The Boeing Company

Theboeing Company

Mitchell L R Mellor

Jonathan B Wallace

Gary M Lindahl

David Ansyl Eckols

Brian P Salsbery

A levered landing gear including a first shock strut having and a second shock strut disposed concentrically with the first shock strut. The second shock strut includes a metering pin coupled to a mounting surface of a piston of the second shock strut, and an orifice plate that cooperates with the metering pin to meter an amount of fluid flow as the second shock strut is compressed. The metering pin includes flutes longitudinally arranged on the metering pin between first and second ends of the metering pin, the flutes having a varying depth so that a fluid flow through the flutes is greater at the second end than fluid flow through the flutes at the first end. A truck lever is coupled to both the first shock strut and the second shock strut such that the second shock strut pivots the truck lever relative to the first shock strut.

Levered landing gear with inner shock strut

A 3D-printed aluminum fuel fitting solution demonstrates higher performance at a potentially lower cost and shorter lead time. The resulting geometry also produced 30% weight savings leaving all interfaces intact.

Enhanced fluid deflection angle structures and methods for manufacturing

A levered landing gear including a first shock strut having a first end and a second end, a truck lever pivotally coupled to the second end of the first shock strut, and a second shock strut disposed between the second end of the first shock strut and the truck lever, where the second shock strut has a first end and a second end, the first end of the second shock strut being coupled to the second end of the first shock strut and the second end of the second shock strut being coupled to the truck lever.

Hydraulic manifold for semi-levered gear actuator

An example aircraft includes (i) a landing gear having a chassis, an axle, and wheels mounted to ends of the axle; (ii) a hydraulic actuator including a cylinder, a first piston coupled to the chassis, and a second piston coupled to the axle; and (iii) a directional control valve including: inlet ports configured to be fluidly coupled to a source of pressurized fluid, tank ports configured to be fluidly coupled to a tank, and workports configured to be fluidly coupled to the hydraulic actuator.

Aircraft landing gear steering systems and methods with enhanced shimmy protection

Flow passage contours for a hydraulic manifold for actuator control with dual solenoids

Hydraulic manifold for actuator control with dual solenoids

Mounting pads for a routing box on a hydraulic manifold for actuator control with dual solenoids

Return boss for a hydraulic manifold for actuator control with dual solenoids

Supply boss for a hydraulic manifold for actuator control with dual solenoids

Supply port boss and return port boss for a hydraulic manifold for actuator control with dual solenoids

A levered landing gear including a first shock strut having a longitudinal axis, a second shock strut disposed concentrically with the first shock strut along the longitudinal axis such that the first shock strut and the second shock strut extend along a common extension axis, and a truck lever coupled to both the first shock strut and the second shock strut such that the second shock strut pivots the truck lever relative to the first shock strut.

An apparatus and method according to one or more embodiments are provided for a latching mechanism. The latching mechanism may be implemented, for example, as a positive lock latching mechanism that provides a positive indication when a latch is not engaged. In one example, an apparatus includes a latch arm comprising a slotted hole and a latch hook configured to engage a pin. The latch includes a bifold handle coupled to the latch arm, the bifold handle comprising a first handle portion and a handle extension portion, wherein the first handle portion comprises a lock hook configured to translate through the slotted hole to engage the pin and the handle extension portion is configured to move away from the first handle portion when the lock hook is not engaged with the pin. Additional systems and methods are also provided.

Positive lock latching mechanism

A system includes an aircraft having a fuselage with a tail portion. A tail skid is disposed in an opening of the tail portion. The tail skid includes a ground contact shoe and a mechanism configured to selectably move the ground contact shoe between respective ones of a stow position disposed within the opening, a landing position disposed below the opening, and a takeoff position different than the stow and landing positions. Before a takeoff or a landing, the ground contact shoe is moved to a corresponding one of the takeoff or landing positions. In the event of an over-rotation or an over-flaring of the aircraft during a takeoff or a landing, respectively, the ground contact shoe makes contact with the ground and a shock absorber of the system absorbs a shock of the contact and thereby prevents tail strike damage to the aircraft.

Growing community of inventors

Bothell, WA, United States of America

Mitchell L R Mellor