Aircraft Landing Gear Steering Systems and Methods with Enhanced Shimmy Protection

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. 1. A hydraulic system comprising:a hydraulic actuator comprising: (i) a cylinder, (ii) a partition disposed in the cylinder and configured to divide the cylinder into a first partition and a second partition, (iii) a first piston slidably accommodated in the first partition and having a piston head and a rod extending from the piston head along a longitudinal axis of the cylinder, wherein the rod is configured to be coupled to a chassis of a landing gear of an aircraft, and wherein the piston head divides the first partition into a first chamber and a second chamber, and (iv) a second piston slidably accommodated in the second partition and having a respective piston head and a respective rod extending from the respective piston head along the longitudinal axis of the cylinder, wherein the respective rod is configured to be coupled to an axle of the landing gear of the aircraft, and wherein the respective piston head divides the second partition into a third chamber and a fourth chamber; anda directional control valve comprising: (i) a first inlet port configured to be fluidly coupled to a source of pressurized fluid, (ii) a second inlet port configured to be fluidly coupled to the source of pressurized fluid, (iii) a first tank port configured to be fluidly coupled to a tank, (iv) a second tank port configured to be fluidly coupled to the tank, (v) a first workport configured to be fluidly coupled to the first chamber, (vi) a second workport configured to be fluidly coupled ...

THREE-POSITION AIRCRAFT TAIL SKID MECHANISM AND METHOD OF ACTUATION

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. 1. A system , comprising:an aircraft having a fuselage with a tail portion; and 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., 'a tail skid disposed in an opening of the tail portion, the tail skid comprising2. The system of claim 1 , wherein the mechanism comprises:first and second attach pins respectively pinioned within a structure of the aircraft for rotation relative thereto;a linkage comprising two pairs of links coupled between the first and second attach pins and defining a node at a middle of the linkage; andan actuating device configured to selectably rotate respective ones of the first and second attach pins in such a way as to move the node between positions respectively corresponding to the stow, landing and takeoff positions.3. The system of claim 2 , wherein the linkage comprises:first and second vertical links, each having opposite ends, whereinan upper end of the upper vertical link is ...

ENHANCED FLUID DEFLECTION ANGLE STRUCTURES AND METHODS FOR MANUFACTURING

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. 1. A method for manufacturing a redundant wall fluid deflection fitting , the method comprising:loading a build file into a Selective Laser Melting (SLM) additive manufacturing machine, the build file including instructions to cause a hardware processor in the SLM additive manufacturing machine to print the redundant wall fluid deflection fitting on a build plate in accordance with the build file instructions; an outer wall;', 'an inner wall; and', 'a drain tube interface between the inner wall and the outer wall and comprising one or more drain tubes;, 'additively printing a first flange comprisingadditively printing the outer wall, the inner wall, and the one or more drain tubes continuously through a first bend to a substantially straight portion to a second bend; the outer wall;', 'the inner wall; and, 'additively printing a second flange comprising;'}the drain tube interface between the inner wall and the outer wall and comprising the one or more drain tubes and wherein the first flange and the second flange are oriented at an angle substantially defined by the radii of curvature of the first bend and the second bend, and wherein the one or more drain tubes comprise substantially continuous curved tubes; andremoving the redundant wall fluid deflection fitting from the build plate.2. The method for manufacturing a redundant wall fluid deflection fitting of further comprising:additively printing one or more reinforcement gussets extending between an outer surface of the first flange and the outer wall.3. The method for manufacturing a redundant wall fluid deflection fitting of further comprising:additively printing one or more attachment lugs near the first flange.4. The method for manufacturing a redundant wall fluid deflection fitting of further ...

LEVERED LANDING GEAR WITH INNER SHOCK STRUT

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. 1. A levered landing gear comprising: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; anda 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.2. The levered landing gear of claim 1 , whereinthe first shock strut includes an outer cylinder and an inner cylinder at least partially disposed within the outer cylinder, the outer cylinder being configured for coupling with a vehicle frame and the inner cylinder extends and retracts relative to the outer cylinder.3. The levered landing gear of claim 2 , wherein the second shock strut is disposed at least partially within the inner cylinder.4. The levered landing gear of claim 2 , wherein the second shock strut includes a piston that reciprocates within the inner cylinder.5. The levered landing gear of claim 4 , further comprising a connecting link coupling the piston to the truck lever.6. The levered landing gear of claim 2 , wherein the inner cylinder includes an inner chamber claim 2 , the inner chamber being bifurcated into a first shock strut fluid compression chamber and a second shock strut fluid compression chamber claim 2 , where fluid within the first shock strut compression chamber extends the inner cylinder relative to the outer cylinder and fluid within the ...

Levered landing gear with inner shock strut

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.

POSITIVE LOCK LATCHING MECHANISM

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. 1. An apparatus comprising: a latch arm comprising a slotted hole and a latch hook configured to engage a pin; and', '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., 'a latch comprising2. The apparatus of claim 1 , wherein:the bifold handle comprises a first end of the first handle portion coupled to the latch arm and a second end of the first handle portion coupled to the handle extension portion; andthe handle extension portion is configured to move adjacent to the first handle portion when the lock hook is engaged with the pin.3. The apparatus of claim 1 , wherein the first handle portion comprises:a first spring mechanism configured to limit the travel of the lock hook;a second spring mechanism configured to apply a force to the handle extension portion to move the handle extension portion relative to the first ...

Aircraft landing gear steering systems and methods with enhanced shimmy protection

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.

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

Positive lock latching mechanism

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.

Levered landing gear with inner shock strut

A levered landing gear (110) including a first shock strut (200) having a longitudinal axis (LAX), a second shock strut (300) disposed concentrically with the first shock strut (200) along the longitudinal axis (LAX) such that the first shock strut (200) 5 and the second shock strut (300) extend along a common extension axis (EX), and a truck lever (220) coupled to both the first shock strut (200) and the second shock strut (300) such that the second shock strut (300) pivots the truck lever (220) relative to the first shock strut (200). .0 42 1/16 Or C6 (O 00 00 Or 0\ /0\ %%SNIPPET%%\ \ O L O \ / O O)

Levered landing gear with inner shock strut

A levered landing gear (110) including a first shock strut (200) having a longitudinal axis (LAX), a second shock strut (300) disposed concentrically with the first shock strut (200) along the longitudinal axis (LAX) such that the first shock strut (200) 5 and the second shock strut (300) extend along a common extension axis (EX), and a truck lever (220) coupled to both the first shock strut (200) and the second shock strut (300) such that the second shock strut (300) pivots the truck lever (220) relative to the first shock strut (200). r O0\ (O 0\ 00\ \ \ O L O \ / O O)

Levered landing gear with inner shock strut

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.

Trem de pouso alavancado com amortecedor de choque interno e método de utilização de um trem de pouso alavancado

A presente invenção refere-se a um trem de pouso alavancado incluindo um primeiro amortecedor de choque possuindo um eixo geométrico longitudinal, um segundo amortecedor de choque disposto concentricamente com o primeiro amortecedor de choque ao longo do eixo geométrico longitudinal de modo que o primeiro amortecedor de choque e o segundo amortecedor de choque se estendam ao longo de um eixo geométrico de extensão comum e uma alavanca de caminhão acoplada a ambos o primeiro amortecedor de choque e segundo amortecedor de choque de modo que o segundo amortecedor de choque articule a alavanca de caminhão com relação ao primeiro amortecedor de choque.

内部ショックストラットを有するレバー式降着装置

【課題】内部ショックストラットを有するレバー式降着装置を提供する。 【解決手段】レバー式降着装置であって、縦軸を有する第一ショックストラットと、第一ショックストラットおよび第二ショックストラットが共通延伸軸に沿って延伸するように、縦軸に沿って第一ショックストラットと同軸に設けられた第二ショックストラットと、第二ショックストラットが第一ショックストラットに対してトラックレバーを旋回させるように、第一ショックストラットおよび第二ショックストラットの両方に連結されたトラックレバーと、を含むレバー式降着装置。 【選択図】なし

trem de pouso alavancado com amortecedor de choque interno

a presente invenção refere-se a um trem de pouso alavancado incluindo um primeiro amortecedor de choque possuindo um eixo geométrico longitudinal, um segundo amortecedor de choque disposto concentricamente com o primeiro amortecedor de choque ao longo do eixo geométrico longitudinal de modo que o primeiro amortecedor de choque e o segundo amortecedor de choque se estendam ao longo de um eixo geométrico de extensão comum e uma alavanca de caminhão acoplada a ambos o primeiro amortecedor de choque e segundo amortecedor de choque de modo que o segundo amortecedor de choque articule a alavanca de caminhão com relação ao primeiro amortecedor de choque.

Levered landing gear with inner shock strut

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 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.