Interleaved wheel landing gear bogie beam

Abstract

A bogie beam for an aircraft landing gear assembly is provided. The bogie beam includes an elongated hub having a first end and a second end. The hub is rotatably mountable to a shock strut of the landing gear assembly. A first leg extends radially from the first end of the hub in a first direction. The first leg has an inner side facing the second end of the hub and is configured to have a first wheel rotatably mounted to the inner side of the first leg about a first wheel axis. A second leg extends radially from the second end of the hub in a second direction and has an inner side facing the first end of the hub. The second leg is configured to have a second wheel rotatably mounted to the inner side of the second leg about a second wheel axis.

Description

Background Technology

[0001] Aerodynamic and economic efficiency demands that aircraft components be as compact and lightweight as possible. For landing gear components, a compact landing gear system reduces the amount of space required in the landing gear bay to accommodate the retracted landing gear. Conventional twin-axle landing gear (such as that used on very narrow-body (aerodynamically efficient) transonic and supersonic commercial jet aircraft) typically requires a tandem bogie and two wheels to fit into the landing gear bay. Conventional single-axle, two-wheel-adjacent landing gear (such as that used on very narrow-body transonic commercial jet aircraft) is not well-suited for smaller civil aircraft requiring supercritical airfoils (supersonic flight) due to the reduced landing gear bay space. Therefore, a lightweight, compact landing gear system is needed that requires a reduced landing gear bay area. Summary of the Invention

[0002] The subject matter disclosed herein provides a truckbeam for a compact aircraft landing gear assembly. When viewed from above (or below), the truckbeam is typically shaped like a "Z", with a first leg and a second leg extending in opposite directions from a first end and a second end of a central hub, respectively. Each leg is configured to have a wheel rotatably mounted on its inner side (i.e., the side closer to the hub).

[0003] A representative embodiment of a bogie beam for an aircraft landing gear assembly includes an elongated hub having a first end and a second end. The hub is configured to be rotatably mounted to a shock-absorbing strut of the landing gear assembly about a mounting axis. A first leg extends radially from the first end of the hub in a first direction and has an inward side facing the second end of the hub. The first leg is configured to have a first wheel rotatably mounted to the inward side of the first leg about a first wheel axis. A second leg extends radially from the second end of the hub in a second direction and has an inward side facing the first end of the hub. The second leg is configured to have a second wheel rotatably mounted to the inward side of the second leg about a second wheel axis.

[0004] In any embodiment, the first direction is a forward direction, and the second direction is a backward direction.

[0005] In any embodiment, the first direction is parallel to the second direction.

[0006] In any embodiment, the axis of the first wheel and the axis of the second wheel are parallel.

[0007] In any embodiment, the mounting axis is parallel to at least one of the first wheel axis and the second wheel axis.

[0008] In any embodiment, the bogie beam also includes an interface configured to rotatably connect a pitchtrimmer to one of the first and second outriggers.

[0009] In any embodiment, the bogie beam further includes a first interface configured to rotatably connect a brake lever to one of a first outrigger and a second outrigger.

[0010] In any embodiment, the bogie beam further includes a second interface configured to rotatably connect the second brake lever to another of the first and second outriggers.

[0011] A representative embodiment of a landing gear assembly for an aircraft includes a vibration-absorbing strut coupled to the aircraft at one end; and a bogie beam. The bogie beam includes a hub rotatably coupled to an end of the vibration-absorbing strut about a first axis. The bogie beam also includes a first leg and a second leg. The first leg extends from a first end of the hub along a first direction and is configured to have a first wheel rotatably mounted thereto. The second leg extends from a second end of the hub along a second direction and is configured to have a second wheel rotatably mounted thereto, wherein the hub is positioned between the first leg and the second leg.

[0012] In any embodiment, the bogie beam further includes a first wheel rotatably mounted to the inside of a first outrigger, the inside of the first outrigger being close to the hub; and a second wheel rotatably mounted to the inside of a second outrigger, the inside of the second outrigger being close to the hub.

[0013] In any embodiment, each of the first leg and the second leg includes an inner side and an outer side, the inner side of the first leg and the second leg being positioned between the outer sides of the first leg and the second leg, wherein the first leg is configured such that the first wheel is rotatably mounted near the inner side of the first leg.

[0014] In any embodiment, the second leg is configured such that the second wheel is rotatably mounted near the inside of the second leg.

[0015] In any embodiment, the hub includes a lug extending radially from the outer surface of the hub, and the hub is rotatably coupled to a hook disposed on a vibration-absorbing strut.

[0016] In any embodiment, the hub includes a hook extending radially from the outer surface of the hub, the hook being rotatably coupled to a lug disposed on a vibration-absorbing strut.

[0017] This summary is provided to introduce, in a simplified form, selected concepts that will be further described in the detailed embodiments described below. This summary is not intended to identify key features of the claimed subject matter, nor is it intended to help determine the scope of the claimed subject matter. Attached Figure Description

[0018] The foregoing aspects and numerous accompanying advantages of this disclosure will become more readily understood, and equally better understood, by referring to the following detailed description, in conjunction with the accompanying drawings:

[0019] Figure 1 An isometric view of a representative embodiment of an aircraft landing gear assembly according to the present disclosure is shown;

[0020] Figure 2 It shows Figure 1 A side view of the aircraft landing gear assembly;

[0021] Figure 3 It shows Figure 1 An isometric view of the bogie beams and tires of the aircraft landing gear assembly; and

[0022] Figure 4 It shows Figure 3 The top view of the bogie beam and tires shown. Detailed Implementation

[0023] A landing gear assembly with a reduced retraction area is provided. The landing gear includes a bogie beam rotatably mounted to a shock absorber strut. Wheels are mounted at the front and rear ends of the bogie beam. To provide a smaller retraction area, the bogie beam assembly has a generally "Z"-shaped profile when viewed from above (or below). The Z-shaped profile of the bogie beam allows the wheels to be mounted closer to the center plane of the bogie beam, thereby reducing the overall width of the bogie beam / wheel.

[0024] Figure 1 and 2 A representative embodiment of a landing gear assembly 10 according to aspects of this disclosure is shown. The landing gear assembly 10 is mounted to the bottom of an aircraft and configured to reciprocate between an extended position and a retracted position. In the extended position, the landing gear assembly 10 extends downward from the aircraft and supports a portion of the aircraft on a pair of wheels 70 and 72. In the retracted position, the landing gear rotates upward to a retracted position, in which the landing gear assembly is at least partially disposed within the aircraft's landing gear bay. In some embodiments, landing gear doors cover the landing gear bay when the landing gear assembly 10 is retracted to improve aerodynamic characteristics and protect the landing gear assembly and other components located within the landing gear bay.

[0025] The landing gear assembly 10 includes a shock absorber strut 20 having a first end coupled to the aircraft to provide reciprocating motion between a retracted position and an extended position. In the illustrated embodiment, the upper end of the shock absorber strut 20 includes a trunnion 22 that rotatably couples the landing gear assembly 10 to the aircraft. An actuator (not shown) is operatively coupled to the shock absorber strut 20 to selectively drive the landing gear assembly between the retracted and extended positions.

[0026] The shock absorber strut 20 is a known shock absorber strut that functions as a damping spring. In the illustrated embodiment, the shock absorber strut 20 includes a piston 26, the upper portion of which is slidably disposed within a cylinder 24. The lower portion of the piston 26 extends from the cylinder 24 and is rotatably coupled to the bogie beam 50 about an axis 200. In the illustrated embodiment, a hook 28 is disposed on the end of the piston 26 and engages with a lug 58 formed on the bogie beam 50 to provide a rotatable pin connection therebetween.

[0027] In the illustrated embodiment, the torque linkage assembly 30 prevents the piston 26, and thereby prevents the bogie beams 50 and wheels 70 and 72 from rotating relative to the cylinder 24 about the common (longitudinal) axis of the piston and cylinder. The known torque linkage assembly 30 includes an upper torque linkage 32 rotatably associated with the cylinder 24 and a lower torque linkage 34 rotatably coupled to the piston 26. The upper torque linkage 32 and the lower torque linkage 34 are rotatably coupled to each other to form a linkage mechanism that prevents the piston 26 from rotating uncontrollably within the cylinder 26.

[0028] Now for reference Figure 3 and Figure 4 For clarity, the bogie beam 50, the first (front) wheel 70, and the second (rear) wheel 72 are shown, excluding the shock absorber strut 20 and the landing gear assembly 10. The bogie beam 50 includes a laterally extending (i.e., generally in an inward-outward direction) cylindrical hub 52. Lugs 58 connecting the bogie beam 50 to the shock absorber strut 20 are provided on top of the hub 52, such that the hub, and therefore the bogie beam 50, is rotatable about axis 200 relative to the piston 26.

[0029] The bogie beam 50 includes a first elongated leg 54 extending rearward from a first end of a hub 52. A second elongated leg 56 extends forward from a second end of the hub 52 (opposite to the first end of the hub). In the illustrated embodiment, the first leg 54 and the second leg 56 also extend upward as the legs extend forward and rearward from the hub 52, respectively. In other embodiments, one leg extends upward from the hub, and the other leg extends downward from the hub 52. In other embodiments, one leg extends horizontally from the hub 52, and the other leg extends upward, downward, or horizontally.

[0030] It is understood that other embodiments are also possible, for example, in which one leg extends from one end of the hub 52 in a generally forward direction and the other leg extends from the other end of the hub in a generally rearward direction, such that the legs are offset from each other and extend in opposite directions relative to the forward and rearward directions. In some embodiments, one or both legs are positioned at right angles relative to the hub 52. In some embodiments, one or both legs form acute or obtuse angles relative to the hub 52. In some embodiments, one or both legs are straight. In some embodiments, one or both legs include one or more curved or angled portions. These and other embodiments are considered and should be considered within the scope of this disclosure.

[0031] The first wheel 70 is rotatably mounted to the inside of the first leg 54 about axis 202, and the second wheel 72 is rotatably mounted to the inside of the second leg 56 about axis 204, wherein axis 202 is parallel to axis 204. Figure 4 As shown, the term "inner" as used herein refers to the direction along axes 202 and 204 toward the center portion of the bogie beam 50. Thus, the inner direction of the first outrigger 54 is opposite to the inner direction of the second outrigger 56. For each outrigger, the term "outer" refers to the direction opposite to the "inner" direction of that particular outrigger.

[0032] Still referencing Figure 4 The offset configuration of the bogie beam outriggers 54 and 56, combined with the first wheel 70 and the second wheel 72 respectively mounted to the inner sides of the first outrigger 54 and the second outrigger 56, provides a more compact bogie beam / wheel configuration. In this respect, the total width of the bogie beam 50 and the mounted wheels 70 and 72 is less than the combined width of the wheels. Conversely, known landing gear assemblies with wheels mounted to opposite sides of the bogie beam typically have a width that is the combined width of the wheels plus a portion of the width of the bogie beam (or the hooks for two adjacent landing gear wheels). Therefore, by offsetting the mounting positions of the wheels 70 and 72 toward or beyond the center of the bogie beam 50, the total width of the bogie beam and the mounted wheels according to an aspect of this disclosure is reduced. This offset provides a more compact landing gear assembly that requires less space in the landing gear bay when in the retracted position.

[0033] See again Figure 1 and Figure 2The landing gear assembly 10 optionally includes a pitch adjuster 90 that positions the bogie beam 50 relative to the shock absorber strut 20. The pitch adjuster 90 is a known pitch adjuster, one end of which is rotatably connected to a hook 36 fixed relative to the piston 26, and its opposite end is rotatably connected to a hook 64 fixed to the second outrigger 56. In some embodiments, the pitch adjuster is fixed to the main assembly 24 instead of the piston hook. The pitch adjuster can be connected to the hook 64, which may be present on either outrigger 56 or outrigger 54, or, if a dual pitch adjuster is used, may be present on both outrigger 56 and outrigger 54.

[0034] In some embodiments, the pitch adjuster 90 is a hydraulically operated telescopic actuator that selectively extends and / or retracts to selectively rotate the bogie beam 50 relative to the piston 26 about axis 200. In some embodiments, the pitch adjuster 90 is a passive pitch adjuster that uses a biasing element (e.g., a spring) and / or aerodynamic loads to position the bogie beam. It should be understood that this disclosure is not limited to including a pitch adjuster or including a particular type of pitch adjuster.

[0035] The illustrated embodiment of the landing gear assembly 10 includes a known braking assembly (not shown) corresponding to each of the first wheel 70 and the second wheel 72. This braking assembly typically applies torque to elements of the brake during braking, whereby the torque causes one or more brake levers to respond. When the brakes are engaged, the response of the brake levers prevents the braking assembly from rotating with the wheels. The brake levers typically connect a point on the braking assembly to an anchor point.

[0036] like Figure 1 and Figure 2 As shown, the bogie beam 50 includes a first brake lever hook 60 located near the intersection of the first outrigger 54 and the hub 52, and a second brake lever hook 62 located near the intersection of the second outrigger 56 and the hub 52. The first brake lever hook 60 provides an anchoring point for the first brake lever 80, and the second brake lever hook 62 provides an anchoring point for the second brake lever 82. It should be understood that each brake lever hook is configured to rotatably engage a lug formed on the end of the brake lever; however, other interfaces are also contemplated. In some embodiments, the lug is formed on the bogie beam 50, and the corresponding hook is formed on the end of the brake lever. In some embodiments, the positions of the lug and / or hook differ from the illustrated embodiment. In some embodiments, the brake lever is located on the upper part of the brake, and brake levers 80 and 82 are attached to lugs on piston hooks. These and other alternative embodiments are contemplated and should be considered within the scope of this disclosure.

[0037] The specific embodiments described above in conjunction with the accompanying drawings (where like reference numerals denote like elements) are intended to describe various embodiments of this disclosure, and are not intended to represent only those embodiments. Each embodiment described in this disclosure is provided by way of example or illustration only and should not be construed as superior to or advantageous to other embodiments. The illustrative examples provided herein are not intended to be exhaustive or to limit this disclosure to the precise forms disclosed.

[0038] In the foregoing description, specific details have been set forth to provide a thorough understanding of exemplary embodiments of the present disclosure. However, it will be apparent to those skilled in the art that the embodiments disclosed herein can be practiced without showing all the specific details. Furthermore, it should be understood that embodiments of the present disclosure may employ any combination of the features described herein.

[0039] This application may reference quantities and numbers. Unless otherwise stated, these quantities and numbers should not be considered limiting, but rather examples of possible quantities or numbers relevant to this application. Furthermore, in this regard, the application may use the term "multiple" to refer to quantities or numbers. In this respect, the term "multiple" means any number greater than one, such as two, three, four, five, etc. The terms "approximately," "about," etc., indicate plus or minus 5% of the stated value.

[0040] For the purposes of this disclosure, the phrase "at least one of A and B" is equivalent to "A and / or B" and vice versa, i.e., "A" alone, "B" alone, or "A and B". Similarly, the phrase "at least one of A, B, and C" refers to, for example, (A), (B), (C), (A and B), (A and C), (B and C), or (A, B, and C), including all further possible permutations when more than three elements are listed.

[0041] In this specification, existing technical terms may be used. These terms have their usual meaning in the prior art from which they are derived, unless expressly defined herein or the context in which they are used clearly implies otherwise.

[0042] The principles, representative embodiments, and modes of operation of this disclosure have been described in the foregoing description. However, the aspects of this disclosure intended to be protected should not be construed as limited to the specific embodiments disclosed. Furthermore, the embodiments described herein are considered illustrative rather than restrictive. It should be understood that changes and modifications, as well as equivalents, can be made by others without departing from the spirit of this disclosure. Therefore, it is expressly stated that all such changes, modifications, and equivalents fall within the spirit and scope of this disclosure.

Claims

1. A bogie beam for an aircraft landing gear assembly, comprising: An elongated hub having a first end and a second end, the hub being configured to be rotatably mounted to a shock-absorbing strut of the landing gear assembly about a mounting axis; A first leg extends radially from the first end of the hub in a first direction, the first leg having an inner side facing the second end of the hub, the first leg being configured to have a first wheel rotatably mounted to the inner side of the first leg about a first wheel axis. as well as A second leg extends radially from the second end of the hub in a second direction, the second leg having an inner side facing the first end of the hub, the second leg being configured to have a second wheel rotatably mounted to the inner side of the second leg about a second wheel axis, wherein the second leg is fixedly oriented relative to the first leg.

2. The bogie beam according to claim 1, characterized in that, The first direction is the forward direction, and the second direction is the backward direction.

3. The bogie beam according to claim 2, characterized in that, The first direction is parallel to the second direction.

4. The bogie beam according to claim 1, characterized in that, The axis of the first wheel is parallel to the axis of the second wheel.

5. The bogie beam according to claim 1, characterized in that, The mounting axis is parallel to at least one of the first wheel axis and the second wheel axis.

6. The bogie beam according to claim 1, characterized in that, It also includes an interface configured to rotatably connect the pitch adjuster to one of the first leg and the second leg.

7. The bogie beam according to claim 1, characterized in that, It also includes a first interface configured to rotatably connect the brake lever to one of the first leg and the second leg.

8. The bogie beam according to claim 7, characterized in that, It also includes a second interface configured to rotatably connect a second brake lever to another of the first and second legs.

9. A landing gear assembly for an aircraft, comprising: Vibration-absorbing struts are attached to the aircraft at one end; as well as Bogie beams, which include: A hub, which is rotatably connected to the end of the vibration-absorbing strut about a first axis; A first leg, extending from a first end of the hub along a first direction, the first leg being configured to have a first wheel rotatably mounted thereto; and A second leg extends from a second end of the hub along a second direction, the second leg being configured to have a second wheel rotatably mounted thereto, wherein the hub is positioned between the first leg and the second leg, wherein the second leg is fixedly oriented relative to the first leg. The first wheel is rotatably mounted to the inside of the first leg, and the inside of the first leg is close to the hub; and The second wheel is rotatably mounted to the second leg on the inside of the second leg, the inside of the second leg being close to the hub.

10. The landing gear assembly according to claim 9, characterized in that, Each of the first leg and the second leg includes an inner side and an outer side, with the inner side of the first leg and the outer side of the second leg positioned between the outer sides of the first leg and the second leg.

11. The landing gear assembly according to claim 9, characterized in that, The hub includes a lug extending radially from the outer surface of the hub, and the hub is rotatably connected to a hook disposed on the vibration-absorbing support.

12. The landing gear assembly according to claim 9, characterized in that, The hub includes a hook extending radially from the outer surface of the hub, the hook being rotatably connected to a lug disposed on the vibration-absorbing strut.

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