Goodrich Corporation

James Acks

Dennis Wayne Martin

Korey Michael Reber

Dennis W Martin

Gary Holloway

Ronald Kucera

Samuel J Reiss

A landing gear system for an aircraft is disclosed. In various embodiments, the system includes a truss frame pivotally connected to a frame of the aircraft and configured to rotate about an axis; a retraction actuator configured to rotate the truss frame about the axis; a first truss link pivotally connected to the truss frame; a second truss link pivotally connected to the first truss link; a truss locking link pivotally connected to the truss frame and to the second truss link; and an articulation actuator configured to pivot the first truss link with respect to the truss frame.

Articulating truss configuration for aircraft landing gear

A wheel retaining assembly for a landing gear having an axle and an outer wheel bearing, the axle defining an axial direction along an axial centerline, is disclosed. In various embodiments, the wheel retaining assembly includes a first wheel spacer configured to slide over the axle and to abut the outer wheel bearing, the first wheel spacer having an axially outward portion; and a second wheel spacer configured to slide over the axle, the second wheel spacer having an axially inward portion configured to engage the axially outward portion of the first wheel spacer.

Landing gear wheel retention device

A nose-wheel steering system is disclosed. In various embodiments, the system includes an actuator; a strut; and a gearing mechanism operably coupling the actuator to the strut, the gearing mechanism including a steering collar attached to the strut, and idler gear engaged with the actuator and a pinion having a first gear engaged with the idler gear and a second gear engaged with the steering collar.

Nose wheel steering system

A steering system may include a gear assembly and a collar. The gear assembly may include a planet carrier, a planet gear, an internal ring gear, and a sun gear. The planet gear may be disposed between the internal ring gear and the sun gear. The gear assembly may provide a mechanical advantage to the steering system, which may result in a greater powered steering range, a shorter rack assembly, and/or increased design space relative to typical steering systems.

Nose wheel steering systems and methods

A locking actuator arrangement may comprise an actuator housing defining a retaining cavity, an actuator piston comprising a piston head and a piston rod extending from the piston head, a receptacle body defining a receiving cavity, wherein the receiving cavity is configured to receive at least a portion of the piston rod, and the piston rod is configured to be received by the receiving cavity in response to alignment of at least two coupled links.

Landing gear folding brace with locking actuator

In various embodiments, a two stage shock strut for use in a landing gear assembly may comprise a first cylinder, a fill port, a first stage piston head, a second cylinder, a second stage piston head, and a bleed tube. The first cylinder may define a first volume. The fill port valve may be in fluid communication with the first cylinder and configured to receive hydraulic fluid. The first stage piston head may be in fluid communication with the first volume. The second cylinder may comprise a metering pin. The metering pin may be in fluid communication with the first volume and a second volume defined by the second cylinder. The metering pin may be configured to receive the hydraulic fluid from the first volume and purge gas from the second volume. The second stage piston head may be in fluid communication with the second volume.

Dual stage shock strut with removable second stage fluid chamber

A landing gear system comprises a bogie beam, a landing gear axle pivotally mounted to the bogie beam, a steering rack, a linear actuator assembly, and a steering control link. The steering rack is secured transversely to the bogie beam and is longitudinally spaced apart from the landing gear axle. The linear actuator assembly is operable to laterally translate the steering rack. The steering control link is longitudinally extendable and has an actuator end secured to the steering rack, and an axle end of the steering control link engaged with the landing gear axle. The steering control link and the landing gear axle are pivotable relative to the bogie beam about a common axis.

Main landing gear compact axle steering

A side articulating main landing gear assembly for an aircraft which includes a wheel axle fitting oriented in a horizontal plane when the landing gear assembly is in an extended condition deployed from a landing gear bay of the aircraft, a shock absorber adapted to stroke between an extended state and a compressed state upon landing the aircraft, a first linkage for maintaining a tire supported on the wheel axle fitting in a substantially vertical plane as the shock absorber strokes between the extended state and the compressed state, and a second linkage for maintaining the wheel axle fitting in the horizontal plane as the shock absorber strokes between the extended state and the compressed state. The first and second linkages are adapted and configured to minimize lateral tire scuffing during shock absorber stroking.

Vertically retracting side articulating landing gear for aircraft

A bogie beam sensor may include a bracket and a target arm pivotably coupled to the bracket. The bracket may be coupled to a bogie beam. A sensor may be coupled to the bracket, and a target may be coupled to the target arm. A drive link may be coupled to the target arm and a piston. In response to the bogie beam pivoting with respect to the piston, the drive link may cause the target arm to rotate with respect to the bogie beam. The sensor may detect movement of the target on the target arm, and an angular position of the bogie beam may be determined based on the position of the target.

Bogie beam angle sensor

A bias steered landing gear system comprises a bogie beam, a first landing gear axle pivotally mounted to the bogie beam, and a steering actuator assembly. The first landing gear axle is pivotable through an axle steering range which includes a maximum inboard steering angle and a maximum outboard steering angle. The steering actuator assembly is operable to apply a steering force to steer the first landing gear axle through the axle steering range between the maximum inboard steering angle and the maximum outboard steering angle. The maximum inboard steering angle is substantially larger than the maximum outboard steering angle.

Main landing gear bias axle steering

An indicator assembly for an aircraft landing gear for providing indication of a hard landing. The indicator assembly including a actuator member movable when the pressure on a shock strut of the aircraft landing gear exceeds a desired load and stroke threshold indicative of a hard landing. A shear pin is coupled to the actuator member which is configured to shear when a desired level of force is applied to at least a portion of the shear pin. A visibly recognizable indictor is moved from a non-indicating position to an indicating position upon shearing of the shear pin.

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Medina, OH, United States of America

James Acks