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AssigneeMessier-Dowty Limited
InventorsMaud Courtois, Dominique Ducos
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The invention relates to an aircraft landing gear having a retractable leg, in which the leg comprises a strut with a telescopic rod, the strut being hinged to a structure of the aircraft in order to pivot between a gear-up position and a gear-down position, said strut also being connected to the structure of the aircraft via hinged brace elements. According to an essential aspect of the invention, the landing gear includes an independent low-noise fairing system that serves, when the leg is in the gear-down position, to cover the front of at least a portion of the hinge between the brace elements, said low-noise fairing system comprising a hinged fairing of two complementary portions connected to each other via a hinge whose axis is parallel to the axis of the corresponding hinge portion of said brace elements.
1/ Aircraft landing gear having a retractable leg, in which the leg comprises a strut with a telescopic rod, the strut being hinged to a structure of the aircraft in order to pivot between a gear-up position and a gear-down position under drive from an associated actuator, said strut also being connected to the structure of the aircraft via hinged brace elements, the landing gear including an independent low-noise fairing system that serves, when the leg is in the gear-down position, to cover the front of at least a portion of the hinge between the brace elements, said low-noise fairing system comprising a hinged fairing of two complementary portions connected to each other via a hinge whose axis is parallel to the axis of the corresponding hinge portion of said brace elements.
2/ Landing gear according to claim 1, in which the brace elements comprise a main brace having a top arm hinged to the structure of the aircraft and a bottom arm hinged to an appendix associated with the strut of the landing gear leg, wherein the hinged fairing of the independent low-noise fairing system acts in the gear-down position to cover the front of the hinged zone between the top and bottom arms of the main brace.
3/ Landing gear according to claim 2, wherein the hinged fairing comprises two complementary portions, in which a first portion is rigidly secured to the bottom arm of the main brace, and a second portion is connected via a connecting rod to the top arm of said brace, the four hinges concerned being arranged to form a hinged parallelogram.
4/ Landing gear according to claim 3, wherein, in the gear-down position, the first portion of the hinged fairing covers the bottom portion of the bottom arm of the main brace, the top portion of said bottom arm and the bottom portion of the top arm of said brace being covered by the second portion of said hinged fairing.
5/ Landing gear according to claim 4, wherein, in the gear-down position, the first portion of the hinged fairing terminates in a raised edge covering part of the hinged zone of the bottom arm of the main brace, the other part of said hinged zone being covered by a rigid fairing associated with the strut of the landing gear leg and also forming part of the independent low-noise fairing system.
6/ Landing gear according to claim 4, wherein the second portion of the hinged fairing has a central bulge which, in the gear-down position, covers the hinge between the two arms of the main brace.
7/ Landing gear according to claim 6, wherein the second portion of the hinged fairing presents longitudinal stiffeners on its inside for stiffening at least the central bulge zone.
8/ Landing gear according to claim 3, wherein the connecting rod is hinged between an end point of the second portion of the hinged fairing, and an associated fitting fixed to the top arm of the main brace at a point that completes the hinged parallelogram.
9/ Landing gear according to claim 8, wherein the connecting rod pivots about its hinge on the fitting connecting it to the top arm, and about its point connected to the second portion of the hinged fairing through a range of about 150° between the two positions of said connecting rod corresponding to the up and down positions of the landing gear leg.
10/ Landing gear according to claim 8, wherein the connecting rod is adjustable in length or is a resilient rod including a spring.
11/ Landing gear according to claim 1, wherein, in the gear-down position, the two complementary portions of the hinged fairing lie substantially in line one with the other.