Gondola turbojet engine with a device for circumferential force PERCEPTION

摘要

1. The nacelle (1) for an aircraft turbojet engine, comprising: - a casing (41) of the fan, the fan covering before the turbojet engine, said casing (41) covered by an outer fan cowl (40) of the fan and is secured to the support pole (2) of the nacelle (1), - an internal structure disposed over the casing (41) enclosing the fan and turbojet; u thrust reverser (50) behind the casing (41) and comprising a fan cowl defining together with the inner structure ring circulation airflow path, wherein said hood encloses the external line (LE) of said annular path and consists of two removable polukapotov ( 51) having respective upper edges (52) which are provided with means (53) hinging polukapotov (51) on the pylon (2), wherein the shape of said means (53) provides a hinge polukapotov rotation (51) between the closed and from rytym positions about respective longitudinal axes forming a hinge line (LC); u device (6; 7; 8; 9; 10) for sensing circumferential forces that connects together the top edges (52) polukapotov (51), said device (6; 7; 8; 9; 10) for sensing effort configured to, on the one hand, to fix polukapoty (51) in the closed position when it is in the locking configuration, and, on the other hand, provide disclosure polukapotov (51) when it is in the unlocking configuration, characterized in that the device (6; 7; 8; 9; 10) arranged resist forces under the forward part of the pylon (2) before the means (53) arnirnogo polukapotov fastening (51) on the pylon (2), and is located