A nacelle for an aircraft turbojet engine , comprising: - an outer cowling , comprising: ∘ a structure , comprising at least one opening , ∘ at least one panel , at least pivotally mounted about an axis between a closure position according to which it seals said opening and an opening position according to which it enables the passage of a portion (F') of a secondary air flow (F) through said opening, the secondary air flow flowing in an annular channel defined between said outer cowling and an inner fixed structure of the nacelle defining a fairing of the turbojet engine , - a system for actuating the panel , designed so as to lock the panel in said closure position and to alternately displace said panel between said closure position and said opening position, said nacelle being characterized in that said actuation system comprises: - at least one lateral connecting rod , on the hand linked to the panel and on the other hand linked to the structure of the outer cowling , said lateral connecting rod being pivotally mounted relative to the structure , on the one hand about a first pivot axis substantially parallel to a longitudinal axis of the nacelle and, on the other hand, about a second pivot axis substantially perpendicular to the first pivot axis , - a linear actuator , attached to said lateral connecting rod , prone to alternately switch between a retracted position and an elongated position, the actuation system being further designed so as to displace the lateral connecting rod during the extension of said actuator , causing the pivoting of said lateral connecting rod about said first and second pivot axes, and so that the lateral connecting rod , bearing on the structure , exerts, during the displacement thereof, a force on the panel , causing a pivoting of said panel about its axis . - an outer cowling , comprising: ∘ a structure , comprising at least one opening , ∘ at least one panel , at least pivotally mounted about an axis between a closure position according to which it seals said opening and an opening position according to which it enables the passage of a portion (F') of a secondary air flow (F) through said opening, the secondary air flow flowing in an annular channel defined between said outer cowling and an inner fixed structure of the nacelle defining a fairing of the turbojet engine , ∘ a structure , comprising at least one opening , ∘ at least one panel , at least pivotally mounted about an axis between a closure position according to which it seals said opening and an opening position according to which it enables the passage of a portion (F') of a secondary air flow (F) through said opening, the secondary air flow flowing in an annular channel defined between said outer cowling and an inner fixed structure of the nacelle defining a fairing of the turbojet engine , - a system for actuating the panel , designed so as to lock the panel in said closure position and to alternately displace said panel between said closure position and said opening position, - at least one lateral connecting rod , on the hand linked to the panel and on the other hand linked to the structure of the outer cowling , said lateral connecting rod being pivotally mounted relative to the structure , on the one hand about a first pivot axis substantially parallel to a longitudinal axis of the nacelle and, on the other hand, about a second pivot axis substantially perpendicular to the first pivot axis , - a linear actuator , attached to said lateral connecting rod , prone to alternately switch between a retracted position and an elongated position, <EOS>