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An investigation of the grid fins as control surface devices for missiles

Published online by Cambridge University Press:  04 July 2016

S. Chen ,
M. Khalid ,
H. Xu  and
F. Lesage
S. Chen
Affiliation:
Institute of Aerospace Research (IAR), National Research Council (NRC), Ontario, Canada
M. Khalid
Affiliation:
Institute of Aerospace Research (IAR), National Research Council (NRC), Ontario, Canada
H. Xu
Affiliation:
Institute of Aerospace Research (IAR), National Research Council (NRC), Ontario, Canada
F. Lesage
Affiliation:
Defense Research Establishment Valcartier (DREV), Canada
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Abstract

Recently, grid fins have been receiving increasing attention as a practical and efficient means of controlling missile trajectory. Preliminary studies at IAR have demonstrated that modern CFD methods can be used for computing flows past complex grid fin type configurations, and that these methods are more soundly physically based than the earlier vortex lattice and/or shock expansion methods.

The current paper addresses the issue of the grid fin size, in terms of both the panel thickness and the frontal shape. The study covers three thicknesses for the grid fin panel, with front shapes having a simple blunt square face, as well as a sharp knife-edge shape. In addition, an important aspect of the present investigation is to quantify the aerodynamic effect of the ramp fairing installed immediately upstream of the blunt base upon which the grid fin assembly resides. A comparison of flow field characteristics and aerodynamic coefficients of the grid fin assembly, with and without the fairing ramp, would provide a direct means of evaluating the effect of the ramp. At this stage, the investigations are based on Euler calculations. The present study focuses on a standard grid fin configuration mounted on a generic cylindrical body.

Type
Research Article
Information
The Aeronautical Journal , Volume 104 , Issue 1034 , April 2000 , pp. 183 - 190
Copyright
Copyright © Royal Aeronautical Society 2000 

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