Abstract: A shaft assembly includes a composite tube and an impact shield. The composite tube has a longitudinal centerline axis and the impact shield may be disposed around the composite tube and may extend along a length of the composite tube. A gap may be defined between the composite tube and the impact shield. Generally, shaft assembly is configured to inhibit impact damage to the composite tube and/or facilitate visual detection of damage from impacts. The shaft assembly may further include a shock absorbing sleeve disposed in the gap between the composite tube and the impact shield.

Abstract: A shaft assembly includes a composite tube and an impact shield. The composite tube has a longitudinal centerline axis and the impact shield may be disposed around the composite tube and may extend along a length of the composite tube. A gap may be defined between the composite tube and the impact shield. Generally, shaft assembly is configured to inhibit impact damage to the composite tube and/or facilitate visual detection of damage from impacts. The shaft assembly may further include a shock absorbing sleeve disposed in the gap between the composite tube and the impact shield.

Abstract: A metallic-composite joint fitting is provided. The fitting may comprise a composite structure, an integral bearing comprising a first frustoconical portion and a second frustoconical portion each having a complimentary shape to the composite structure, a sleeve comprising a third frustoconical portion coupled to a cylindrical bearing surface of the integral bearing, and a metallic end fitting coupled to the third frustoconical portion, wherein the metallic end fitting comprises a bearing portion contacted with the cylindrical bearing surface.

Abstract: A tube arrangement includes a composite tube defining a centerline axis, wherein the composite tube comprises a proximal surface and a distal surface, and an end fitting comprising a first end disposed within the composite tube and a second end extending from the composite tube, wherein an outer surface of the end fitting defines a flared portion defining a terminus of the first end, a lobe portion disposed axially from the flared portion, and a terminating portion disposed axially from the lobe portion, the proximal surface conforms to a geometry of the outer surface of the end fitting, the lobe portion and the flared portion mechanically lock the end fitting to the composite tube to mitigate movement of the end fitting relative to the composite tube.

Abstract: A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing having a bore, a conical sleeve configured to be disposed about the frustoconical internal bearing, a composite structure configured to couple between the frustoconical internal bearing and the conical sleeve, a metallic end fitting configured to be disposed within the bore and couple to the frustoconical internal bearing, and an external nut configured to couple to the metallic end fitting and the conical sleeve, wherein at least one of the frustoconical internal bearing or the conical sleeve comprises a flanged portion mutually configured to couple the conical sleeve to the frustoconical internal bearing via a locking ring.

Abstract: A shaft assembly includes a composite tube and an impact shield. The composite tube has a longitudinal centerline axis and the impact shield may be disposed around the composite tube and may extend along a length of the composite tube. A gap may be defined between the composite tube and the impact shield. Generally, shaft assembly is configured to inhibit impact damage to the composite tube and/or facilitate visual detection of damage from impacts. The shaft assembly may further include a shock absorbing sleeve disposed in the gap between the composite tube and the impact shield.

Abstract: An additively manufactured component for a landing gear assembly may comprise a lug and a lubrication channel extending through the lug. The lubrication channel may comprise an inlet and an outlet. The outlet may be located at a pin orifice defined by the lug. A center axis of a first portion of the lubrication channel may be oriented at an angle relative to a center axis of a second portion of the lubrication channel.

Abstract: 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.

Abstract: A tube arrangement includes a composite tube defining a centerline axis, wherein the composite tube comprises a proximal surface and a distal surface, and an end fitting comprising a first end disposed within the composite tube and a second end extending from the composite tube, wherein an outer surface of the end fitting defines a flared portion defining a terminus of the first end, a lobe portion disposed axially from the flared portion, and a terminating portion disposed axially from the lobe portion, the proximal surface conforms to a geometry of the outer surface of the end fitting, the lobe portion and the flared portion mechanically lock the end fitting to the composite tube to mitigate movement of the end fitting relative to the composite tube.

Abstract: There is provided a system for predicting loading of a landing gear including, a plurality sensors positioned proximate to the landing gear. The plurality of sensors measure strain applied to the landing gear, and each sensor yielding strain data. The system further includes a processor that receives the strain data from the plurality of sensors and predicts at least one ground load based on strain data. There is further provided a method for predicting loading of a landing gear. The method includes powering a plurality of sensors located proximate to a landing gear structure, interrogating the plurality of sensors via data acquisition circuitry to yield strain data, instructing the data acquisition circuitry as to a sampling rate and data resolution to be used for the interrogating, and, finally, processing the strain data to predict a ground load.

Abstract: A hybrid metallic/composite structural component may comprise a metallic inner tube, a first lobe extending from the metallic inner tube, and a composite outer tube surrounding the metallic inner tube and the lobe, wherein a first end of the metallic inner tube extends from the composite outer tube and a second end of the metallic inner tube extends from the composite outer tube.

Abstract: An additively manufactured component for a landing gear assembly may comprise a lug and a lubrication channel extending through the lug. The lubrication channel may comprise an inlet and an outlet. The outlet may be located at a pin orifice defined by the lug. A center axis of a first portion of the lubrication channel may be oriented at an angle relative to a center axis of a second portion of the lubrication channel.

Abstract: 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.

Abstract: A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing having a bore, a conical sleeve configured to be disposed about the frustoconical internal bearing, a composite structure configured to couple between the frustoconical internal bearing and the conical sleeve, a metallic end fitting configured to be disposed within the bore and couple to the frustoconical internal bearing, and an external nut configured to couple to the metallic end fitting and the conical sleeve, wherein at least one of the frustoconical internal bearing or the conical sleeve comprises a flanged portion mutually configured to couple the conical sleeve to the frustoconical internal bearing via a locking ring.

Abstract: A metallic-composite joint fitting is provided. The fitting may comprise a composite structure, an integral bearing comprising a first frustoconical portion and a second frustoconical portion each having a complimentary shape to the composite structure, a sleeve comprising a third frustoconical portion coupled to a cylindrical bearing surface of the integral bearing, and a metallic end fitting coupled to the third frustoconical portion, wherein the metallic end fitting comprises a bearing portion contacted with the cylindrical bearing surface.

Abstract: A hybrid metallic/composite structural component may comprise a metallic inner tube, a first lobe extending from the metallic inner tube, and a composite outer tube surrounding the metallic inner tube and the lobe, wherein a first end of the metallic inner tube extends from the composite outer tube and a second end of the metallic inner tube extends from the composite outer tube.

Abstract: A metallic-composite joint fitting is provided. The fitting may comprise a frustoconical internal bearing, an internal bolt coupled within a bore of the frustoconical internal bearing, a metallic end fitting coupled to the internal bolt, wherein the metallic end fitting comprises a bearing portion disposed within the bore, a conical sleeve disposed about the frustoconical internal bearing, and an external nut coupled to the metallic end fitting and the conical sleeve.

Abstract: A rod end of an actuator assembly is disclosed. The rod end may comprise a rod piston end having an outer profile, and a rod joint end opposite the rod piston end, wherein the outer profile comprises an elliptical shape comprising a major diameter and a minor diameter, wherein the major diameter may be larger than the minor diameter in length.

Abstract: There is provided a system for predicting loading of a landing gear including, a plurality sensors positioned proximate to the landing gear. The plurality of sensors measure strain applied to the landing gear, and each sensor yielding strain data. The system further includes a processor that receives the strain data from the plurality of sensors and predicts at least one ground load based on strain data. There is further provided a method for predicting loading of a landing gear. The method includes powering a plurality of sensors located proximate to a landing gear structure, interrogating the plurality of sensors via data acquisition circuitry to yield strain data, instructing the data acquisition circuitry as to a sampling rate and data resolution to be used for the interrogating, and, finally, processing the strain data to predict a ground load.

Abstract: A rod end of an actuator assembly is disclosed. The rod end may comprise a rod piston end having an outer profile, and a rod joint end opposite the rod piston end, wherein the outer profile comprises an elliptical shape comprising a major diameter and a minor diameter, wherein the major diameter may be larger than the minor diameter in length.