A turbojet engine rear portion, comprising: - an upstream stator structure ; - a convergent-divergent nozzle with a variable geometry comprising a set of convergent flaps distributed around a longitudinal axis of the rear portion of the turbojet engine, each comprising a panel intended to channel an exhaust gas flow (F4) within the nozzle, and each having an upstream end hinged on the upstream stator structure, and further comprising a set of divergent flaps distributed around the longitudinal axis , each comprising a panel intended to channel the exhaust gas flow within the nozzle, and each having an upstream end hinged on a downstream end of a corresponding convergent flap; - a synchronisation ring arranged around the set of convergent flaps or the upstream stator structure ; - drive means configured to move the synchronisation ring in translation according to the longitudinal axis , relative to the upstream stator structure ; - actuating means by which the synchronisation ring acts on at least some of the convergent flaps , called controlled convergent flaps, to control a geometric variation of the nozzle; and - means for controlling the positions of the divergent flaps on the basis of those of the convergent flaps, comprising a first connecting rod having a first end portion hinged to the corresponding convergent flap and an opposite second end portion , a second connecting rod having a first end portion hinged to the corresponding divergent flap and an opposite second end portion , and a third connecting rod having a first end portion hinged to the synchronisation ring and an opposite second end portion ; characterized in that the second end portion of the first connecting rod is hinged to at least one amongst the second end portion of the second connecting rod and the second end portion of the third connecting rod , and the second end portion of the third connecting rod is hinged to the second end portion of the second connecting rod . - an upstream stator structure ; - a convergent-divergent nozzle with a variable geometry comprising a set of convergent flaps distributed around a longitudinal axis of the rear portion of the turbojet engine, each comprising a panel intended to channel an exhaust gas flow (F4) within the nozzle, and each having an upstream end hinged on the upstream stator structure, and further comprising a set of divergent flaps distributed around the longitudinal axis , each comprising a panel intended to channel the exhaust gas flow within the nozzle, and each having an upstream end hinged on a downstream end of a corresponding convergent flap; - a synchronisation ring arranged around the set of convergent flaps or the upstream stator structure ; - drive means configured to move the synchronisation ring in translation according to the longitudinal axis , relative to the upstream stator structure ; - actuating means by which the synchronisation ring acts on at least some of the convergent flaps , called controlled convergent flaps, to control a geometric variation of the nozzle; and - means for controlling the positions of the divergent flaps on the basis of those of the convergent flaps, comprising a first connecting rod having a first end portion hinged to the corresponding convergent flap and an opposite second end portion , a second connecting rod having a first end portion hinged to the corresponding divergent flap and an opposite second end portion , and a third connecting rod having a first end portion hinged to the synchronisation ring and an opposite second end portion ; characterized in that the second end portion of the first connecting rod is hinged to at least one amongst the second end portion of the second connecting rod and the second end portion of the third connecting rod , and the second end portion of the third connecting rod is hinged to the second end portion of the second connecting rod . <EOS>