Patent ID: 8186620
Filing Date: 2012-05-29
Classification: B64C

Abstract:
1. A landing gear system for an aircraft, the landing gear system comprising: a shock strut assembly having a housing, a cylinder and a piston, wherein the piston is movably receivable with respect to the cylinder and the housing is sized to telescopically receive at least a portion of the cylinder, the housing being configured and adapted to be pivotally coupled to the aircraft at a first longitudinal distance from an aircraft center of gravity; and a linkage member having a first portion configured and adapted to be pivotally coupled to the aircraft at a second longitudinal distance from the aircraft center of gravity, the second longitudinal distance aft of the first longitudinal distance by a desired amount, and a second portion pivotally connected to a pivot point on the cylinder, wherein the first portion of the linkage member is moveable relative to the second portion of the linkage member, the linkage member being actuatable from a first length to a second length to change a pre-flight angle of attack of the aircraft when the landing gear system is in a deployed configuration, and wherein, at least a portion of the piston is movably received within the cylinder, and at least a portion of the cylinder is telescopically received within the housing.