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Aero-Thermo-Structural Optimisation in Radome Design

Published online by Cambridge University Press:  04 July 2016

M. J. Wooldridge
M. J. Wooldridge*
Affiliation:
formerly Hawker Siddeley Dynamics Ltd, now at the Commonwealth Scientific and Industrial Research Organisation, Victoria, Australia
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Extract

The design of a homing missile normally involves the incorporation of a dielectric window to form the nose region of the flight vehicle. Immediately this creates a situation in which a compromise is required between the conflicting needs of

  1. (a) The aerodynamicist who requires a fairing of minimum drag, within the length limitations imposed, and which at the same time possesses a reasonably predictable shape. The shape must often satisfy rain erosion requirements.

  2. (b) The heat transfer engineer who requires that the thermal load be spread as uniformly as possible over the fairing surface.

  3. (c) The materials/structures technologist who requires the fairing to be manufactured from readily available material at reasonable cost.

  4. (d) The microwave engineer who requires no fairing at all.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 74 , Issue 711 , March 1970 , pp. 237 - 240
Copyright
Copyright © Royal Aeronautical Society 1970 

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References

1. Owens, R. V. Aerodynamic characteristics of spherically blunted cones at Mach numbers 0-5-5-0. NASA TN D-3088, 1965.Google Scholar
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