By Topic

Missile autopilot design using dynamic inversion and structured singular value synthesis

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
$33 $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)
M. B. McFarland ; Navigation & Control Branch, US Air Force Armament Directorate, Eglin AFB, FL, USA ; C. N. D'Souza

A methodology incorporating both dynamic inversion and structured singular value synthesis is employed to design a robust nonlinear autopilot for an air-to-air missile. The nonlinear components include fast and slow inversion loops which approximately linearize the system when closed in the absence of modeling errors. A feedback control law is designed for this closed-loop system in the presence of structured uncertainties. The current controller architecture differs from previous work in the choice of desired body rate dynamics used in the fast inversion. In this case, the desired dynamics correspond to the body rate dynamics at a central flight condition

Published in:

Control Applications, 1994., Proceedings of the Third IEEE Conference on

Date of Conference:

24-26 Aug 1994