This paper describes the synthesis of a SISO scheduled controller for a launcher vehicle. The problem consists
in designing a control law which will be valid on the atmospheric ascent trajectory from time 25 s to time 60 s,
while ensuring robustness and performance requirements. Moreover a flexible model with two bending modes is
considered, making the problem more challenging. An algorithm based upon guardian maps has been retained in
order to find an a priori fixed architecture controller. The algorithm yields a sequence of controllers that ensures
that pole confinement constraints are fulfilled for any time between 25 s and 60 s. The user can then interpolate
those controllers to find a scheduled controller with respect to time
