Thrust reverser system limiting aerodynamic perturbation in an inactive configuration

A thrust reverser system for a double-flow aircraft turbomachine, the thrust reverser system comprising:

• at least one thrust reversal grating through which air from a secondary channel of the turbomachine circulates in an active configuration of the thrust reverser system,
• at least one reverser gate configured to at least partly block said secondary channel downstream of the at least one thrust reversal grating when the system is in the active configuration, wherein the at least one reverser gate is produced using at least two gate sections arranged in a state folded back relative to one another in an inactive configuration of the reverser system and housed in a housing space situated outside of said secondary channel and in which is also located said at least one thrust reversal grating to which at least one of said at least two gate sections is connected,
• wherein the thrust reverser system is configured in such a way that there occurs simultaneously, upon a transition from the inactive configuration to the active configuration:
• a backward displacement of the at least one thrust reversal grating towards a nacelle opening, released by a mobile outer nacelle fairing driven backwards by the at least one thrust reversal grating via the at least one of said at least two gate sections;
• and
• a deployment of said at least two gate sections relative to one another, until said at least two gate sections reach a deployed position of blocking in the secondary channel.