Aerospace launch vehicle control: a gain scheduling approach

This paper presents a methodology for designing an aerospace launch vehicle autopilot. Linear controllers are first designed using a multi-objective method based on the Youla parameterization and the optimization under constraints described by linear matrix inequalities. These controllers are then interpolated in such a way that the stability of the closed-loop plant is guaranteed. Results obtained from a nonlinear simulator against wind disturbances and parameter uncertainties are then given.