Unfoldable divergent nozzle for a rocket engine

An unfoldable divergent nozzle for a rocket engine comprises a set of elementary individual panels of a refractory material articulated together and with respect to a fixed upstream portion of the divergent nozzle in the vicinity of the neck of the nozzle. The articulations between two adjacent panels arranged to be folded on one another with their inner surfaces facing one another; each comprise at least one hinge with two axles inserted in the walls of the two panels articulated to one another, and held at a constant distance from one another by a link set back with respect to the thickness of the panel. Two adjacent panels have in the vicinity of a hinge two cylindrical surfaces respectively centered on each of the axles and rollable without sliding on one another.