Abstract: The invention relates to a wide-vectoring, axisymmetric turbojet-engine exhaust nozzle including vectoring structure (12) supporting a plurality of converging flaps (21). The vectoring structure is mounted on the downstream end of an exhaust housing (2) by means of an intermediate ring (9) which is pivotable about a first axis relative to the exhaust housing (2) and further about a second axis perpendicular to the first axis and relative to the vectoring structure (12). The converging flaps (21) hinge on the downstream end of the vectoring structure (12). A single drive ring (27) controlled by three linear actuators (28) and linked by linkrods (24) to the converging flaps (21) controls the tipping of the vectoring structure (12) and the kinematics of the flaps (21).