Abstract: An arrangement for landing gear comprises a piston, a bogie beam and forward and rear brake rods. The piston has an attachment portion with a pivot connection for the bogie beam at its lower end. The bogie beam is mounted to the attachment portion at the pivot connection. The bogie beam supports forward and rear brake assemblies on forward and rear sides of the piston. The forward brake rod is connected to the forward brake assembly at a location for acting under tension during braking and the rear brake rod is connected to the rear brake assembly at a location for acting under tension during braking. The rear end of the forward brake rod is connected to the attachment portion forward of the pivot connection of the bogie beam, and a forward end of the rear brake rod is connected to the attachment portion.

Abstract: A composite metallic joint assembly may include a composite metal rod having a metal liner and a composite material disposed around the metal liner. A first portion of the composite metal rod may comprise the composite material and the metal liner and a second portion of the composite metal rod may comprise the metal liner exposed at a radially outer surface of the composite metal rod. The metal liner may have a first radial thickness at a first axial position corresponding to the first portion of the composite metal rod and a second radial thickness at a second axial position corresponding to the second portion of the composite metal rod. The second thickness may be greater than the first thickness.

Abstract: Systems and methods for landing gear arrangements are provided. In various embodiments, a landing gear arrangement may comprise a first composite layer, the first composite layer having a cylindrical geometry, a metallic ring comprising an inner surface and an outer surface, the metallic ring perimetrically surrounding at least a portion of the first composite layer, the inner surface being in contact with the first composite layer, a metallic connecting tab extending away from the outer surface, and a second composite layer at least partially perimetrically surrounding the metallic ring and at least partially perimetrically surrounding the first composite layer, the outer surface being in contact with the second composite layer.

Abstract: A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag.

Abstract: Composite tubes comprising a compression sleeve coupled to an inner surface of a composite tube, a carbon extrusion member disposed within the composite tube, and an end fitting comprising a locking feature, wherein the end fitting is coupled to an inner surface of the compression sleeve and the locking feature is configured to engage the carbon extrusion member are disclosed. Methods comprising coupling a compression sleeve to an inner surface of a distal end of a composite tube, placing a carbon extrusion member inside the compression sleeve and the composite tube, and disposing an end fitting on the distal end of the composite tube, wherein the end fitting comprises a locking feature configured to interact with the carbon extrusion member are also disclosed.

Abstract: A method of manufacture may comprise disposing a locking collar nut at least partially around a composite tube, wherein the composite tube comprises a variable diameter portion comprising a first frustoconical portion and a second frustoconical portion, wherein a diameter of the composite tube at an interface between the first frustoconical portion and the second frustoconical portion is a maximum diameter value with respect to the first frustoconical portion and is a maximum diameter value with respect to the second frustoconical portion, disposing a locking wedge at least partially around the first frustoconical portion, disposing an end fitting at least partially around the second frustoconical portion, and coupling the locking collar nut with the end fitting, wherein the locking collar nut circumferentially surrounds the locking wedge disposed around the first frustoconical portion.

Abstract: A composite tube assembly may comprise a composite tube comprising a variable diameter portion comprising a first frustoconical portion and a second frustoconical portion, wherein a diameter of the composite tube at an interface between the first frustoconical portion and the second frustoconical portion is a maximum diameter value with respect to the first frustoconical portion and is a maximum diameter value with respect to the second frustoconical portion, a locking wedge disposed at least partially around a circumference of the first frustoconical portion, a locking collar nut disposed at least partially around a circumference of the locking wedge, and an end fitting disposed at least partially around a circumference of the second frustoconical portion, wherein the end fitting is coupled to the locking collar nut, wherein the first frustoconical portion and the second frustoconical portion comprise a metallic insert.

Abstract: A composite tube assembly may comprise a composite tube comprising a radially outer surface having a variable diameter portion comprising a first frustoconical portion and a second frustoconical portion, a locking wedge disposed at least partially around a circumference of the first frustoconical portion, a locking collar nut disposed at least partially around a circumference of the locking wedge, and an end fitting disposed at least partially around a circumference of the second frustoconical portion, wherein the end fitting is coupled to the locking collar nut. A diameter of the composite tube, at an interface between the first frustoconical portion and the second frustoconical portion, may be a maximum diameter value with respect to the first frustoconical portion and may be a maximum diameter value with respect to the second frustoconical portion.

Abstract: A noise abatement system for an aircraft landing gear is provided. The system may have a retention member and a covering member. In this regard, the system may be configured to block the airflow through a structural void to abate noise. Moreover, the system may be shaped to diminish aerodynamic drag.

Abstract: Composite tube assemblies comprising a composite tube comprising a distal end having a first conical section and a second conical section, wherein a distal end of the first conical section is in contact with a proximal end of the second conical section having the same outer diameter as the distal end of the first conical section, wherein a proximal end of the first conical section and a distal end of the second conical section have a smaller outer diameter than the distal end of the first conical section, a locking ring disposed around the first conical section, an end fitting disposed around the second conical section, wherein the end fitting is coupled to the locking ring, and a retaining ring circumferentially disposed around the locking ring are disclosed.

Abstract: The present disclosure describes composite actuator piston rods and methods for making such rods. Composite actuator piston rods of the present disclosure may include a flared end and an embedded nut positioned within the flared end. A rod end assembly may be secured to the embedded nut. The rod end assembly may include a rod attachment end with a threaded surface configured to engage the embedded nut and a edge configured to compress a portion fo the flared end. The rod end assembly may also include an external nut proximate to the wedge nad configured to exert a force against the wedge.

Abstract: Composite tube assemblies comprising a composite tube comprising a distal end having a first conical section and a second conical section, wherein a distal end of the first conical section is in contact with a proximal end of the second conical section having the same outer diameter as the distal end of the first conical section, wherein a proximal end of the first conical section and a distal end of the second conical section have a smaller outer diameter than the distal end of the first conical section, a locking ring disposed around the first conical section, an end fitting disposed around the second conical section, wherein the end fitting is coupled to the locking ring, and a retaining ring circumferentially disposed around the locking ring are provide.

Abstract: Composite tubes comprising a compression sleeve coupled to an inner surface of a composite tube, a carbon extrusion member disposed within the composite tube, and an end fitting comprising a locking feature, wherein the end fitting is coupled to an inner surface of the compression sleeve and the locking feature is configured to engage the carbon extrusion member are disclosed. Methods comprising coupling a compression sleeve to an inner surface of a distal end of a composite tube, placing a carbon extrusion member inside the compression sleeve and the composite tube, and disposing an end fitting on the distal end of the composite tube, wherein the end fitting comprises a locking feature configured to interact with the carbon extrusion member are also disclosed.

Abstract: Composite tube assemblies comprising a composite tube comprising a distal end having a first conical section and a second conical section, wherein a distal end of the first conical section is in contact with a proximal end of the second conical section having the same outer diameter as the distal end of the first conical section, wherein a proximal end of the first conical section and a distal end of the second conical section have a smaller outer diameter than the distal end of the first conical section, a locking ring disposed around the first conical section, an end fitting disposed around the second conical section, wherein the end fitting is coupled to the locking ring, and a retaining ring circumferentially disposed around the locking ring are disclosed.