Modeling and robust control of a spinning missile

Date

2003-12-01

Author

Semerci, Bulent
Merttopcuoglu, Osman
Tekinalp, Ozan

Metadata

Show full item record

This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Item Usage Stats

14
views

0
downloads

Modeling and control of a spinning missile is investigated. A new frame called non-rolling frame is proposed to carry out proportional navigation guidance laws 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. Linear quadratic regulators are designed using the linearized non-rolling frame equations. The effectiveness of the designs under changing flight conditions is demonstrated through nonlinear simulations. The effectiveness of the design for target engagement in spite of parameter uncertainty is also demonstrated through Monte Carlo simulations.

Subject Keywords

Linear quadratic regulator, Missile control, Modeling spinning missile, Monte Carlo simulations, Proportional navigation, Robust control

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=1542287671&origin=inward
https://hdl.handle.net/11511/106854

Conference Name

22nd International Conference on Modelling Identification and Control

Collections

Department of Aerospace Engineering, Conference / Seminar

Citation Formats

B. Semerci, O. Merttopcuoglu, and O. Tekinalp, “Modeling and robust control of a spinning missile,” presented at the 22nd International Conference on Modelling Identification and Control, Innsbruck, Avusturya, 2003, Accessed: 00, 2023. [Online]. Available: https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=1542287671&origin=inward.