Design of a nonlinear missile flight control system using optimal time-domain finite element method
by
S. Ahmad Fazelzadeh
Mechanical Eng. Dept., Shiraz University, Shiraz, I.R.Iran
Coauthors: Ali Rasti

In this paper, an optimal time-domain finite element method is used to design nonlinear missile autopilot system to stabilize the missile airframe and track a commanded angle of attack. The longitudinal dynamic model of missile is considered. The model is consisted of four strictly nonlinear differential equations describing the pitch-plane rigid-body dynamics of missile. Angle of attack regulation of a hypothetical tail-controlled missile has been considered which is important for the guidance purpose. The problem has been formulated through the variational approach. The time-domain finite element discretized form of the regulator performance index, state equation constraints and the related boundary conditions are presented. Finally by setting out the discrete equations, a set of nonlinear algebraic equations is generated. The numerical simulation results of the state and control parameters at the optimal conditions are illustrated the excellent efficiency of the time-domain finite element method. Also, the effects of the number of time segments on the performance index are examined.

Date received: March 23, 2008