DocumentCode :
3686251
Title :
Nonlinear missile autopilot design using a density function-based sum-of-squares optimization approach
Author :
Min-Won Seo;Hyuck-Hoon Kwon;Han-Lim Choi
Author_Institution :
Pangyo R&
fYear :
2015
Firstpage :
947
Lastpage :
952
Abstract :
This paper presents a procedure of a Sum-Of-Squares (SOS) based autopilot design for a Skid-To-Turn (STT) missile. In particular, we consider a nonlinear short period mode in the pitch dynamic model of a SRAAM (Short-Range Air-to-Air Missile). A nonlinear state-feedback controller is designed using SOS Optimization approach, taking advantage of its capability of transforming a control design problem into a convex optimization problem. The dynamic model for autopilot design is represented as polynomial equations through the approximation of aerodynamic coefficients. Then, appropriate density functions, based on the dual Lyapunov theorem, are introduced to formulate the nonlinear control design as a convex program. The performance of the proposed method is verified via numerical simulations, including the case with uncertainty in the aerodynamic coefficients.
Keywords :
"Missiles","Aerodynamics","Acceleration","Polynomials","Stability analysis","Uncertainty","Nonlinear dynamical systems"
Publisher :
ieee
Conference_Titel :
Control Applications (CCA), 2015 IEEE Conference on
Type :
conf
DOI :
10.1109/CCA.2015.7320734
Filename :
7320734
Link To Document :
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