new concern with fatigue and because supersonic speeds are bringing with them service temperatures for the airframe higher than anything arising while speeds of flight were comfortably subsonic.

Type
Research Article
Information
The Aeronautical Journal , Volume 61 , Issue 562 , October 1957 , pp. 653 - 666
Copyright
Copyright © Royal Aeronautical Society 1957

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

*

A Section Lecture given on 11th December 1956.

References

1. Hartshorn, A. S. (1955). The Temperature of Materials at High Flight Speeds and the Problems Involved. R.A.E. Tech. Note Aero 2397, September 1955.Google Scholar
2. Meikle, G. (1956). Summary of the Effect of Heating Some Aluminium Alloys and Alloy Steels at Elevated Temperatures. R.A.E. Tech. Note Met. 187, and Lecture to the Institution of Metallurgists Refresher Course, Llandudno, 1956.Google Scholar
3. Battelle Memorial Institute (1948). An Appraisal of the Usefulness of Aluminium Alloys for Supersonic Aircraft and Guided Missile Construction. R.104, 8th August 1948.Google Scholar
4. Aluminium Industrie, A.G., Switzerland. S.A.P.Google Scholar
5. Dryden, H. L. and Duberg, J. E. (1955). Aeroelastic Effects of Aerodynamic Heating. Presented to 5th General Assembly of the Advisory Group for Aeronautical Research and Development, Ottawa, June 1955, Published by N.A.C.A.Google Scholar
6. Pilling, N. B. and Talbot, A. M. (1939). Dispersion Hardening Alloys of Nickel and Iron-Nickel-Titanium. Paper Presented before 21st Annual Convention of American Society of Metals, October 1939.Google Scholar
7. Mudge, W. A. and Talbot, A. M. (1956). Ni-Span. Iron Age 25th April 1956.Google Scholar
8. The Mond Nickel Co. Ltd. The Physical Properties of the Nickel-Iron Alloys.Google Scholar
9. Baur, G. W. (1956). The Properties of MST.6A14V May Also be Enhanced. Metal Progress, October 1956.Google Scholar