INTEGRATED PYLON STRUCTURE FOR PROPULSION SYSTEM

摘要

An integrated pylon structure for a propulsion system is suitable for one end to be connected to an aircraft wing and the other end to be connected to an aircraft engine. The pylon structure includes a pylon box section (110) formed from an upper and a lower bean, a frame (100) and a side wall panel. The pylon structure has a thrust reverser hood connection structure, provided on the side wall and connected with a nacelle thrust reverser hood having a front fixed hood (301) and a rear movable hood (302). A guide rail allows the rear movable hood to slide and open relative to the pylon box section. The engine thrust reverser hood is directly connected to the side wall of the pylon box section and a guide rail on the side wall guides the opening of the thrust reverser hood.

主权项

1. A pylon structure of an integrated propulsion system, which is adapted to be connected to an aircraft airfoil at one end and connected at the other end to an aero-engine having a fan casing, the pylon structure comprising:
a pylon box segment including, an upper beam, a lower beam, a frame and a sidewall panel, wherein the pylon structure further includes: a thrust reverser cowl connection structure disposed on the sidewall panel and connected to a nacelle thrust reverser cowl that includes a front fixed cowl and a rear moveable cowl, the thrust reverser cowl connection structure including at least one guide rail for guiding the rear moveable cowl to enable the rear moveable cowl to slideably open relative to the pylon box segment; wherein the frame includes a front end frame that includes a front wall, where the pylon structure further includes a front installation joint disposed on the front wall of the front end frame of the frame and connected to the fan casing of the aero-engine; wherein the front installation joint includes: a first lug and a second lug respectively protruding outward from a respective one of two opposite sides of the front end frame; and a first link and a second link respectively connected to the first lug and the second lug at one end, and respectively adapted to be connected to the aero-engine at the other end; wherein the first link and the first lug are pivotally connected at a first connection point, and the second link and the second lug are connected respectively at a second connection point and a third connection point.