Cart (Loading....) | Create Account
Close category search window
 

Electromagnetic Propagation through Shock Ionized Air Surrounding Glide Re-Entry Spacecraft

Sign In

Cookies must be enabled to login.After enabling cookies , please use refresh or reload or ctrl+f5 on the browser for the login options.

Formats Non-Member Member
$31 $13
Learn how you can qualify for the best price for this item!
Become an IEEE Member or Subscribe to
IEEE Xplore for exclusive pricing!
close button

puzzle piece

IEEE membership options for an individual and IEEE Xplore subscriptions for an organization offer the most affordable access to essential journal articles, conference papers, standards, eBooks, and eLearning courses.

Learn more about:

IEEE membership

IEEE Xplore subscriptions

2 Author(s)
McCabe, William M ; Department of Electrical Engineering, Institute of Technology, St. Louis University, St. Louis, Mo. ; Stolwyk, Carl F.

Radio frequency communication with spacecraft is necessary during all phases of flight including the period of atmospheric re-entry. During re-entry, the velocity of these vehicles is sufficiently high to induce thermal ionization of the air surrounding the vehicle. Resultant electron concentrations are in some cases high enough to interfere with normal communications with the vehicle. This interference takes the form of attenuation or reflection of signals transmitted from the vehicle. Exact analysis of the problem requires precise information regarding the flow field surrounding the vehicle of interest. Since these data are generally unavailable until late in the vehicle design phase, it is the purpose of this paper to examine means by which an approximation of the interference effects may be obtained when only the trajectory and body configuration are known. Many glide vehicle designs are complex in their shape; however, for the purposes of analysis of phenomena associated with the vehicle configuration, the vehicle may be considered to be composed of combinations of shapes having more elemental forms. A procedure is described by which analysis of propagation effects for these elemental bodies may be used to approximate the conditions to be expected in the corresponding region of the more complex vehicle. A sample problem is presented as a demonstration of the procedure.

Published in:

Space Electronics and Telemetry, IRE Transactions on  (Volume:SET-8 ,  Issue: 4 )

Date of Publication:

Dec. 1962

Need Help?


IEEE Advancing Technology for Humanity About IEEE Xplore | Contact | Help | Terms of Use | Nondiscrimination Policy | Site Map | Privacy & Opting Out of Cookies

A not-for-profit organization, IEEE is the world's largest professional association for the advancement of technology.
© Copyright 2014 IEEE - All rights reserved. Use of this web site signifies your agreement to the terms and conditions.