Abstract: An aircraft landing gear assembly including a first landing gear element movably coupled relative to a second landing gear element to pivot about a pivot axis; a cam surface defined by the second landing gear element; and a leaf spring having a first end region and a second end region, the first end region of the leaf spring being coupled to the first landing gear element including a cam follower arranged in moving contact with the cam surface such that the cam follower moves from a first region to a third region via a second region, wherein the cam surface is shaped such that a distance between the pivot axis and the cam surface increases between the first region and the second region and the distance between the pivot axis and the cam surface varies between the second region and the third region of the cam.

Abstract: Describes a deflection mechanism of the flap panels of an aircraft, the aforesaid deflection mechanism being connected to a wing of an aircraft by means of a first fixed structure and to the flap panels by linkage points, in order to support and deflect the flap panels in desired positions, the deflection mechanism of the flap panels of an aircraft comprises of a set of moving hinged links pivotally connected with each other and linked to a first fixed structure, and a hinged drive link connected to the flap panel and to a second fixed structure, the set of moving hinged links being linked to the flap panel by at least one linkage point in order to pivot jointly the moving hinged links deploying the flap panels in an initially predominantly rectilinear and subsequently deflected trajectory and at the same time aligned with a longitudinal direction of the aircraft, without the use of tracks and rollers, the hinged drive link being pivoted from the movement of the flap panels by the set of moving hinged links.

Abstract: Describes a deflection mechanism of the flap panels of an aircraft, the aforesaid deflection mechanism being connected to a wing of an aircraft by means of a first fixed structure and to the flap panels by linkage points, in order to support and deflect the flap panels in desired positions, the deflection mechanism of the flap panels of an aircraft comprises of a set of moving hinged links pivotally connected with each other and linked to a first fixed structure, and a hinged drive link connected to the flap panel and to a second fixed structure, the set of moving hinged links being linked to the flap panel by at least one linkage point in order to pivot jointly the moving hinged links deploying the flap panels in an initially predominantly rectilinear and subsequently deflected trajectory and at the same time aligned with a longitudinal direction of the aircraft, without the use of tracks and rollers, the hinged drive link being pivoted from the movement of the flap panels by the set of moving hinged links.

Abstract: A counterbalance mechanism for counterbalancing weight of a bottom-hinged door (such as a clamshell-type airstair door of an aircraft) includes an operator handle, a hoist rod pivotally connected at one end to the operator handle and at an opposite end thereof to the door near a bottom region thereof. A force accumulator assembly is provided which includes a force biasing member which accumulates and dissipates a bias force when opening and closing the door, respectively, to provide mechanical counterbalance to the weight of the door. A bellcrank assembly operatively connects the operator handle to the force accumulator. In such a manner, weight counterbalancing of the door is achieved.

Abstract: A counterbalance mechanism for counterbalancing weight of a bottom-hinged door (such as a clamshell-type airstair door of an aircraft) includes an operator handle, a hoist rod pivotally connected at one end to the operator handle and at an opposite end thereof to the door near a bottom region thereof. A force accumulator assembly is provided which includes a force biasing member which accumulates and dissipates a bias force when opening and closing the door, respectively, to provide mechanical counterbalance to the weight of the door. A bellcrank assembly operatively connects the operator handle to the force accumulator. In such a manner, weight counterbalancing of the door is achieved.