A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes an upper cam fastened to the piston and a lower cam fastened to the cylinder. The system further includes a brace configured to be coupled to the shock strut to lock the landing gear in a deployed position, and to fold towards the shock strut during retraction of the landing gear. The system further includes a collar coupled to the brace and the piston and configured to rotate relative to the cylinder in response to folding of the brace such that rotation of the collar rotates the piston and the upper cam relative to the lower cam, the rotation of the upper cam relative to the lower cam forcing the piston towards the aircraft attachment within the cylinder.

A thin-skin support member is provided. The thin-skin support member may include a semi-circular edge and a flat edge that define a hollow cavity. A cylindrical cavity may be adjacent the hollow cavity and at least partially defined by the semi-circular edge. The cylindrical cavity may be configured to retain a strut assembly. A mounting interface may be coupled to the semi-circular edge and the flat edge. A torsion interface may be disposed adjacent the cylindrical cavity and configured to receive a torsion link. The thin-skin support member may be made using additive manufacturing and thus may have a grain structure grown in the direction of material being added.

A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes a collar coupled to a brace linkage and the piston, a torque arm configured to resist rotation between the collar and the piston, and a shrink linkage coupled between the torque arm and the cylinder. The collar rotates relative to the cylinder in response to retraction of the landing gear. Rotation of the collar rotates the piston and the torque arm relative to the cylinder. The rotation of the collar relative to the cylinder forces, via the shrink linkage, the piston towards the aircraft attachment within the cylinder.

An aircraft landing gear includes a shock strut with a rod slidably received within a cylinder. A beam is rotatably mounted to the rod, and wheels are mounted to the beam. The landing gear further includes a link assembly with an upper link and a lower link. The upper link has a first end rotatably connected to the cylinder, and the lower link has a first end rotatably connected to the beam. The second ends of the upper and lower links are rotatably coupled to each other by a limiter joint. The limiter joint includes a first stop associated the upper link and a second stop associated with the lower link. The stops are configured such that the first stop engages the second stop to limit rotation of the upper link relative to the lower link.

An aircraft landing gear assembly having a main strut pivotally coupled to an aircraft, a bogie beam pivotally connected to the main strut, a first axle mounted at the first end of the bogie beam and arranged to carry one or more first wheel assemblies and brake assemblies, each first brake assembly being attached to the bogie beam by a brake rod, and a second axle mounted at a second end of the bogie beam and arranged to carry one or more second wheel assemblies and brake assemblies. A double acting actuator is coupled between the strut and the bogie beam to apply a compressive or tensile force to the bogie beam. The ends of the bogie beam are arranged to position the bogie pivot axis below a plane intersecting the axes of rotation of the first and second wheel assemblies when the strut is in the deployed condition.

A thin-skin support member is provided. The thin-skin support member may include a semi-circular edge and a flat edge that define a hollow cavity. A cylindrical cavity may be adjacent the hollow cavity and at least partially defined by the semi-circular edge. The cylindrical cavity may be configured to retain a strut assembly. A mounting interface may be coupled to the semi-circular edge and the flat edge. A torsion interface may be disposed adjacent the cylindrical cavity and configured to receive a torsion link. The thin-skin support member may be made using additive manufacturing and thus may have a grain structure grown in the direction of material being added.

A system for shrinking landing gear includes a shock strut having a cylinder and a piston to be received by the cylinder. The system further includes an upper cam fastened to the piston and a lower cam fastened to the cylinder. The system further includes a brace configured to be coupled to the shock strut to lock the landing gear in a deployed position, and to fold towards the shock strut during retraction of the landing gear. The system further includes a collar coupled to the brace and the piston and configured to rotate relative to the cylinder in response to folding of the brace such that rotation of the collar rotates the piston and the upper cam relative to the lower cam, the rotation of the upper cam relative to the lower cam forcing the piston towards the aircraft attachment within the cylinder.

A torque link assembly may comprise an upper torque link, a lower torque link, and a torque link pin. The upper torque link may define an upper hydraulic fluid channel. The lower torque link may define a lower hydraulic fluid channel. The torque link pin may fluidly couple the upper hydraulic fluid channel to the lower hydraulic fluid channel.

A non jamming shrink latch is provided and may comprise a cradle, a first rocker arm, a first inboard pivot, and a first outboard pivot, wherein the first inboard pivot is coupled to the first rocker arm at a first end and the first outboard pivot is coupled to the first rocker arm at a second end opposite the first end, and wherein the cradle is coupled to the first outboard pivot. In various embodiments, a non jamming shrink latch may further comprise a second rocker arm coupled to the cradle at a second outboard pivot and a second inboard pivot coupled to the second rocker arm opposite the second outboard pivot.

A bracket manifold for a landing gear assembly is disclosed. In various embodiments, the bracket manifold includes a mounting plate having a central portion and a first wing portion extending from the central portion; and a first manifold section integrated monolithically into at least one of the central portion and the first wing portion of the mounting plate.