DocumentCode
1049658
Title
Frequency domain approach to guidance system design
Author
Yanushevsky, Rafael
Author_Institution
Res. & Technol. Consulting, Bethesda
Volume
43
Issue
4
fYear
2007
fDate
10/1/2007 12:00:00 AM
Firstpage
1544
Lastpage
1552
Abstract
The frequency domain approach to guidance system design is presented. The model of the guidance control system reflects the most important characteristics of the flight control system that combines airframe and autopilot dynamics (damping, natural frequency, time constant, and airframe zero frequency). The analytical expressions for frequency response and related expressions for missile system performance are given. The analytical results obtained can be utilized for missile system design.
Keywords
aircraft control; aircraft navigation; frequency response; frequency-domain analysis; missile guidance; airframe zero frequency; autopilot dynamics; flight control system characteristics; frequency domain approach; frequency response; guidance control system design; missile system design; missile system performance; proportional navigation guidance system; Acceleration; Aerospace control; Control theory; Damping; Frequency domain analysis; Frequency response; Missiles; Navigation; Performance analysis; System performance;
fLanguage
English
Journal_Title
Aerospace and Electronic Systems, IEEE Transactions on
Publisher
ieee
ISSN
0018-9251
Type
jour
DOI
10.1109/TAES.2007.4441757
Filename
4441757
Link To Document