Abstract: An axisymmetric, converging-diverging and swiveling exhaust nozzle includes converging flaps (3) driven by an axially displaceable drive ring (7). The diverging flaps (15) are connected by linkrods (20) to a pivoting ring (21). The pivoting ring (21) is mounted in swiveling manner on a spherical segment (30) fixedly joined to the structure (13). In an embodiment variation, the spherical segment (30) is mounted by a sliding connection on the stationary structure. A rotation-blocking system (33) precludes the rotation of the spherical segment (30) about the axis X of the turbojet engine.

Abstract: An axisymmetric, converging-diverging exhaust nozzle swiveled by a guided vectoring ring (20). The guides comprise three axial apertures (44) which are each located in a base firmly joined to relatively fixed structure and of which the center planes intersect along the longitudinal axis of the turbojet-engine. The side walls (45) of the apertures (43) guide three mutually equidistant spherical rollers (41) fastened to radial stubs (40) firmly affixed to the vectoring ring (20).

Abstract: An axisymmetric, converging-diverging turbojet-engine exhaust nozzle for jet deflection. The diverging flaps are connected by linkrods to a vectoring ring (13). The vectoring ring (13) is driven by linear actuators (20) anchored in the stationary structure (2). The linear actuators (20) are connected by a swivel (22) to the vectoring ring (13) and are affixed to the stationary structure (2) to absorb the tangential loads applied by the exhaust gases on the diverging flaps and to allow positioning the vectoring ring (13). Preferably the linear actuator (20) is connected by a sheath (25) to the vectoring ring (13), the sheath (25) slidable on the actuator case (26) and being displaceable in a radial plane passing through the turbojet-engine's axis.