Patent ID: 8943793
Filing Date: 2015-02-03
Classification: B64D

Abstract:
1. An aircraft nacelle comprising: a front section; a middle section surrounding a fan; and a rear section formed of two halves, the rear section surrounding a turbojet engine: wherein the rear section comprises: a central part defined by at least two internal panels, wherein each internal panel is fixed on a corresponding lower beam, a cold air annular flow path passing through said at least two internal panels and said central part via a pipe, the two halves each having the pipe; at least one cavity at a six o'clock position from a mounting point of the nacelle and an aircraft wing, said cavity positioned under said central part, at least one latch connecting said two halves, wherein each latch of the at least one latch is mounted on the corresponding lower beam and is positioned between said central part and said cavity, and a space formed by the lower beams wherein said pipe provides a fluidic communication between the cold air annular flow path and the cavity via said space.