On the Guidance and Control of a Spinning Missile
by
Ozan Tekinalp
Middle East Technical University, Aerospace Engineering Department, Ankara, Turkey
Coauthors: Bulent Semerci, Graduate Student, METU, Aerospace Engr. Dept. (also Engineer at the Roketsan Missile Industries), Osman Merttopcuoglu, Senior Engineer, Roketsan Missile Industries, Ankara, Turkey

Guidance and control of a spinning missile is investigated. A new frame called non-rolling frame is proposed to carry out proportional navigation and control. It is shown that the missile equations of motion written in this new frame are simpler, and trim conditions may also be defined in this frame without neglecting gravity contributions. The proportional navigation with linear quadratic regulator type autopilot designs are obtained. The robustness of the designs and effectiveness of the approach are demonstrated using nonlinear spinning missile simulations.

Date received: January 15, 2002

Copyright © 2002 by the author(s). The author(s) of this document and the organizers of the conference have granted their consent to include this abstract in Atlas Conferences Inc. Document # cago-26.