Landing gear retraction linkage

Abstract

The present disclosure relates to a landing gear retraction link mechanism. A landing gear comprises: an outer barrel rotatably coupled to a frame of an aircraft around a trunnion rotation axis; a shock strut assembly movably coupled to the outer barrel so as to reciprocate along a longitudinal axis of the outer barrel; and a retraction mechanism, the retraction mechanism comprising: a first retraction link member pivotally coupled to the outer barrel; a second retraction link member coupling the first retraction link member to the shock strut assembly; a crank member pivotally coupled to the outer barrel; a follower member coupling the crank member to a walking beam (also called a retraction actuator beam) of a landing gear retraction mechanism; and a follower member coupling the crank member to the first retraction link member.

Description

Technical Field

[0001] The exemplary embodiments relate generally to aircraft landing gear components and aircraft landing gear systems, and particularly to a landing gear assembly for extending and retracting the landing gear. Background Art

[0002] Aircraft typically include landing gear to facilitate takeoff, landing and taxiing. For various reasons, it is generally desirable to have a high landing gear. These reasons include generating a greater rotation angle (e.g., angle of attack) of the aircraft during takeoff and landing, providing more ground clearance for installing engines, increasing the aircraft's ride height, etc. Lengthening the landing gear can cause several problems, including the requirement to move the landing gear further outboard of the fuselage along the wing to compensate for the increased length of the landing gear when stored, integrating the wing skids into the aircraft, larger wheel wells, etc. In addition, increasing the length of the landing gear increases the static height of the aircraft, resulting in the need for a new sill waterline, a longer and higher exit skid, a redesign of the landing gear actuation mechanism, the need for an off-wing exit skid, a redesign of the landing gear storage compartment, etc.

[0003] Some aircraft utilize telescopic landing gear to provide increased ground clearance, wherein the length of the telescopic landing gear can be reduced for storage of the landing gear in the wheel well of the aircraft. The telescopic landing gear can also provide a greater rotation angle of the aircraft during takeoff and / or landing. The telescopic landing gear can be used in conventional aircraft to resist the cost of reconfiguring the wheel well of the aircraft to include a higher landing gear. When the landing gear is retracted to store the landing gear (i.e., shortening the landing gear to fit the existing wheel well), the length of the telescopic landing gear will be shortened, and when deployed for ground handling (e.g., takeoff, landing, taxiing, etc.), the landing gear will be extended (i.e., its length will increase) to utilize a higher landing gear. Summary of the invention

[0004] The following is a non-exhaustive list of examples that may or may not be claimed according to the present disclosure.

[0005] One example of the subject matter of the present disclosure relates to a landing gear, comprising: an outer barrel rotatably coupled to a frame of an aircraft about a trunnion rotation axis; a shock strut assembly movably coupled to the outer barrel for reciprocating movement along a longitudinal axis of the outer barrel; and a retraction mechanism, the retraction mechanism comprising: a first retraction link member pivotally coupled to the outer barrel; a second retraction link member coupling the first retraction link member to the shock strut assembly; a crank member pivotally coupled to the outer barrel; a driving member coupling the crank member to a walking beam (also called a retraction actuator beam) of a landing gear retraction mechanism; and a driven member coupling the crank member to the first retraction link member.

[0006] Another example of the subject matter according to the present disclosure relates to a retraction mechanism for use with a landing gear of an aircraft, the landing gear comprising: an outer barrel rotatably coupled to a frame of the aircraft about a trunnion rotation axis; a shock strut assembly movably coupled to the outer barrel for reciprocating movement along a longitudinal axis of the outer barrel; and a retraction mechanism comprising: a first retraction link member pivotally coupled to the outer barrel; a second retraction link member coupling the first retraction link member to the shock strut assembly; a crank member pivotally coupled to the outer barrel; a driving member coupling the crank member to a walking beam (also referred to as a retraction actuator beam) of a landing gear retraction mechanism; and a driven member coupling the crank member to the first retraction link member.

[0007] Yet another example according to the subject matter of the present disclosure relates to an aircraft, comprising a frame and a landing gear coupled to the frame, the landing gear comprising: an outer barrel rotatably coupled to the frame of the aircraft about a trunnion rotation axis; a shock strut assembly movably coupled to the outer barrel for reciprocating movement along a longitudinal axis of the outer barrel; and a retraction mechanism, the retraction mechanism comprising: a first retraction link member pivotally coupled to the outer barrel; a second retraction link member coupling the first retraction link member to the shock strut assembly; a crank member pivotally coupled to the outer barrel; a driving member coupling the crank member to a walking beam (also referred to as a retraction actuator beam) of a landing gear retraction mechanism; and a driven member coupling the crank member to the first retraction link member.

[0008] Yet another example of the subject matter according to the present disclosure relates to a method of operating a landing gear of an aircraft, the method comprising: rotating the landing gear about a trunnion rotation axis, wherein the trunnion rotation axis is defined by an outer barrel of the landing gear; and moving a shock strut assembly relative to the outer barrel using a retraction mechanism, wherein the outer barrel at least partially surrounds the shock strut assembly, and the retraction mechanism comprises: a first retraction link member pivotally coupled to the outer barrel; a second retraction link member coupling the first retraction link member to the shock strut assembly; a crank member pivotally coupled to the outer barrel; a driving member coupling the crank member to a walking beam (also referred to as a retraction actuator beam) of a landing gear retraction mechanism; and a driven member coupling the crank member to the first retraction link member. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] Having thus described examples of the disclosure in general terms, reference will now be made to the drawings, which are not necessarily drawn to scale and in which like reference numerals refer to the same or similar parts throughout the several views, and in which:

[0010] Figure 1A-Figure 1C is a schematic diagram of an aircraft and landing gear according to one or more aspects of the present disclosure;

[0011] Figure 2is in an extended configuration according to one or more aspects of the present disclosure Figure 1A-Figure 1C A schematic perspective view of the landing gear;

[0012] Figure 3 A device according to one or more aspects of the present disclosure in a retracted configuration and an extended configuration Figure 2 A schematic partial cross-sectional side view showing a comparison between various parts of a landing gear;

[0013] Figure 4 is in an extended configuration according to one or more aspects of the present disclosure Figure 2 a schematic perspective partial cross-sectional view of a portion of a landing gear of;

[0014] Figure 5 is in a retracted configuration according to one or more aspects of the present disclosure Figure 2 A schematic perspective partial cross-sectional view of a landing gear;

[0015] Figure 6 According to one or more aspects of the present disclosure Figure 2 a schematic cross-sectional side view of a portion of a landing gear of;

[0016] Figure 7 According to one or more aspects of the present disclosure Figure 2 a schematic perspective cross-sectional side view of a portion of a landing gear;

[0017] Figure 8 According to one or more aspects of the present disclosure Figure 2 a schematic perspective view of a portion of a landing gear;

[0018] Fig. 9 According to one or more aspects of the present disclosure Figure 2 a schematic partial cross-sectional side view of a portion of a landing gear of;

[0019] Fig.10 According to one or more aspects of the present disclosure Figure 2 a schematic perspective cross-sectional view of a portion of a landing gear of;

[0020] Fig.11 According to one or more aspects of the present disclosure Figure 2 a schematic perspective view of a portion of a landing gear;

[0021] Fig.12 According to one or more aspects of the present disclosure Figure 2 a schematic perspective view of a portion of a landing gear;

[0022] Fig.13 According to one or more aspects of the present disclosure Figure 2a schematic perspective partial cross-sectional view of a portion of a landing gear of;

[0023] Fig.14 According to one or more aspects of the present disclosure Figure 2 a schematic perspective view of a portion of a landing gear;

[0024] Fig.15 is in an extended configuration according to one or more aspects of the present disclosure Figure 1A-Figure 1C A schematic perspective partial cross-sectional view of a landing gear;

[0025] Fig.16 is in a retracted configuration according to one or more aspects of the present disclosure Fig.15 A schematic perspective partial cross-sectional view of a landing gear;

[0026] Fig.17 A device according to one or more aspects of the present disclosure in a retracted configuration and an extended configuration Fig.15 A schematic cross-sectional side view showing a comparison between various parts of a landing gear;

[0027] Fig.18 According to one or more aspects of the present disclosure Fig.15 a schematic perspective view of a portion of a landing gear;

[0028] Fig.19 According to one or more aspects of the present disclosure Fig.15 a schematic perspective view of a portion of a landing gear;

[0029] Fig. 20 According to one or more aspects of the present disclosure Figure 1A-Figure 1C a schematic perspective view of a portion of a landing gear;

[0030] Fig.21 According to one or more aspects of the present disclosure Figure 1A-Figure 1C a schematic perspective view of a portion of a landing gear;

[0031] Fig. 22 According to one or more aspects of the present disclosure Figure 1A-Figure 1C a schematic perspective view of a portion of a landing gear;

[0032] Fig.23 is an exemplary graph showing a retracted length of a landing gear and a retracted angle of the landing gear according to one or more aspects of the present disclosure;

[0033] Fig.24A is in an extended configuration according to one or more aspects of the present disclosure Fig.15 A schematic cross-sectional side view of a landing gear;

[0034] Fig. 24B is in a retracted configuration according to one or more aspects of the present disclosure Fig.15 A schematic cross-sectional side view of a landing gear;

[0035] Figure 25A-Figure 25C According to one or more aspects of the present disclosure Figure 2 A schematic perspective view of a retraction sequence of a landing gear;

[0036] Figure 26A-26C According to one or more aspects of the present disclosure Fig.15 A schematic perspective view of a retraction sequence of a landing gear;

[0037] Fig. 27 According to one or more aspects of the present disclosure Figure 1A-Figure 1C A flowchart of a method for retracting a landing gear;

[0038] Fig.28 According to one or more aspects of the present disclosure Figure 1A-Figure 1C A flowchart of a method for extending a landing gear; and

[0039] Fig.29 It is a block diagram of the aircraft manufacturing and maintenance methods. DETAILED DESCRIPTION

[0040] refer to Figure 1A-Figure 1C , Figure 2 and Fig.15 , incorporating aspects of the present disclosure, shows an exemplary aircraft 1000 and landing gear 100, 100A, 100B having a retraction mechanism 130A, 130B. To achieve a greater angle of attack / rotation of the aircraft during takeoff and / or landing, maintaining the current static ground clearance and current attachment position of conventional landing gear without having to redesign the aircraft, the retraction mechanism 130A, 130B for the landing gear 100, 100A, 100B described herein increases the height of the aircraft during takeoff and shortens the length of the landing gear in the stowed position after takeoff for stowage in a current landing gear bay with little or no modification to the aircraft. In particular, the landing gear 100, 100A, 100B described herein is cost effective and not overly complex while still meeting the static height, takeoff and / or landing height, and stowage requirements of the landing gear.

[0041] The following provides illustrative, non-exhaustive examples of subject matter that may or may not be claimed in accordance with the present disclosure.

[0042] Aspects of the disclosure described herein may provide landing gear, generally referred to as landing gear 100, and more specifically as landing gear 100A, 100B. The landing gear 100, 100A, 100B is retracted when retracted into the wheel well of the aircraft 1000 so that the landing gear 100, 100A, 100B can be stored within the frame 1001 of the aircraft 1000. When extended, the landing gear 100, 100A, 100B provides increased ground clearance, such that, for example, larger and more efficient engines can be installed for the aircraft 1000. Aspects of the disclosure described herein provide landing gear 100, 100A, 100B with a retraction mechanism 130A, 130B that generally has a configuration that provides a low static ground clearance for the aircraft, a high take-off height for the aircraft, and a shortened landing gear length for storing the landing gear 100, 100A, 100B within the aircraft 1000.

[0043] In one aspect, while the landing gear 100, 100A, 100B described herein is described with respect to a commercial passenger aircraft (referred to herein as aircraft 1000), in other aspects, the aircraft may be any suitable aircraft having fixed wings, variable sweep wings, or rotary wings. The landing gear 100, 100A, 100B may also be used in any suitable position on the aircraft 1000, such as a main landing gear 101 positioned toward the longitudinal center of the aircraft 1000, or in other aspects, a nose landing gear 102 positioned toward the longitudinal front of the aircraft 1000. As will be described herein, the landing gear 100, 100A, 100B is configured to be coupled to a frame 1001 of an aircraft 1000 and one or more of the landing gear components (e.g., a landing gear retraction mechanism 200 including an actuator 201, a reaction link 202, a walking beam 210 (i.e., also referred to as a retraction actuator beam), etc.) for providing a low static ground clearance, a high take-off altitude, and achieving a retracted length of the landing gear 100, 100A, 100B for retracting the landing gear 100, 100A, 100B.

[0044] refer to Figure 1B and Figure 1C , the landing gear 100 is shown in the extended / deployed and stowed / retracted positions. A conventional high landing gear 105 is also shown for comparison of the landing gear attachment position relative to the frame 1001 of the aircraft 1000. In one aspect, the landing gear 100 provides the same static ground clearance A (e.g., the distance from the ground to the lowest point on the aircraft 1000 (such as the bottom of the frame 1001)) as the conventional high landing gear 105 when coupled to the frame 1001 further inwardly by a predetermined distance B relative to the centerline CL of the frame 1001. As can be seen in FIG. Figure 1BAs best seen in FIG. 1 , when retracted, the landing gear wheel assembly 119 and the location of the wheel axis WA are located in a common location (e.g., within the wheel well of the aircraft 1000 with little or no modification to the wheel well), as shown by the retraction path 103 of the conventional high landing gear 105 and the retraction path 104 of the landing gear 100. In this way, the landing gear 100 can be installed to the aircraft while maintaining the aircraft's existing conventional landing gear well, sill waterline, etc., i.e., the aircraft 1000 does not have to be redesigned to accommodate the landing gear 100 and receive the increased takeoff and / or landing altitude and aircraft rotation benefits of the landing gear 100.

[0045] Reference now Figure 2-Figure 10 In one aspect, the landing gear 100A includes an outer barrel 110, a shock strut assembly 120, a wheel assembly 119 coupled to the shock strut assembly 120, and a retraction mechanism 130A. In one aspect, the landing gear 100A also includes a cover 114 ( Fig.11 )、sensor actuator arm 300( Fig.14 )、Sensor 310( Fig.11 )、Door 400( Figure 20-22 ), and the door driving member 410 ( Figure 20-22 The landing gear retracting mechanism 200 is coupled to the landing gear 100A for extending / retracting the landing gear 100A and driving the retracting mechanism 130A.

[0046] The outer barrel 110 includes a first end 111 and a second end 112 longitudinally spaced apart from the first end 111 along a longitudinal axis 115. The outer barrel 110 also includes a retracting connecting rod cavity 113 ( Figure 3 ) and the inner cavity 117. The inner cavity 117 is configured such that the shock strut assembly 120 is at least partially disposed within the inner cavity 117. The retraction link cavity 113 is configured to at least partially accommodate a portion of the retraction mechanism 130A. In one aspect, the outer barrel 110 is a single rigid member such that the retraction link cavity 113 and the inner cavity 117 are integrally formed with the outer barrel 110. The outer barrel 110 is rotatably coupled to the frame 1001 of the aircraft 1000 about the trunnion rotation axis 1002 so that the outer barrel 110 can be rotated in the direction R1 ( Figure 2 ) on the trunnion rotation axis 1002. In one aspect, the first end 111 of the outer barrel 110 forms the landing gear trunnion 165 and is rotatably coupled to the frame 1001 of the aircraft 1000 about the trunnion rotation axis 1002, effectively coupling the outer barrel 110 to the frame 1001. In one aspect, the outer barrel 110 further includes: a cover 114 ( Fig.11 ), the cover 114 is configured to enclose the first contraction link member 140 and the second contraction link member 150 in the outer tube 110; the fluid discharge hole 116 ( Fig.10), the fluid drain hole 116 is configured to drain condensate or fluid that may penetrate / accumulate in the retracting link cavity 113 or the inner cavity 117; and the eccentric stop surface 118 ( Fig. 9 and 17 ).

[0047] The shock strut assembly 120 includes a bulkhead 123 ( Figure 6 ) to form a first seal 124 ( Figure 6 ). The partition 123 is also coupled to the retraction mechanism 130A to achieve reciprocating movement of the shock strut assembly 120 in the inner cavity 117, thereby retracting and extending the landing gear 100A. The inner barrel 125 is movably coupled to both the inner cavity 117 of the outer barrel 110 and the partition 123 to form a second seal 126 ( Figure 5 ), and allows the inner barrel 125 to move within the inner cavity 117 of the outer barrel 110 relative to the diaphragm 123 (such as during compression and rebound of the shock strut assembly 120) and together with the diaphragm 123 (such as during retraction and extension of the landing gear 100A). The retraction mechanism 130A enables the diaphragm 123 and the inner barrel 125 to move as a unit in the directions D1, D2 ( Figure 3 ) to increase or decrease the length 1950 (of the landing gear 100A) according to the corresponding deployed / extended configuration 800 or retracted / folded configuration 850 of the landing gear 100A Figure 1B ). In one aspect, the length 1950 can be increased or decreased according to the retracted configuration 850 or the deployed configuration 800 by moving the shock strut assembly 120 a distance 950 using the retraction mechanism 130A. The distance 950 can be about 10 inches, or in other aspects, the distance can be greater or less than about 10 inches.

[0048] Still reference Figure 2-Figure 10 The retraction mechanism 130A of the landing gear 100A includes a first retraction link member 140, a second retraction link member 150, a crank member 160, a driving member 170, and a driven member 180. The crank member 160 includes a first end 161 and a second end 162. In one aspect, the crank member 160 is rotatably coupled to the outer cylinder 110 about a first rotation axis 500, so that the crank member 160 rotates about the first rotation axis 500 in directions R2, R3. In one aspect, the crank member 160 is coupled to the outer cylinder 110 between the first end 111 and the second end 112 of the outer cylinder 110. For example, as Figure 7As shown, crank member 160 is coupled to outer barrel 110 in any suitable manner, such as by a cross-bolt assembly 700 including a cross-bolt 701, a pivot washer 702, and a stud 703. In one aspect, crank member 160 is coupled to outer barrel via bracket 169, such as Figure 8 shown.

[0049] The driving member 170 includes a first end 171 and a second end 172. The first end 171 of the driving member 170 is at a position 2000 ( Figure 2 ) is rotatably coupled to the walking beam 210 of the landing gear retraction mechanism 200, so that the drive member 170 and the walking beam 210 pivot relative to each other in directions R4, R5 around the walking beam pivot axis 2000. The second end 172 of the drive member 170 is rotatably coupled to the first end 161 of the crank member 160 at the first crank pivot axis 2101, so that the drive member 170 and the crank member 160 pivot relative to each other in directions R6, R7 around the first crank pivot axis 2101. In one aspect, the drive member 170 is coupled to the crank member 160 via a U-joint, while in other aspects, they may be coupled together via spherical bearings or any other suitable couplings (it should be noted that each rotatable coupling between the links of the retraction mechanisms 130A, 130B described herein may be coupled in a manner substantially similar to the rotatable coupling between the drive member 170 and the crank member 160 to transfer torque between each link and change the direction of the force applied by the walking beam 210 to retract and extend the landing gear 100, 100A, 100B). The drive member 170 is configured to effectively couple the crank member 160 to the walking beam 210 of the landing gear retraction mechanism 200. The drive member 170 drives the rotational movement of the crank member 160 in directions R2, R3 about the first rotational axis 500 via the walking beam 210. In one aspect, the drive member 170 has an adjustable length 998 ( Figure 4 ).

[0050] The driven member 180 includes a first end 181 and a second end 182. The first end 181 is coupled to the second end 162 of the crank member 160 at the second crank pivot axis 2102, so that the driven member 180 and the crank member 160 pivot relative to each other about the second crank pivot axis 2102 in directions R8, R9. The second end 182 is coupled to the first contraction link member 140. The driven member 180 is configured to effectively couple the crank member 160 to the first contraction link member 140, so that the crank member 160 drives the first contraction link member 140 to rotate about the second rotation axis 501. In one aspect, the driving member 170 and the driven member 180 extend adjacent to each other substantially along the longitudinal axis 115 of the outer cylinder 110. In one aspect, the driven member 180 has an adjustable length 999 ( Figure 4 ).

[0051] Reference now Figure 3-Figure 5 and Figure 9-10 The first contraction link member 140 includes a first end 141 (rotatably coupled to the outer cylinder 110) Fig. 9 and Fig.10 ) and a second end 142 (rotatably coupled to the second retracting link member 150 Fig. 9 and Fig.10 ). The first retract link member 140 is at least partially disposed in the retract link cavity 113 of the outer barrel 110. In one aspect, the first retract link member 140 is disposed in the retract link cavity 113 so that the first retract link member 140 is enclosed by the outer barrel 110. For example, the cover 114 ( Fig.11 ) may enclose the first retraction link member 140 within the retraction link cavity 113 of the outer cylinder 110. The cover 114 may include a vent 1199 to allow air to flow into and out of the retraction link cavity 113 and the inner cavity 117 during extension and retraction of the shock strut assembly 120 relative to the outer cylinder 110. The first retraction link member 140 is rotatably coupled to the outer cylinder 110 so that the first retraction link member 140 rotates in directions R10, R11 relative to the outer cylinder 110 about the second rotation axis 501. The second rotation axis 501 is spaced apart from the first rotation axis 500 along the longitudinal axis 115 of the outer cylinder 110. In one aspect, the first rotation axis 500 and the second rotation axis 501 are substantially parallel to each other (e.g., Figure 2 In one aspect, the first contraction link member 140 further includes a contraction crank member 190 that couples the first contraction link member 140 to the driven member 180 .

[0052] The second retracting link member 150 includes a first end 151 and a second end 152 ( Fig. 9 and Fig.10 In one aspect, the second retract link member 150 is disposed within the retract link chamber 113 such that the second retract link member 150 is enclosed by the outer cylinder 110. For example, the cover 114 ( Fig.11 ) can enclose the second retract link member 150 (and the first retract link member 140) within the retract link cavity 113. The first end 151 of the second retract link member 150 is rotatably coupled to the bulkhead 123 ( Fig. 9 and Fig.10). The second end 152 of the second retract link member 150 is rotatably coupled to the second end 142 of the first retract link member 140, effectively coupling the first retract link member 140 to the shock strut assembly 120. The first retract link member 140 and the second retract link member 150 are rotatably connected to each other so as to be folded and unfolded relative to each other in directions R12, R13. For example, the driven member 180 is coupled to the first retract link member 140 so as to achieve the folding and unfolding of the second retract link member 150 relative to the first retract link member 140 under the push of the driving member 170. Since the driven member 180 pivotally coupled to the first retract link member 140 drives the rotation of the first retract link member 140 and thus drives the folding / expansion of the first and second retract link members 140, 150, the extension or retraction of the shock strut assembly 120 relative to the outer cylinder 110 and along the longitudinal axis 115 is achieved. When deployed, the first retract link member 140 and the second retract link member 150 are locked in the over-center position 900 ( Fig. 9 In one aspect, the eccentric stop surface 118 ( Fig. 9 and 17 ) is configured to be releasably coupled with one or more of the first retraction link member 140 and the second retraction link member 150 to achieve eccentric locking of the first retraction link member 140 and the second retraction link member 150 in the eccentric position 900. In one aspect, the eccentric stop surface 118 is integral with the outer cylinder 110, while in another aspect, the eccentric stop surface 118 is a replaceable, detachable component. The eccentric position 900 can be maintained due to the preload on at least one or more of the first retraction link member 140 and the second retraction link member 150. For example, the length of one or more of the driving member 170, the crank member 160 and the driven member 180 can be set so that, when in the deployed configuration 800, the retraction mechanism 130A acts as a spring mechanism that pushes the first retraction link member 140 and the second retraction link member 150 to the eccentric position 900 ( Fig. 9 ), so that one or more of the first retraction link member 140 and the second retraction link member 150 are coupled to the eccentric stop surface 118. In the retracted configuration 850, the preload on the retraction mechanism 130A can be released compared to the deployed configuration 800.

[0053] Reference now Figure 2 and Figure 12-14, the contraction crank member 190 is coupled to the first contraction link member 140 such that the contraction crank member 190 and the first contraction link member 140 rotate as a unit about the second rotation axis 501. The contraction crank member 190 is disposed adjacent to the first end 141 of the first contraction link member 140. In one aspect, the crank member receiver 193 of the first contraction link member 140 is configured to receive the contraction crank member 190 such that the contraction crank member 190 is rotationally fixed relative to the first contraction link member 140. For example, the contraction crank member 190 may include mating polygonal surfaces 1901-1904 that couple with polygonal surfaces 1941-1944 of the crank member receiver 193. It should be noted that although the mating surfaces are shown as having a square configuration, the mating surfaces may have any suitable configuration, including triangles, hexagons, octagons, splines, etc., which transmit torque between the first contraction link member 140 and the contraction crank member 190. In one aspect, the contraction crank member 190 utilizes a cross bolt 898 and a pin 899 ( Fig.13 ) is coupled to the first contraction link member 140. On the other hand, the contraction crank member 190 and the first contraction link member 140 can be constructed as a single integral member. At least a portion of the contraction crank member 190 extends through the outer cylinder 110. The driven member 180 is coupled to the contraction crank member 190 at the third crank pivot axis 2103, so that the driven member 180 and the contraction crank member 190 pivot relative to each other around the third crank pivot axis 2103 in directions R17, R18. The pivoting of the driven member 180 and the contraction crank member 190 relative to each other around the third crank pivot axis 2103 drives the rotation of the first contraction link member 140 around the second rotation axis 501. As described above, the rotation of the first contraction link member 140 around the second rotation axis 501 enables the extension and retraction of the shock strut assembly 120 relative to the outer cylinder 110 and along the longitudinal axis 115.

[0054] Sensor actuator arm 300 ( Fig.14 ) is coupled to the first retract link member 140. The sensor actuator arm 300 is coupled to the first retract link member 140 to rotate together with the first retract link member 140. The sensor 310 ( Fig.11) is coupled to the outer barrel 110 and configured to sense the sensor actuator arm 300 when the shock strut assembly 120 is extended. For example, the sensor actuator arm 300 includes a target 301, and the sensor 310 is a proximity sensor configured to sense the target 301. It should be noted that the sensor actuator arm 300 may include any suitable sensor input, and the sensor 310 may be any suitable sensor configured to sense the corresponding sensor input of the sensor actuator arm 300. The sensor 310 may be coupled to any suitable controller 1005 (FIG. 1) of the aircraft 1000, wherein the controller 1005 is configured to indicate to an operator or maintenance personnel of the aircraft 1000 that the retraction mechanism 130A is in a predetermined position relative to, for example, the outer barrel 110.

[0055] Reference now Figure 15-19 Unless otherwise specified, the landing gear 100B is substantially similar to the landing gear 100A. For example, the landing gear 100B includes an outer barrel 110, a wheel assembly 119, a shock strut assembly 120, and a retraction mechanism 130B. The landing gear retraction mechanism 200 is coupled to the landing gear 100B for extending / retracting the landing gear 100B and driving the retraction mechanism 130B.

[0056] The retraction mechanism 130B of the landing gear 100B includes a crank member 1560, a drive member 1570, a driven member 1580, and a first retraction link member 140 and a second retraction link member 150. Each component of the retraction mechanism 130B of the landing gear 100B functions in a substantially similar manner to the components of the retraction mechanism 130A of the landing gear 100A. For example, the retraction mechanism 130B enables extension and retraction of the shock strut assembly 120 relative to the outer barrel 110 and along the longitudinal axis 115 to increase or decrease the length 1950 ( 1950 ) of the landing gear 100B according to the corresponding deployed configuration 800 or retracted configuration 850 of the landing gear 100B. Figure 1B ). In one aspect, the length 1950 can be increased or decreased according to the retracted configuration 850 or the deployed configuration 800 by moving the shock strut assembly 120 a distance 950 using the retraction mechanism 130B. The distance 950 can be about 10 inches, or in other aspects, the distance can be greater or less than about 10 inches.

[0057] In this regard, the crank member 1560 is pivotally coupled to the outer barrel 110 at a first end 111 of the outer barrel 110 opposite the second end 112 of the outer barrel 110 relative to the trunnion rotation axis 1002. Here, the crank member 1560 is coupled to the outer barrel 110 about the first rotation axis 705, as shown in FIG. Fig.15 and Fig.17 In this regard, the first rotation axis 705 and the second rotation axis 501 intersect each other ( Fig.16). It should be noted that the crank member 1560 can be coupled to the outer barrel 110 in any suitable manner that enables rotational movement of the crank member 1560 about the first rotational axis 705. In this regard, the driven member 1580 is pivotally coupled to the first retraction link member 140 adjacent the second end 142 to drive the rotation of the first retraction link member 140 about the second rotational axis 501 and enable extension or retraction of the shock strut assembly 120 relative to the outer barrel 110 and along the longitudinal axis 115 in a manner similar to the landing gear 100A. In one aspect, the landing gear 100B may also include a door 400 ( Figure 20-22 ) and the door driving member 410 ( Figure 20-22 ).

[0058] Reference now Figure 20-22 , the door 400 is pivotally coupled to the frame 1001 about the door pivot axis 401. In one aspect, the door drive member 410 couples the door 400 to the outer cylinder 110 so that the rotation of the outer cylinder 110 about the trunnion rotation axis 1002 enables the door 400 to rotate about the door pivot axis 401 in the open position (when the landing gear 100A, 100B is as in Fig. 20 extended) and closed position (when the landing gear 100A, 100B is in Fig.21 and Fig. 22 In one aspect, the door drive member 410 is a hinge member that couples the door 400 to the walking beam 210 ( Fig. 20 and Fig.21 ), so that the rotation of the outer cylinder 110 around the trunnion rotation axis 1002 and the movement of the walking beam 210 realize the pivoting of the door 400 around the door pivot axis 401 between the open position and the closed position. In other aspects, the door drive member 410 can be a single rigid member or any other suitable member to realize the pivoting of the door 400 between the open position and the closed position.

[0059] Now refer to Figure 3 , Fig.17 and Fig.23 , shows an exemplary graph of landing gear 100A, 100B, showing retracted length (e.g., distance 950) versus retraction angle (e.g., the angle of landing gear 100A, 100B relative to frame 1001 of aircraft 1000 as landing gear 100A, 100B rotates about trunnion rotation axis 1002). As landing gear 100A, 100B is retracted, such as during takeoff, the position of bulkhead 123 is tracked, indicating the distance 950 that bulkhead 123 travels relative to outer barrel 110. As shown in FIG. Fig.23As shown, when the landing gear 100A, 100B is retracted to form a zero (0) degree angle (i.e., the landing gear 100A, 100B is extended) to an angle between about sixty (60) degrees and about eighty (80) degrees, the distance 950 increases to approximately 10 inches (and the landing gear 100A, 100B is retracted a corresponding distance to retract the length 1950).

[0060] Reference now Figure 2 , Fig.24A , Fig. 24B , Figure 25A-Figure 25C , Figure 26A-26C and Fig. 27 , a method 2700 for operating, for example, landing gear 100A, 100B is shown. In one aspect, the landing gear 100A, 100B is in a deployed configuration 800, such as during ground operation, takeoff, and landing of the aircraft 1000. When the landing gear 100A is in the deployed configuration 800, the retraction mechanism 130A is in an extended position 801, such as, for example Fig.24A , Fig.25A and Fig.26A shown.

[0061] To retract the landing gear 100A, 100B, for example, after takeoff, the landing gear retraction mechanism 200 is operated to rotate the landing gear 100A, 100B about the trunnion rotation axis 1002 ( Fig. 27 , block 2701), wherein the trunnion rotation axis is defined by the outer barrel 110 of the landing gear 100A, 100B. For example, the walking beam 210 is actuated by the actuator 201 to rotate the outer barrel 110 about the trunnion rotation axis 1002 and retract the landing gear 100A, 100B. The outer barrel 110 is rotatably fixed to the frame 1001 of the aircraft 1000 about the trunnion rotation axis 1002. The force F ( Fig.25A and Fig.26A ) is applied to the walking beam 210 by the actuator 201. Since the outer barrel 110 is rotatably fixed to the frame 1001 of the aircraft 1000, the outer barrel 110 is forced to rotate about the trunnion rotation axis 1002 in the direction R1R ( Fig.25A and Fig.26A With respect to the outer cylinder 110 rotating about the trunnion rotation axis 1002 in the direction R1R, the shock strut assembly 120 is moved relative to the outer cylinder 110 in the direction D1 by the contraction mechanisms 130A and 130B ( Fig. 27 , block 2702). The drive member 170, 1570 of the retraction mechanism 130A, 130B is rotatably coupled to the walking beam 210 and rotates relative to the crank member 160, 1560 about the first crank pivot axis 2101 in the direction R7, which forces the crank member 160, 1560 to rotate about the first rotation axis 500, 705 in the direction R2 ( Fig. 27, block 2703). With respect to the landing gear 100A, when the drive member 170 and the crank member 160 rotate relative to each other, the driven member 180 is forced to pivot relative to the retract crank member 190 about the third crank pivot axis 2103 in the direction R17, which causes the first retract link member 140 and the retract crank member 190 to rotate as a unit about the second rotation axis 501 in the direction R10 ( Fig. 27 , block 2704). With respect to the landing gear 100B, when the drive member 1570 and the crank member 1560 rotate relative to each other, the driven member 1580 is forced to pivot relative to the first retract link member 140 about the third crank pivot axis 2103A in the direction R17, which causes the first retract link member 140 to rotate about the second rotation axis 501 in the direction R10 ( Fig. 27 , box 2704).

[0062] When the first retraction link member 140 rotates in the direction R10 about the second rotation axis 501, the eccentric position 900 is unlocked (i.e., the first retraction link member 140 is folded relative to the second retraction link member 150) to achieve the movement of the inner barrel 125 and the partition 123 of the shock strut assembly 120 in the direction D1 and the retraction of the landing gears 100A, 100B ( Fig. 27 , block 2705). The first retract link member 140 and the second retract link member 150 are folded relative to each other and the shock strut assembly 120 is driven from the second end 112 of the outer cylinder 110 to the first end 111 of the outer cylinder 110 along the longitudinal axis 115 ( Fig. 27 , block 2706). When the landing gear 100A, 100B is retracted and rotated to the retracted configuration 850 (eg, Fig.25C and Fig.26C When the inner cylinder 125 is transferred from the second end 112 of the outer cylinder 110 to the first end 111, the wheel assembly 119 is transported toward the first end 111 of the outer cylinder 110 to retract the length 1950 ( Figure 1B ).

[0063] Reference now Figure 2 , Fig.24A , Fig. 24B , Figure 25A-Figure 25C , Figure 26A-26C and Fig.28 , a method 2800 for extending the landing gear 100A, 100B is shown. The landing gear 100A, 100B is in a retracted configuration 850 ( Fig.25C and Fig.26C ). When the landing gear 100A, 100B is in the retracted configuration 850, the retracting mechanism 130A, 130B is in the retracted position 851, such as Fig.25C and Fig.26C shown.

[0064] To extend the landing gear 100A, 100B, for example before landing, the reverse sequence to that described above is initiated by deploying the landing gear 100A, 100B, for example under gravity. Fig.28 , block 2801). When the outer cylinder 110 rotates about the trunnion rotation axis 1002 in the direction R1E and moves to the deployed configuration 800 under gravity, the retraction mechanisms 130A, 130B are extended ( Fig.28 , block 2802). For example, the drive member 170, 1570 of the retraction mechanism 130A, 130B is rotatably coupled to the walking beam 210 and rotates in the direction R6 relative to the crank member 160, 1560 about the first crank pivot axis 2101, which forces the crank member 160, 1560 to rotate in the direction R3 about the first rotation axis 500, 705 ( Fig.28 , block 2803). When the drive member 170, 1570 and the crank members 160, 1560 rotate relative to each other, the driven member 180 is forced to pivot relative to the retract crank member 190 about the third crank pivot axis 2103 in the direction R18, which causes the first retract link member 140 and the retract crank member 190 to rotate as a unit in the direction R11 about the second rotation axis 501 (or in the case of the landing gear 100B, the driven member 1580 pivots relative to the first retract link member 140 in the direction R18, thereby causing the first retract link member 140 to rotate about the second rotation axis 501 in the direction R11) ( Fig.28 , block 2804). When the first retract link member 140 rotates in the direction R11, the first retract link member 140 and the second retract link member 150 are deployed relative to each other and drive the shock strut assembly 120 from the first end 111 of the outer cylinder 110 to the second end 112 of the outer cylinder 110 along the longitudinal axis 115 ( Fig.28 , block 2805). The first retracting link member 140 and the second retracting link member 150 are deployed to the extended position and locked in the eccentric position 900 ( Fig.28 , block 2806). As the landing gear 100A, 100B deploys, the preload in the retraction mechanism 130A, 130B increases to maintain the first and second retraction link members 140, 150 in the over-center position 900.

[0065] You can Fig.29 Examples of the present disclosure are described in the context of aircraft manufacturing and service method 2900 shown. In other aspects, examples of the present disclosure may be applied to any suitable industry, such as, for example, automotive, marine, and aerospace. With respect to aircraft manufacturing, during pre-production, illustrative method 2900 may include specification and design of aircraft 1000 ( Fig.29 , Box 2904) and Material Procurement ( Fig.29 During production, component and subassembly manufacturing of aircraft 1000 may occur ( Fig.29 , box 2908) and system integration ( Fig.29 , block 2910), which may include manufacturing and installing the landing gear 100. Thereafter, the aircraft 1000 may undergo certification and delivery ( Fig.29 , box 2912) to be put into use ( Fig.29 , block 2914). While in use, aircraft 1000 may be scheduled for routine maintenance and repair ( Fig.29 , block 2916). Routine maintenance and repair may include modification, reconfiguration, refurbishment, etc. of one or more systems of the aircraft 1000, which may include installation of the landing gear 100 as described herein.

[0066] Each process of the illustrative method 2900 may be performed or implemented by a system integrator, a third party, and / or an operator (e.g., a customer). For the purpose of this description, a system integrator may include, but is not limited to, any number of aircraft manufacturers and main system subcontractors; a third party may include, but is not limited to, any number of orderers, subcontractors, and suppliers; an operator may be an airline, a leasing company, a military entity, a service organization, etc.

[0067] The apparatus(es) and method(s) shown or described herein may be employed during any one or more stages of the manufacturing and repair method 2900. For example, corresponding to component and subassembly manufacturing ( Fig.29 , block 2908) may be similar to the components or subassemblies that were present when the aircraft 1000 was in service ( Fig.29 , block 2914) to produce a component or subassembly. Moreover, one or more instances of the apparatus (multiple apparatuses), method (multiple methods), or a combination thereof may be utilized during the production of the aircraft 1000, for example, by significantly speeding up the assembly of the aircraft 1000 or reducing the cost of the aircraft 1000. Similarly, one or more instances of the apparatus or method implementations or a combination thereof may be utilized, for example, but not limited to, when the aircraft 1000 is put into service ( Fig.29 , box 2914) and / or during maintenance and repair ( Fig.29 , box 2916).

[0068] According to aspects of the present disclosure, the following is provided:

[0069] A1. A landing gear, comprising:

[0070] an outer barrel rotatably coupled to a frame of the aircraft about a trunnion rotation axis;

[0071] a shock strut assembly movably coupled to the outer barrel for reciprocating movement along a longitudinal axis of the outer barrel; and

[0072] The contraction mechanism comprises:

[0073] a first retraction link member pivotally coupled to the outer cylinder,

[0074] a second telescoping link member coupling the first telescoping link member to the shock strut assembly,

[0075] a crank member pivotally coupled to the outer cylinder,

[0076] a drive member that couples the crank member to a walking beam (also called a retraction actuator beam) of a landing gear retraction mechanism, and

[0077] A driven member couples the crank member to the first contraction link member.

[0078] A2. The landing gear of paragraph A1, wherein:

[0079] The crank member pivots about a first axis of rotation; and

[0080] The first retraction link member pivots about a second rotational axis that is spaced apart from the first rotational axis along a longitudinal axis of the outer barrel.

[0081] A3. A landing gear as described in paragraph A2, wherein the first rotation axis and the second rotation axis are substantially parallel to each other.

[0082] A4. The landing gear of paragraph A2, wherein the drive member and the driven member extend substantially adjacent to each other along a longitudinal axis.

[0083] A5. The landing gear of paragraph A2, wherein the first rotation axis and the second rotation axis intersect each other.

[0084] A6. The landing gear of paragraph A1, further comprising:

[0085] a retract crank member coupled to the first retract link such that the retract crank member and the first retract link rotate as a unit; and

[0086] The driven member is coupled to the retract crank member to drive the rotation of the first retract link and achieve extension and retraction of the shock strut assembly relative to the outer cylinder and along the longitudinal axis.

[0087] A7. A landing gear as described in paragraph A6, wherein the first retraction link includes a first end and a second end, the first end of the first retraction link is rotatably coupled to the outer tube, the second end of the first retraction link is rotatably coupled to the second retraction link, and the retraction crank member is arranged adjacent to the first end of the first retraction link.

[0088] A8. The landing gear of paragraph A6, wherein the first retraction link includes a crank member receiver configured to receive the retraction crank member such that the retraction crank member is rotationally fixed relative to the first retraction link.

[0089] A9. The landing gear of paragraph A8, wherein the crank member receiver includes a polygonal surface, and the retraction crank member includes a mating polygonal surface coupled to the polygonal surface of the crank member receiver.

[0090] A10. The landing gear of paragraph A6, wherein at least a portion of the retraction crank member extends through the outer barrel.

[0091] A11. The landing gear of paragraph A1, further comprising:

[0092] a sensor actuator arm coupled to the first retraction link for rotation therewith; and

[0093] a sensor coupled to the outer barrel;

[0094] Wherein the sensor is configured to sense the sensor actuator arm when the shock strut assembly is extended.

[0095] A12. The landing gear of paragraph A11, wherein the sensor actuator arm includes a target and the sensor is a proximity sensor configured to sense the target.

[0096] A13. The landing gear of paragraph A1, wherein the outer barrel includes a retraction link cavity, and the first retraction link member and the second retraction link member are disposed within the retraction link cavity and enclosed by the outer barrel.

[0097] A14. The landing gear of paragraph A13, wherein the outer barrel includes a cover configured to enclose the first and second retract link members within the retract link cavity.

[0098] A15. The landing gear of paragraph A13, wherein the retraction link cavity includes a fluid drain hole.

[0099] A16. The landing gear of paragraph A1, wherein:

[0100] The first retracting link comprises a first end and a second end, the first end of the first retracting link is rotatably coupled to the outer cylinder, and the second end of the first retracting link is rotatably coupled to the second retracting link; and

[0101] The follower member is pivotally coupled to the first retract link adjacent the second end of the first retract link to drive rotation of the first retract link and effectuate extension or retraction of the shock strut assembly relative to the outer barrel and along the longitudinal axis.

[0102] A17. The landing gear as described in paragraph A1, wherein the driven member is coupled to the first retraction link so that under the push of the driving member, the second retraction link can be folded and unfolded relative to the first retraction link.

[0103] A18. The landing gear of paragraph A1, wherein one or more of the drive member and the driven member has an adjustable length.

[0104] A19. A landing gear as described in paragraph A1, wherein the outer barrel includes a first end and a second end, the first end of the outer barrel having the trunnion rotation axis, the second end of the outer barrel being longitudinally spaced apart from the first end of the outer barrel, and the crank member being pivotally coupled to the outer barrel between the first end of the outer barrel and the second end of the outer barrel.

[0105] A20. A landing gear as described in paragraph A1, wherein the outer barrel includes a first end and a second end, the first end of the outer barrel having the trunnion rotation axis, the second end of the outer barrel being longitudinally spaced apart from the first end of the outer barrel, and the crank member being pivotally coupled to the outer barrel at the second end of the outer barrel opposite the first end of the outer barrel relative to the trunnion rotation axis.

[0106] A21. The landing gear of paragraph A1, wherein the outer barrel includes a retraction link cavity, and the first retraction link member and the second retraction link member are disposed within the retraction link cavity.

[0107] A22. The landing gear of paragraph A21, wherein the retraction link cavity includes a fluid drain hole.

[0108] A23. The landing gear of paragraph A1, wherein the first retraction link member and the second retraction link member are rotatably coupled to each other so as to fold and unfold relative to each other and to be locked in an over-center position when unfolded.

[0109] A24. A landing gear as described in paragraph A23, wherein the outer barrel includes an eccentric stop surface, which is configured to couple with one or more of the first retract link member and the second retract link member to achieve eccentric locking of the first retract link member and the second retract link member.

[0110] A25. The landing gear of paragraph A1, further comprising:

[0111] a door pivotally coupled to the frame about a door pivot axis; and

[0112] A door drive member couples the door to the outer cylinder such that rotation of the outer cylinder about the trunnion rotation axis effects pivoting of the door about the door pivot axis.

[0113] A26. The landing gear of paragraph A1, further comprising:

[0114] a door pivotally coupled to the frame about a door pivot axis; and

[0115] A door drive member couples the door to the walking beam such that rotation of the outer cylinder about the trunnion rotation axis effects pivoting of the door about the door pivot axis.

[0116] A27. The landing gear of paragraph A1, wherein the outer barrel includes an inner cavity, and the shock strut assembly includes:

[0117] a diaphragm movably coupled to the inner cavity so as to form a first seal with the inner cavity, the diaphragm coupled to the retraction mechanism; and

[0118] an inner barrel movably coupled to both the inner cavity and the diaphragm so as to form a second seal with the inner cavity and such that the inner barrel is movable with the diaphragm relative to the outer barrel;

[0119] The retraction mechanism enables relative movement of the bulkhead and the inner barrel so that one of the two increases or decreases the length of the landing gear according to the corresponding deployed configuration or retracted configuration of the landing gear.

[0120] B1. A retraction mechanism for use with an aircraft landing gear, the landing gear comprising: an outer barrel rotatably coupled to a frame of the aircraft about a trunnion rotation axis; and a shock strut assembly movably coupled to the outer barrel for reciprocating movement along a longitudinal axis of the outer barrel, the retraction mechanism comprising:

[0121] a first retraction link member pivotally coupled to the outer cylinder,

[0122] a second telescoping link member coupling the first telescoping link member to the shock strut assembly,

[0123] a crank member pivotally coupled to the outer cylinder,

[0124] a drive member that couples the crank member to a walking beam (also called a retraction actuator beam) of a landing gear retraction mechanism, and

[0125] A driven member couples the crank member to the first contraction link member.

[0126] B2. The retraction mechanism as described in paragraph B1, wherein:

[0127] The crank member pivots about a first axis of rotation; and

[0128] The first retraction link member pivots about a second rotational axis that is spaced apart from the first rotational axis along a longitudinal axis of the outer barrel.

[0129] B3. A retraction mechanism as described in paragraph B2, wherein the first rotation axis and the second rotation axis are substantially parallel to each other.

[0130] B4. The retraction mechanism of paragraph B2, wherein the drive member and the driven member extend substantially adjacent to each other along a longitudinal axis.

[0131] B5. The retraction mechanism of paragraph B2, wherein the first rotation axis and the second rotation axis intersect each other.

[0132] B6. The retraction mechanism as described in paragraph B1 further includes:

[0133] a retract crank member coupled to the first retract link such that the retract crank member and the first retract link rotate as a unit; and

[0134] The driven member is coupled to the retract crank member to drive the rotation of the first retract link and achieve extension and retraction of the shock strut assembly relative to the outer cylinder and along the longitudinal axis.

[0135] B7. A contraction mechanism as described in paragraph B6, wherein the first contraction link includes a first end and a second end, the first end of the first contraction link is rotatably coupled to the outer cylinder, the second end of the first contraction link is rotatably coupled to the second contraction link, and the contraction crank member is arranged to be adjacent to the first end of the first contraction link.

[0136] B8. The retraction mechanism of paragraph B6, wherein the first retraction link includes a crank member receiver configured to receive the retraction crank member such that the retraction crank member is rotationally fixed relative to the first retraction link.

[0137] B9. The retraction mechanism of paragraph B8, wherein the crank member receiver includes a polygonal surface, and the retraction crank member includes a mating polygonal surface coupled to the polygonal surface of the crank member receiver.

[0138] B10. The retraction mechanism of paragraph B6, wherein at least a portion of the retraction crank member extends through the outer cylinder.

[0139] B11. The retraction mechanism as described in paragraph B1 further includes:

[0140] a sensor actuator arm coupled to the first retraction link for rotation therewith; and

[0141] a sensor coupled to the outer barrel;

[0142] Wherein the sensor is configured to sense the sensor actuator arm when the shock strut assembly is extended.

[0143] B12. The retraction mechanism of paragraph B11, wherein the sensor actuator arm includes a target and the sensor is a proximity sensor configured to sense the target.

[0144] B13. The retraction mechanism as described in paragraph B1, wherein the outer cylinder includes a retraction link cavity, and the first retraction link member and the second retraction link member are disposed in the retraction link cavity and enclosed by the outer cylinder.

[0145] B14. The retraction mechanism of paragraph B1, wherein:

[0146] The first retracting link comprises a first end and a second end, the first end of the first retracting link is rotatably coupled to the outer cylinder, and the second end of the first retracting link is rotatably coupled to the second retracting link; and

[0147] The follower member is pivotally coupled to the first retract link adjacent the second end of the first retract link to drive rotation of the first retract link and effectuate extension or retraction of the shock strut assembly relative to the outer barrel and along the longitudinal axis.

[0148] B15. The retracting mechanism as described in paragraph B1, wherein the driven member is coupled to the first retracting link so that under the push of the driving member, the second retracting link can be folded and unfolded relative to the first retracting link.

[0149] B16. The retraction mechanism of paragraph B1, wherein one or more of the drive member and the driven member has an adjustable length.

[0150] B17. A contraction mechanism as described in paragraph B1, wherein the outer cylinder includes a first end and a second end, the first end of the outer cylinder having the ear shaft rotation axis, the second end of the outer cylinder is longitudinally spaced apart from the first end of the outer cylinder, and the crank member is pivotally coupled to the outer cylinder between the first end of the outer cylinder and the second end of the outer cylinder.

[0151] B18. A contraction mechanism as described in paragraph B1, wherein the outer cylinder includes a first end and a second end, the first end of the outer cylinder having the ear shaft rotation axis, the second end of the outer cylinder is longitudinally spaced apart from the first end of the outer cylinder, and the crank member is pivotally coupled to the outer cylinder at the first end of the outer cylinder opposite to the ear shaft rotation axis at the second end of the outer cylinder.

[0152] B19. The retraction mechanism as described in paragraph B1, wherein the outer cylinder includes a retraction link cavity, and the first retraction link member and the second retraction link member are disposed in the retraction link cavity.

[0153] B20. The retraction mechanism of paragraph B1, wherein the first retraction link member and the second retraction link member are rotatably coupled to each other so as to be folded and unfolded relative to each other and locked in an over-center position when unfolded.

[0154] B21. A contraction mechanism as described in paragraph B20, wherein the outer cylinder includes an eccentric stop surface, and the eccentric stop surface is configured to couple with one or more of the first contraction link member and the second contraction link member to achieve eccentric locking of the first contraction link member and the second contraction link member.

[0155] C1. An aircraft comprising:

[0156] Framework; and

[0157] a landing gear coupled to the frame, the landing gear comprising:

[0158] an outer barrel rotatably coupled to the frame of the aircraft about a trunnion rotation axis;

[0159] a shock strut assembly movably coupled to the outer barrel for reciprocating movement along a longitudinal axis of the outer barrel; and

[0160] The contraction mechanism comprises:

[0161] a first retraction link member pivotally coupled to the outer cylinder,

[0162] a second telescoping link member coupling the first telescoping link member to the shock strut assembly,

[0163] a crank member pivotally coupled to the outer cylinder,

[0164] a drive member that couples the crank member to a walking beam (also called a retraction actuator beam) of a landing gear retraction mechanism, and

[0165] A driven member couples the crank member to the first contraction link member.

[0166] C2. An aircraft as described in paragraph C1, wherein:

[0167] The crank member pivots about a first axis of rotation; and

[0168] The first retraction link member pivots about a second rotational axis that is spaced apart from the first rotational axis along a longitudinal axis of the outer barrel.

[0169] C3. The aircraft of paragraph C2, wherein the first axis of rotation and the second axis of rotation are substantially parallel to each other.

[0170] C4. The aircraft of paragraph C2, wherein the driving member and the driven member extend substantially adjacent to each other along a longitudinal axis.

[0171] C5. The aircraft of paragraph C2, wherein the first rotation axis and the second rotation axis intersect each other.

[0172] C6. An aircraft as described in paragraph C1, further comprising:

[0173] a retract crank member coupled to the first retract link such that the retract crank member and the first retract link rotate as a unit; and

[0174] The driven member is coupled to the retract crank member to drive the rotation of the first retract link and achieve extension and retraction of the shock strut assembly relative to the outer cylinder and along the longitudinal axis.

[0175] C7. An aircraft as described in paragraph C6, wherein the first retraction link includes a first end and a second end, the first end of the first retraction link is rotatably coupled to the outer tube, the second end of the first retraction link is rotatably coupled to the second retraction link, and the retraction crank member is arranged adjacent to the first end of the first retraction link.

[0176] C8. The aircraft of paragraph C6, wherein the first retraction link includes a crank member receiver configured to receive the retraction crank member such that the retraction crank member is rotationally fixed relative to the first retraction link.

[0177] C9. The aircraft of paragraph C8, wherein the crank member receiver includes a polygonal surface, and the retracted crank member includes a mating polygonal surface coupled to the polygonal surface of the crank member receiver.

[0178] C10. The aircraft of paragraph C6, wherein at least a portion of the contraction crank member extends through the outer barrel.

[0179] C11. The aircraft of paragraph C1, further comprising:

[0180] a sensor actuator arm coupled to the first retraction link for rotation therewith; and

[0181] a sensor coupled to the outer barrel;

[0182] Wherein the sensor is configured to sense the sensor actuator arm when the shock strut assembly is extended.

[0183] C12. The aircraft of paragraph C11, wherein the sensor actuator arm includes a target and the sensor is a proximity sensor configured to sense the target.

[0184] C13. The aircraft of paragraph C1, wherein the outer barrel includes a retraction link cavity, and the first retraction link member and the second retraction link member are disposed within the retraction link cavity and enclosed by the outer barrel.

[0185] C14. The aircraft of paragraph C13, wherein the outer barrel includes a cover configured to enclose the first and second retract link members within the retract link cavity.

[0186] C15. The aircraft of paragraph C13, wherein the retraction link cavity includes a fluid drain hole.

[0187] C16. An aircraft as described in paragraph C1, wherein:

[0188] The first retracting link comprises a first end and a second end, the first end of the first retracting link is rotatably coupled to the outer cylinder, and the second end of the first retracting link is rotatably coupled to the second retracting link; and

[0189] The follower member is pivotally coupled to the first retract link adjacent the second end of the first retract link to drive rotation of the first retract link and effectuate extension or retraction of the shock strut assembly relative to the outer barrel and along the longitudinal axis.

[0190] C17. The aircraft of paragraph C1, wherein the driven member is coupled to the first retracting link so that under the push of the driving member, the second retracting link can be folded and unfolded relative to the first retracting link.

[0191] C18. The aircraft of paragraph C1, wherein one or more of the driving member and the driven member has an adjustable length.

[0192] C19. An aircraft as described in paragraph C1, wherein the outer barrel includes a first end and a second end, the first end of the outer barrel having the trunnion rotation axis, the second end of the outer barrel being longitudinally spaced apart from the first end of the outer barrel, and the crank member being pivotally coupled to the outer barrel between the first end of the outer barrel and the second end of the outer barrel.

[0193] C20. An aircraft as described in paragraph C1, wherein the outer barrel includes a first end and a second end, the first end of the outer barrel having the trunnion rotation axis, the second end of the outer barrel being longitudinally spaced apart from the first end of the outer barrel, and the crank member being pivotally coupled to the outer barrel at the second end of the outer barrel opposite the first end of the outer barrel relative to the trunnion rotation axis.

[0194] C21. The aircraft of paragraph C1, wherein the outer barrel includes a retraction link cavity, and the first retraction link member and the second retraction link member are disposed within the retraction link cavity.

[0195] C22. The aircraft of paragraph C21, wherein the retraction link cavity includes a fluid drain hole.

[0196] C23. The aircraft of paragraph C1, wherein the first retraction link member and the second retraction link member are rotatably coupled to each other so as to fold and unfold relative to each other and to be locked in an over-center position when unfolded.

[0197] C24. The aircraft of paragraph C23, wherein the outer barrel includes an eccentric stop surface configured to couple with one or more of the first retract link member and the second retract link member to achieve eccentric locking of the first retract link member and the second retract link member.

[0198] C25. The aircraft of paragraph C1, further comprising:

[0199] a door pivotally coupled to the frame about a door pivot axis; and

[0200] A door drive member couples the door to the outer cylinder such that rotation of the outer cylinder about the trunnion rotation axis effects pivoting of the door about the door pivot axis.

[0201] C26. The aircraft of paragraph C1, further comprising:

[0202] a door pivotally coupled to the frame about a door pivot axis; and

[0203] A door drive member couples the door to the walking beam such that rotation of the outer cylinder about the trunnion rotation axis effects pivoting of the door about the door pivot axis.

[0204] C27. The aircraft of paragraph C1, wherein the outer barrel includes an inner cavity, and the shock strut assembly includes:

[0205] a diaphragm movably coupled to the interior cavity to form a first seal with the interior cavity, the diaphragm coupled to the retraction mechanism; and

[0206] an inner barrel movably coupled to both the inner cavity and the diaphragm so as to form a second seal with the inner cavity and such that the inner barrel is movable with the diaphragm relative to the outer barrel;

[0207] The retraction mechanism enables relative movement of the bulkhead and the inner barrel so that one of the two increases or decreases the length of the landing gear according to the corresponding deployed configuration or retracted configuration of the landing gear.

[0208] D1. A method of operating a landing gear of an aircraft, the method comprising:

[0209] rotating the landing gear about a trunnion rotation axis, wherein the trunnion rotation axis is defined by an outer barrel of the landing gear; and

[0210] The shock strut assembly is moved relative to the outer barrel using a retracting mechanism, wherein the outer barrel at least partially surrounds the shock strut assembly, and the retracting mechanism comprises:

[0211] a first retraction link member pivotally coupled to the outer cylinder,

[0212] a second telescoping link member coupling the first telescoping link member to the shock strut assembly,

[0213] a crank member pivotally coupled to the outer cylinder,

[0214] a drive member that couples the crank member to a walking beam (also called a retraction actuator beam) of a landing gear retraction mechanism, and

[0215] A driven member couples the crank member to the first contraction link member.

[0216] D2. The method as described in paragraph D1, further comprising:

[0217] pivoting the crank member about a first axis of rotation; and

[0218] pivoting the first retraction link member about a second rotational axis spaced from the first rotational axis along a longitudinal axis of the outer barrel;

[0219] Wherein the first rotation axis and the second rotation axis are substantially parallel to each other.

[0220] D3. The method as described in paragraph D1 further includes:

[0221] pivoting the crank member about a first axis of rotation; and

[0222] pivoting the first retraction link member about a second rotational axis spaced from the first rotational axis along a longitudinal axis of the outer barrel;

[0223] Wherein the drive member and the driven member extend substantially adjacent to each other along a longitudinal axis.

[0224] D4. The method as described in paragraph D1, further comprising:

[0225] pivoting the crank member about a first axis of rotation; and

[0226] pivoting the first retraction link member about a second rotational axis spaced from the first rotational axis along a longitudinal axis of the outer barrel;

[0227] The first rotation axis and the second rotation axis intersect each other.

[0228] D5. The method as described in paragraph D1, further comprising:

[0229] coupling a retract crank member to the first retract link so that the retract crank member and the first retract link rotate as a unit; and

[0230] Rotation of the first retraction link is driven, wherein the driven member is coupled to the retraction crank member, and effects extension and retraction of the shock strut assembly relative to the outer barrel and along a longitudinal axis of the outer barrel.

[0231] D6. The method as described in paragraph D5, further comprising:

[0232] rotatably coupling a first end of the first retraction link to the outer cylinder; and

[0233] rotatably coupling the second end of the first retract link to the second retract link;

[0234] The retraction crank member is disposed adjacent to the first end of the first retraction link.

[0235] D7. The method of paragraph D5, wherein the first telescoping link includes a crank member receiver configured to receive the telescoping crank member such that the telescoping crank member is rotationally fixed relative to the first telescoping link.

[0236] D8. The method as described in paragraph D1, further comprising:

[0237] A sensor actuator arm is sensed with a sensor when the shock strut assembly is extended, wherein the sensor actuator arm is coupled to the first retract link for rotation with the first retract link and the sensor coupled to the outer barrel.

[0238] D9. The method described in paragraph D8 also includes using the sensor to sense a target of the sensor actuator arm, wherein the sensor includes a proximity sensor.

[0239] D10. The method of paragraph D1, wherein:

[0240] rotatably coupling a first end of the first retraction link to the outer barrel;

[0241] rotatably coupling the second end of the first retract link to the second retract link; and

[0242] Rotation of the first retract link is driven by a follower member pivotally coupled to the first retract link adjacent the second end of the first retract link and effects extension or retraction of the shock strut assembly relative to the outer barrel and along a longitudinal axis of the outer barrel.

[0243] D11. The method described in paragraph D1 further includes folding and unfolding the second retracting link relative to the first retracting link and the driven member coupled to the first retracting link under the push of the driving member.

[0244] D12. The method of paragraph D1, further comprising adjusting the length of one or more of the driving member and the driven member.

[0245] D13. The method of paragraph D1, further comprising pivotally coupling the crank member to the outer cylinder between a first end of the outer cylinder and a second end of the outer cylinder.

[0246] D14. The method described in paragraph D1 further includes pivotally coupling the crank member to the outer cylinder at a first end of the outer cylinder relative to the ear shaft rotation axis at a second end of the outer cylinder, wherein the first end of the outer cylinder has an ear shaft rotation axis and the second end of the outer cylinder is longitudinally spaced apart from the first end of the outer cylinder.

[0247] D15. The method of paragraph D1 further includes locking the first and second retract link members in an over-center position when deployed, wherein the first and second retract link members are rotatably coupled to each other so as to fold and unfold relative to each other.

[0248] D16. The method of paragraph D15, wherein the relative movement between the first retract link and the second retract link is prevented by an eccentric stop surface of the outer cylinder to achieve eccentric locking of the first retract link member and the second retract link member.

[0249] D17. The method as described in paragraph D1, further comprising:

[0250] pivotally coupling a door to a frame of the aircraft about a door pivot axis; and

[0251] The door is pivoted about the door pivot axis using a door drive member coupling the door to the outer barrel, wherein rotation of the outer barrel about the trunnion rotation axis effects pivoting of the door about the door pivot axis.

[0252] D18. The method as described in paragraph D1, further comprising:

[0253] pivotally coupling a door to a frame of the aircraft about a door pivot axis; and

[0254] The door is pivoted about the door pivot axis using a door drive member coupling the door to the walking beam, wherein rotation of the outer cylinder about the trunnion rotation axis effects pivoting of the door about the door pivot axis.

[0255] D19. The method of paragraph D1, wherein the outer cylinder includes an inner cavity, and the method further includes:

[0256] using the retraction mechanism to move both the bulkhead of the shock strut assembly and the inner barrel of the shock strut assembly to increase or decrease the length of the landing gear according to the respective deployed or retracted configuration of the landing gear; and

[0257] in:

[0258] The diaphragm is movably coupled to the inner cavity so as to form a first seal with the inner cavity, the diaphragm being coupled to the retraction mechanism; and

[0259] The inner barrel is movably coupled to both the inner cavity and the diaphragm to form a second seal with the inner cavity and to allow the inner barrel to move with the diaphragm relative to the outer barrel.

[0260] Furthermore, the present disclosure includes implementations according to the following clauses:

[0261] Clause 1. A landing gear (100A, 100B), comprising:

[0262] an outer barrel (110) rotatably coupled to a frame (1001) of an aircraft (1000) about a trunnion rotation axis (1002);

[0263] a shock strut assembly (120) movably coupled to the outer barrel (110) for reciprocating movement along a longitudinal axis (115) of the outer barrel (110); and

[0264] A contraction mechanism (130A, 130B), the contraction mechanism comprising:

[0265] a first retraction link member (140) pivotally coupled to the outer cylinder (110),

[0266] a second retract link member (150) coupling the first retract link member (140) to the shock strut assembly (120),

[0267] a crank member (160, 1560) pivotally coupled to the outer cylinder (110),

[0268] a drive member (170, 1570) coupling the crank member (160, 1560) to a walking beam (201) of a landing gear retraction mechanism (200), and

[0269] A follower member (180, 1580) couples the crank member (160, 1560) to the first contraction link member (140).

[0270] Clause 2. The landing gear (100A, 100B) of clause 1, wherein:

[0271] The crank member (160, 1560) pivots about a first axis of rotation (500, 705); and

[0272] The first retraction link member (140) pivots about a second rotation axis (501) that is spaced apart from the first rotation axis (500, 705) along a longitudinal axis (115) of the outer cylinder (110).

[0273] Clause 3. The landing gear (100A) as described in clause 1 or 2, further comprising:

[0274] a retraction crank member (190) coupled to the first retraction link member (140) such that the retraction crank member (190) and the first retraction link member (140) rotate as a unit; and

[0275] The driven member (180) is coupled to the contraction crank member (190) so as to drive the rotation of the first contraction link member (140) and realize the extension and retraction of the shock strut assembly (120) relative to the outer cylinder (110) and along the longitudinal axis (115).

[0276] Clause 4. A landing gear (100A) as described in Clause 3, wherein the first retraction link member (140) includes a first end (141) and a second end (142), the first end of the first retraction link is rotatably coupled to the outer tube (110), the second end of the first retraction link is rotatably coupled to the second retraction link member (150), and the retraction crank member (190) is arranged to be adjacent to the first end (141) of the first retraction link member (140).

[0277] Clause 5. A landing gear (100A) as described in clause 3 or 4, wherein the first retraction link member (140) includes a crank member receiver (193), the crank member receiver being configured to receive the retraction crank member (190) so that the retraction crank member (190) is rotationally fixed relative to the first retraction link member (140).

[0278] Clause 6. A landing gear (100B) as described in any one of clauses 1 to 5, wherein:

[0279] The first retracting link member (140) includes a first end (141) and a second end (142), the first end of the first retracting link member is rotatably coupled to the outer cylinder (110), and the second end of the first retracting link is rotatably coupled to the second retracting link member (150); and

[0280] The driven member (1580) is pivotally coupled to the first retract link member (140) adjacent to the second end (142) of the first retract link so as to drive the rotation of the first retract link member (140) and achieve extension or retraction of the shock strut assembly (120) relative to the outer cylinder (110) and along the longitudinal axis (115).

[0281] Clause 7. A landing gear (100A, 100B) as described in any of Clauses 1-6, wherein the first retraction link member (140) and the second retraction link member (150) are rotatably coupled to each other so as to fold and unfold relative to each other and lock in an eccentric position (900) when unfolded.

[0282] Clause 8. An aircraft (1000), comprising:

[0283] Framework (1001); and

[0284] A landing gear (100A, 100B), the landing gear being coupled to the frame (1001), the landing gear comprising:

[0285] an outer barrel (110) rotatably coupled to a frame (1001) of an aircraft (1000) about a trunnion rotation axis (1002);

[0286] a shock strut assembly (120) movably coupled to the outer barrel (110) for reciprocating movement along a longitudinal axis (115) of the outer barrel (110); and

[0287] A contraction mechanism (130A, 130B), the contraction mechanism comprising:

[0288] a first retraction link member (140) pivotally coupled to the outer cylinder (110),

[0289] a second retract link member (150) coupling the first retract link member (140) to the shock strut assembly (120),

[0290] a crank member (160, 1560) pivotally coupled to the outer cylinder (110),

[0291] a drive member (170, 1570) coupling the crank member (160, 1560) to a walking beam (201) of a landing gear retraction mechanism (200), and

[0292] A follower member (180, 1580) couples the crank member (160, 1560) to the first contraction link member (140).

[0293] Clause 9. The aircraft (1000) of clause 8, further comprising:

[0294] a sensor actuator arm (300) coupled to the first retract link member (140) to rotate together with the first retract link member (140); and

[0295] a sensor (310), the sensor being coupled to the outer cylinder (110);

[0296] The sensor (310) is configured to sense the sensor actuator arm (300) when the shock strut assembly (120) is extended.

[0297] Clause 10. The aircraft (1000) of clause 8 or 9, wherein the outer barrel (110) includes a retraction link cavity (113), and the first retraction link member (140) and the second retraction link member (150) are disposed in the retraction link cavity (113) and enclosed by the outer barrel (110).

[0298] Clause 11. The aircraft (1000) of Clause 10, wherein the outer barrel (110) includes a cover (114) configured to enclose the first retract link member (140) and the second retract link member (150) within the retract link cavity (113).

[0299] Clause 12. The aircraft (1000) of Clause 10 or 11, wherein the retraction link cavity (113) includes a fluid drain hole (116).

[0300] Clause 13. The aircraft (1000) of any one of clauses 8 to 12, further comprising:

[0301] a door (400) pivotally coupled to the frame (1001) about a door pivot axis (401); and

[0302] A door drive member (410) couples the door (400) to the outer cylinder (110) so that rotation of the outer cylinder (110) around the trunnion rotation axis (1002) enables pivoting of the door (400) around the door pivot axis (401).

[0303] Clause 14. The aircraft (1000) of any one of Clauses 8-13, wherein the outer barrel (110) includes an inner cavity (117), and the shock strut assembly (120) includes:

[0304] a diaphragm (123) movably coupled to the inner cavity (117) so as to form a first seal (124) with the inner cavity (117), the diaphragm (123) being coupled to the retraction mechanism (130A, 130B); and

[0305] an inner cylinder (125) movably coupled to both the inner cavity (117) and the diaphragm (123) so as to form a second seal (126) with the inner cavity (117) and to enable the inner cylinder (125) to move relative to the outer cylinder (110) together with the diaphragm (123);

[0306] The retraction mechanism (130A, 130B) realizes the relative movement of the partition (123) and the inner tube (125) so that one of them increases or decreases the length (1950) of the landing gear (100A, 100B) according to the corresponding deployment configuration or retraction configuration (800, 850) of the landing gear (100A, 100B).

[0307] Clause 15. A method of operating a landing gear (100A, 100B) of an aircraft (1000), the method comprising:

[0308] Rotating the landing gear (100A, 100B) about a trunnion rotation axis (1002), wherein the trunnion rotation axis (1002) is defined by an outer barrel (110) of the landing gear (100A, 100B); and

[0309] The shock strut assembly (120) is moved relative to the outer cylinder (110) by using a retracting mechanism (130A, 130B), wherein the outer cylinder (110) at least partially surrounds the shock strut assembly (120), and the retracting mechanism (130A, 130B) comprises:

[0310] a first retraction link member (140) pivotally coupled to the outer cylinder (110),

[0311] a second retract link member (150) coupling the first retract link member (140) to the shock strut assembly (120),

[0312] a crank member (160, 1560) pivotally coupled to the outer cylinder (110),

[0313] a drive member (170, 1570) coupling the crank member (160, 1560) to a walking beam (201) of a landing gear retraction mechanism (200), and

[0314] A follower member (180, 1580) couples the crank member (160, 1560) to the first contraction link member (140).

[0315] Clause 16. The method of clause 15, further comprising:

[0316] pivoting the crank member (160) about a first axis of rotation (500); and

[0317] causing the first retraction link member (140) to pivot about a second rotation axis (501) spaced apart from the first rotation axis (500) along a longitudinal axis (115) of the outer cylinder (110);

[0318] Wherein the first rotation axis (500) and the second rotation axis (501) are substantially parallel to each other.

[0319] Clause 17. The method according to clause 15 or 16, further comprising:

[0320] pivoting the crank member (160) about a first axis of rotation (500); and

[0321] causing the first retraction link member (140) to pivot about a second rotation axis (501) spaced apart from the first rotation axis (500) along a longitudinal axis (115) of the outer cylinder (110);

[0322] The drive member (170) and the driven member (180) extend substantially adjacent to each other along a longitudinal axis (115).

[0323] Clause 18. The method of clause 15, 16 or 17, further comprising:

[0324] pivoting the crank member (1560) about a first axis of rotation (705); and

[0325] causing the first retraction link member (140) to pivot about a second rotation axis (501) spaced apart from the first rotation axis (705) along a longitudinal axis (115) of the outer cylinder (110);

[0326] The first rotation axis (705) and the second rotation axis (501) intersect each other.

[0327] Clause 19. The method as described in any one of Clauses 15-18 also includes folding and unfolding the second retracting link member (150) relative to the first retracting link member (140) and the driven member (180, 1580) coupled to the first retracting link member (140) under the push of the driving member (170, 1570).

[0328] Clause 20. The method of any one of clauses 15-19, wherein the outer barrel (110) comprises an inner cavity (117), and the method further comprises:

[0329] using the retraction mechanism (130A, 130B) to move both the bulkhead (123) of the shock strut assembly (120) and the inner barrel (125) of the shock strut assembly (120) so as to increase or decrease the length (1950) of the landing gear (100A, 100B) according to the respective deployed or retracted configuration (800, 850) of the landing gear (100A, 100B); and

[0330] in:

[0331] The diaphragm (123) is movably coupled to the inner cavity (117) so as to form a first seal (124) with the inner cavity (117), and the diaphragm (123) is coupled to the retraction mechanism (130A, 130B); and

[0332] The inner cylinder (125) is movably coupled to both the inner cavity (117) and the partition (123) so as to form a second seal (126) with the inner cavity (117) and enable the inner cylinder (125) to move relative to the outer cylinder (110) together with the partition (123).

[0333] In the above-mentioned drawings, the solid lines (if any) connecting various elements and / or components can represent mechanical, electrical, fluid, optical, electromagnetic, wireless and other couplings and / or combinations thereof. As used herein, "coupling" means direct and indirect correlation. For example, component A can be directly associated with component B, or can be indirectly associated with it, for example, via another component C. It should be understood that it is not necessary to represent all relationships between various disclosed elements. Therefore, there may also be couplings other than those depicted in the drawings. The dotted lines (if any) connecting the boxes representing various elements and / or components represent couplings similar to those represented by solid lines in function and purpose; however, the couplings represented by dotted lines can be selectively provided or can relate to alternative examples of the present disclosure. Similarly, the elements and / or components (if any) represented by dotted lines represent alternative examples of the present disclosure. Without departing from the scope of the present disclosure, one or more elements shown by solid lines and / or dotted lines can be omitted from a specific example. Environmental elements (if any) are represented by dotted lines. For clarity, virtual (imaginary) elements can also be shown. Those skilled in the art will appreciate that some features shown in the drawings may be combined in various ways without including other features described in the drawings, other drawings, and / or the accompanying disclosure, even if such a combination or various combinations are not explicitly described herein. Similarly, additional features not limited to the examples presented may be combined with some or all of the features shown and described herein.

[0334] Refer to the above, Figure 27-Figure 29 In the present disclosure, boxes may represent operations and / or portions thereof, and the lines connecting the boxes do not imply any particular order or dependency of the operations or portions thereof. Boxes represented by dashed lines represent alternative operations and / or portions thereof. Dashed lines connecting the boxes (if any) represent alternative dependencies of operations or portions thereof. It should be understood that not all dependencies between the various disclosed operations are necessarily represented. Figure 27-Figure 29 The attached disclosures describing the operations of the methods described herein should not be construed as necessarily determining the sequence in which the operations must be performed. On the contrary, although an illustrative sequence is indicated, it should be understood that the sequence of operations can be modified when appropriate. Therefore, some operations can be performed in different orders or simultaneously. In addition, those skilled in the art will appreciate that not all described operations need to be performed.

[0335] In the foregoing description, many specific details are set forth to provide a thorough understanding of the disclosed concepts, which concepts may be implemented without some or all of these details. In other cases, details of known equipment and / or processes have been omitted to avoid unnecessarily obscuring the present disclosure. Although some concepts will be described in conjunction with specific examples, it should be understood that these examples are not intended to be limiting.

[0336] Unless otherwise indicated, the terms "first", "second", etc. are used herein merely as labels and are not intended to impose order, position, or hierarchical requirements on the items to which these terms refer. In addition, reference to, for example, a "second" item does not require or exclude the presence of, for example, a "first" or lower numbered item and / or, for example, a "third" or higher numbered item.

[0337] References herein to "an example" mean that one or more features, structures, or characteristics described in conjunction with the example are included in at least one implementation. The phrase "an example" in various places in the specification may or may not refer to the same example.

[0338] As used herein, a system, device, structure, article, element, component, or hardware that is "configured to" perform a specified function is actually capable of performing the specified function without any changes, rather than merely having the possibility of performing the specified function after further modification. In other words, a system, device, structure, article, element, component, or hardware that is "configured to" perform a specified function is specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing the specified function. As used herein, "configured to" means an existing characteristic of a system, device, structure, article, element, component, or hardware that enables the system, device, structure, article, element, component, or hardware to perform the specified function without further modification. For the purposes of this disclosure, a system, device, structure, article, element, component, or hardware that is described as "configured to" perform a particular function may additionally or alternatively be described as "suitable for" and / or "operable to" perform this function.

[0339] The different examples of the apparatus and methods disclosed herein include various components, features, and functions. It should be understood that the various examples of the apparatus and methods disclosed herein may include any components, features, and functions of any other examples of the apparatus and methods disclosed herein in any combination, and all of these possibilities are intended to fall within the scope of the present disclosure.

[0340] Many modifications of the examples set forth herein will come to mind to one skilled in the art to which this disclosure pertains having the benefit of the teachings presented in the foregoing descriptions and the associated drawings.

[0341] Therefore, it should be understood that the present disclosure is not limited to the specific examples shown, and modifications and other examples are intended to be included within the scope of the appended claims. In addition, although the foregoing description and related drawings describe examples of the present disclosure in the context of certain illustrative combinations of elements and / or functions, it should be appreciated that different combinations of elements and / or functions may be provided by alternative embodiments without departing from the scope of the appended claims. Therefore, the reference numerals in parentheses in the appended claims, if any, are presented for illustrative purposes only and are not intended to limit the scope of the claimed subject matter to the specific examples provided in the present disclosure.

Claims

1. A landing gear (100A, 100B), comprising: an outer barrel (110) rotatably coupled to a frame (1001) of an aircraft (1000) about a trunnion rotation axis (1002); a shock strut assembly (120) movably coupled to the outer cylinder (110) so as to reciprocate along a longitudinal axis (115) of the outer cylinder (110); as well as A contraction mechanism (130A, 130B), the contraction mechanism comprising: a first retracting link member (140) pivotally coupled to the outer cylinder (110), a second retract link member (150) coupling the first retract link member (140) to the shock strut assembly (120), a crank member (160, 1560) pivotally coupled to the outer cylinder (110), a drive member (170, 1570) coupling the crank member (160, 1560) to a walking beam (201) of a landing gear retraction mechanism (200), and a driven member (180, 1580) coupling the crank member (160, 1560) to the first contraction link member (140), Characterized in that the landing gear (100A, 100B) further comprises: a retraction crank member (190) coupled to the first retraction link member (140) such that the retraction crank member (190) and the first retraction link member (140) rotate as a unit; and The driven member (180) is coupled to the contraction crank member (190) so as to drive the rotation of the first contraction link member (140) and realize the extension and retraction of the shock strut assembly (120) relative to the outer cylinder (110) and along the longitudinal axis (115).

2. The landing gear (100A, 100B) according to claim 1, wherein: The crank member (160, 1560) pivots about a first rotation axis (500, 705); and The first retraction link member (140) pivots about a second rotation axis (501) that is spaced apart from the first rotation axis (500, 705) along the longitudinal axis (115) of the outer cylinder (110).

3. The landing gear (100A, 100B) according to claim 1, wherein the first retracting link member (140) includes a first end (141) and a second end (142), the first end of the first retracting link member being rotatably coupled to the outer barrel (110), the second end of the first retracting link member being rotatably coupled to the second retracting link member (150), and the retracting crank member (190) being disposed adjacent to the first end (141) of the first retracting link member (140).

4. The landing gear (100A, 100B) of claim 1, wherein the first retract link member (140) includes a crank member receiver (193) configured to receive the retract crank member (190) such that the retract crank member (190) is rotationally fixed relative to the first retract link member (140).

5. The landing gear (100A, 100B) according to claim 1 or 2, wherein: The first contraction link member (140) comprises a first end (141) and a second end (142), the first end of the first contraction link member being rotatably coupled to the outer cylinder (110), and the second end of the first contraction link member being rotatably coupled to the second contraction link member (150); and The driven member (1580) is pivotally coupled to the first retract link member (140) adjacent to the second end (142) of the first retract link member so as to drive the rotation of the first retract link member (140) and achieve extension or retraction of the shock strut assembly (120) relative to the outer cylinder (110) and along the longitudinal axis (115).

6. The landing gear (100A, 100B) according to claim 1 or 2, wherein the first retracting link member (140) and the second retracting link member (150) are rotatably coupled to each other so as to be folded and unfolded relative to each other and locked in an over-center position (900) when unfolded.

7. An aircraft (1000), comprising: Frame(1001); as well as The landing gear (100A, 100B) of any one of claims 1 to 6, coupled to the frame (1001).

8. The aircraft (1000) according to claim 7, further comprising: a sensor actuator arm (300) coupled to the first retract link member (140) to rotate together with the first retract link member (140); as well as a sensor (310), the sensor being coupled to the outer cylinder (110); The sensor (310) is configured to sense the sensor actuator arm (300) when the shock strut assembly (120) is extended.

9. The aircraft (1000) according to claim 7 or 8, wherein the outer barrel (110) comprises a retraction link cavity (113), and the first retraction link member (140) and the second retraction link member (150) are disposed in the retraction link cavity (113) and enclosed by the outer barrel (110).

10. The aircraft (1000) of claim 9, wherein the outer barrel (110) includes a cover (114) configured to enclose the first retract link member (140) and the second retract link member (150) within the retract link cavity (113).

11. The aircraft (1000) of claim 9, wherein the retraction link cavity (113) includes a fluid drain hole (116).

12. The aircraft (1000) according to claim 7 or 8, further comprising: a door (400) pivotally coupled to the frame (1001) about a door pivot axis (401); as well as A door drive member (410) couples the door (400) to the outer cylinder (110) so that rotation of the outer cylinder (110) around the trunnion rotation axis (1002) enables pivoting of the door (400) around the door pivot axis (401).

13. The aircraft (1000) of claim 7 or 8, wherein the outer barrel (110) includes an inner cavity (117), and the shock strut assembly (120) includes: a diaphragm (123) movably coupled to the inner cavity (117) so as to form a first seal (124) with the inner cavity (117), the diaphragm (123) being coupled to the retraction mechanism (130A, 130B); and an inner cylinder (125) movably coupled to both the inner cavity (117) and the partition (123) so as to form a second seal (126) with the inner cavity (117) and enable the inner cylinder (125) to move together with the partition (123) relative to the outer cylinder (110); The retraction mechanism (130A, 130B) realizes the relative movement of the partition (123) and the inner tube (125) so that one of the two increases or decreases the length (1950) of the landing gear (100A, 100B) according to the corresponding deployed configuration or retracted configuration (800, 850) of the landing gear (100A, 100B).

14. A method of operating a landing gear (100A, 100B) of an aircraft (1000) according to any one of claims 7 to 13, the method comprising: Rotating the landing gear (100A, 100B) about the trunnion rotation axis (1002), wherein the trunnion rotation axis (1002) is defined by the outer barrel (110) of the landing gear (100A, 100B); as well as The retraction mechanism (130A, 130B) is used to move the shock strut assembly (120) relative to the outer cylinder (110), wherein the outer cylinder (110) at least partially surrounds the shock strut assembly (120).

15. The method according to claim 14, further comprising: causing the crank member (160) to pivot about a first rotational axis (500); as well as causing the first retraction link member (140) to pivot about a second rotation axis (501), the second rotation axis (501) being spaced apart from the first rotation axis (500) along a longitudinal axis (115) of the outer cylinder (110); The first rotation axis (500) and the second rotation axis (501) are substantially parallel to each other.

16. The method according to claim 14 or 15, further comprising: causing the crank member (160) to pivot about a first rotational axis (500); as well as causing the first retraction link member (140) to pivot about a second rotation axis (501), the second rotation axis (501) being spaced apart from the first rotation axis (500) along a longitudinal axis (115) of the outer cylinder (110); The drive member (170) and the driven member (180) extend substantially adjacent to each other along the longitudinal axis (115).

17. The method according to claim 14, further comprising: causing the crank member (1560) to pivot about a first axis of rotation (705); as well as causing the first retraction link member (140) to pivot about a second rotation axis (501), the second rotation axis (501) being spaced apart from the first rotation axis (705) along the longitudinal axis (115) of the outer cylinder (110); The first rotation axis (705) and the second rotation axis (501) intersect each other.

18. The method according to claim 14 or 15, further comprising folding and unfolding the second retracting link member (150) relative to the first retracting link member (140) and the driven member (180, 1580) coupled to the first retracting link member (140) under the push of the driving member (170, 1570).

19. The method according to claim 14 or 15, wherein the outer cylinder (110) comprises an inner cavity (117), and the method further comprises: using the retraction mechanism (130A, 130B) to move both the bulkhead (123) of the shock strut assembly (120) and the inner barrel (125) of the shock strut assembly (120) so as to increase or decrease the length (1950) of the landing gear (100A, 100B) according to the respective deployed configuration or retracted configuration (800, 850) of the landing gear (100A, 100B); and in: The diaphragm (123) is movably coupled to the inner cavity (117) so as to form a first seal (124) with the inner cavity (117), and the diaphragm (123) is coupled to the retraction mechanism (130A, 130B); and The inner cylinder (125) is movably coupled to both the inner cavity (117) and the diaphragm (123) so as to form a second seal (126) with the inner cavity (117) and enable the inner cylinder (125) to move relative to the outer cylinder (110) together with the diaphragm (123).

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