| Authors | M Irani Rahaghi, J Roshanian |
|---|---|
| Journal | Journal of aerospace science and technology |
| Paper Type | Full Paper |
| Published At | 2006 |
| Journal Grade | Scientific - research |
| Journal Type | Typographic |
| Journal Country | Iran, Islamic Republic Of |
Abstract
This paper presents an application of the nonlinear optimal control techniques to the design of launch vehicle autopilots. The optimal control is given by the solution to the Hamilton-Jacobi-Bellman (HJB) equation, which in this case cannot be solved explicity. A method based upon Successive Galerkin Approximation (SGA) is used to obtain an approximate optimal solution. Simulation results involving the three degrees-of-freedom (3DOF) model of a launch vehicle during atmospheric flight are reported to demonstrate the performance of the considered autopilot. Alternative results are also presented for classical and linear optimal approaches.