Patent ID: 8096501

Claim:
An aircraft nacelle which includes: a cowl with a longitudinal axis, an engine housed in the internal space defined by the cowl, an annular channel surrounding the engine and which is designed to receive a secondary flow, the cowl being made up of a fixed part and a moving part designed to slide along the longitudinal axis in order to define a radial opening between the moving part and the fixed part, a thrust reverser system which includes internal flaps fitted so that they rotate and designed to have an at-rest position in which the internal flaps are effectively parallel to the longitudinal axis and a deployed position in which the internal flaps obstruct, at least partially, the annular channel, the moving part of the cowl including a radial housing which extends longitudinally to receive the internal flaps in the at rest position, a system designed to apply an elastic force to each internal flap towards a deployed position, so that control over the position of the internal flaps is achieved directly by sliding the moving part of the cowl, maximum deployment limiters equipping the thrust reverser system, said limiters including a bushing which can move along a rod which extends longitudinally from the fixed part of the cowl across the radial opening and a rod which connects the bushing to the internal flap.