• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    QUICK RELEASE SET AND AIRCRAFT LANDING TRAIN SET. The present invention relates to an aircraft landing gear torque rod element (11) (10) which includes a first end (20) for connection to a lower portion (16) or an upper portion (14) of the aircraft landing gear (10) and a second end (22) for connection to another torque rod element (11). A locking pin (32, 34) is arranged on one of the upper portion (14), the lower portion (16), the first end (20) or the second end (22). The locking pin (32, 34) is axially movable between an engaged position in which the pin (32, 34) projects for interconnection with a cooperating opening at the first end (20), the second end (22), the portion upper (14), the lower portion (16) or the second end (22) of the other torque rod element (11) and an undocked position. The locking pin (32, 34) is conditioned to the engaged position and movable against conditioning to the disengaged position.
    公开号:BR112013009394B1
    申请号:R112013009394-3
    申请日:2011-10-14
    公开日:2020-12-22
    发明作者:Charles T. O'connell
    申请人:Honda Patents & Technologies North America, Llc；
    IPC主号:
    专利说明:

    [001] The present description claims the benefit of U.S. Provisional Patent Application Serial No. 61 / 394,250, filed on October 18, 2010, which is incorporated by reference in its entirety here. BACKGROUND
    [002] The present description refers, in general, to a quick release set, and, more particularly, it refers to a quick release set for an aircraft undercarriage damper, although the quick release set is susceptible to other applications.
    [003] The front landing gear of an aircraft is typically comprised of an aircraft landing gear damper of the type that has an upper cylindrical part and a lower piston part received telescopically or mutually in the cylindrical part. The upper cylindrical part is connected to a lower side of an aircraft front. A wheel frame, where a landing wheel is rotatably mounted, is attached to the piston part. The relative movement between the lower piston portion and the upper cylindrical portion and, therefore, between the wheel and the aircraft, can be hydraulically or pneumatically controlled to provide damping characteristics that allow the damper to absorb shock on the ground when the aircraft is landing .
    [004] In such a landing gear, the landing wheel can be commanded by a pilot on the aircraft, as needed, to steer the aircraft after landing. In one example, a control device includes a steering ring over the cylindrical part. The steering ring is rotated by a steering actuator according to the command input provided by the pilot. A pair of torque rod elements connect the ring to the landing wheel and, in particular, to the wheel frame, to transmit steering command from the ring to the wheel. The torque rod elements prevent relative rotation between the ring and the wheel, while allowing reciprocal movement between the upper cylindrical portion and the wheel.
    [005] After landing, it is often desirable to disconnect the landing wheel from the steering ring and thus from the steering device to allow free rotation of the landing wheel. This can allow the aircraft to be maneuvered from the ground, such as when being pulled by a tractor or other land vehicle. To disconnect the landing wheel structure from the ring, the torque rod elements are usually disconnected, either one or the other or together from the cylindrical part or the piston part. A disconnect assembly may be provided in association with the torque rod elements to facilitate such disconnection from the torque rod elements; however, known disconnecting means or assemblies can be heavy, excessively complex, prone to missing parts, usually heavy or uncomfortable and / or liable to become obstacles when in a disconnected state (for example, a hanging rope). SUMMARY
    [006] According to one aspect, a quick release assembly includes a clamping structure that has at least two toothed portions, a tight structure and a locking pin arranged on each of the at least two toothed portions. The locking pin includes a cable part, a stationary cover attached to the toothed portion, a sliding tube that slides inside the stationary cover and together with the cable part between a docked and an undocked position and a spring that deflects the slide tube towards the docked position. A hole size of the stationary cover of the clamping structure and a bushing of the clamped structure are substantially the same size and a sectional area of a connecting side of the sliding tube is slightly smaller than the hole size of the stationary cover of the clamping structure and the tightened structure bushing.
    [007] According to another aspect, a quick release kit for an aircraft landing gear damper is provided. The damper has an upper portion and a lower portion that is telescopic and rotatable in relation to the upper portion. An upper torque rod element has a first end connected to the upper portion. A lower torque rod element has a first end connected to the lower portion. Second ends of the torque rod elements are connected together to prevent relative rotation between the upper and lower portions. The quick release assembly comprises a locking pin arranged on a first element, wherein the first element is one of the upper portion, the upper torque rod element, the lower torque rod element or the lower portion. A cooperating structure is arranged on a second element, the second element being another of the upper portion, the upper torque rod element, the lower torque rod element or the lower portion. The locking pin is axially driven into an engaged position, where the locking pin cooperates with the cooperation structure of the second element when the locking pin and the cooperation structure are aligned to connect the first and second elements together. The locking pin is axially movable against the impulse from the engaged position to an undocked position to disconnect the first and second elements.
    [008] According to yet another aspect, an aircraft landing gear assembly includes an upper portion, a telescopic lower portion and rotatably movable in relation to the upper part, an upper rod that has a first end connected to the upper portion and a second end and a lower torque rod that has a first end connected to the upper portion and a second end. The second ends of the upper and lower torque arms are connected together to prevent relative rotation between the upper and lower portions. The aircraft landing gear assembly further includes a quick release assembly that connects one of the first end of the upper torque rod and the top portion, the first end of the lower torque rod and the bottom or second end of the upper torque and the second end of the lower torque rod. The quick release assembly including a pin disposed on one of the first end of the upper torque rod, the top portion, the first end of the lower torque rod, the bottom portion, the second end of the upper torque rod or the second end of the lower torque rod.
    [009] The pin is slidably movable between an engaged position and an undocked position, with the pin propelled to the engaged position where the pin cooperates with a cooperation structure arranged on top of the first end of the upper torque rod, the upper portion , the first end of the lower torque rod, the lower portion, the second end of the upper torque rod or the second end of the lower torque rod, when the pin is aligned with the cooperation structure on it. The pin is manually movable against the impulse to the disengaged position for disconnecting said one from the first end of the upper torque rod, the upper portion, the first end of the lower torque rod, the lower portion, the second end of the torque rod upper or the second end of the lower torque rod from said other of the first end of the upper torque rod, the upper portion, the first end of the lower torque rod, the lower portion, the second end of the upper torque rod or the second end of the lower torque rod.
    [0010] According to an additional aspect, a torque rod element of the aircraft landing gear includes a first end for connection to a lower portion or an upper portion of the aircraft landing gear and a second end for connection to another torque rod element. A locking pin is arranged on either the first or the second end. The locking pin is axially movable between an engaged position where the pin protrudes for interconnection with a cooperative opening over one of the upper portion, the lower portion or the second end of the other torque rod element and an undocked position. The locking pin is deflected to the engaged position and movable against deflection to the disengaged position. BRIEF DESCRIPTION OF THE DRAWINGS
    [0011] FIG. 1 is a schematic elevational view of an aircraft light train having a lower portion connected to an upper portion of a pair of torque rod elements.
    [0012] FIG. 2 is a partial perspective view of an aircraft landing gear similar to FIG. 1, but including a quick release assembly disposed in a lower connecting portion and shown in a locking condition (i.e., connecting a lower of the torque rod elements to the lower portion).
    [0013] FIG. 3 is a sectional view of the lower connecting portion taken along line 3-3 of FIG. two.
    [0014] FIG. 4 is another sectional view similar to FIG. 3, but showing the first end of the lower torque rod element in an undocked condition (i.e., disconnected from the lower portion).
    [0015] FIG. 5 is a plan view of the lower torque rod element shown separately from the landing gear.
    [0016] FIG. 6 is a sectional view similar to FIG. 3 showing a quick release set according to an alternative mode.
    [0017] FIG. 7 is a plan view similar to FIG. 5 of a torque rod element with four teeth according to an alternative embodiment.
    [0018] FIG. 8 is a plan view similar to FIG. 5 of a torque rod element with three teeth according to another alternative embodiment.
    [0019] FIG. 9 is a plan view similar to FIG. 5 of a torque rod element with four teeth according to yet another alternative embodiment. DETAILED DESCRIPTION
    [0020] Referring now to the drawings in which, for purposes of illustration, one or more exemplary modalities are shown and not for the purpose of limiting them, FIG. 1 illustrates an aircraft landing gear or landing gear assembly generally designated by the reference numeral 10. The aircraft landing gear 10 is comprised of an aircraft landing gear damper 12 having an upper portion 14 and a lower portion 16, wherein the lower portion 16 is telescopic and rotatably movable with respect to the upper portion 14. The upper portion 14 is also connected to the lower portion 16 by a torque rod 11 which has a pair of torque rod elements 18 , 24 and three connection portions A, B, C.
    [0021] More particularly, the upper torque rod element 18 has a first end 20 and a second end 22. The first end 20 is connected to the upper portion 14 of the upper connecting portion A. The lower torque rod element 24 it also has a first end 26 and a second end 28. The first end 26 is connected to the lower portion 16 of the lower connecting portion C. The second ends 22, 28 of the torque rod elements 18, 22 are connected together in the lower portion. median connection B to prevent relative rotation between the upper and lower portions 14, 16. In the illustrated embodiment, the projection 52a of the steering ring 52 of the upper portion 14 and the first end 20 of the upper torque rod element 18 are connected together in the upper connecting portion A. The second end 22 of the upper torque rod element 18 and the second end 28 of the lower torque rod element 24 are connected together in the middle connection portion B. The first end 26 of the lower torque rod element 24 and the projection 56a of the wheel frame 56 of the lower portion 16 are connected together in the lower connection portion C.
    [0022] As will be described in greater detail below, the aircraft landing gear set 10 can include a quick release set (for example, the quick release set 30 shown in Fig. 2) that can be used in either or more of the three connection portions A, B, C. In particular, the quick release assembly 30 may be releasably connected to one of the first end 20 of the upper torque rod 18 and the upper portion 14, the first end 26 of the rod lower torque 24 and the lower end 16 and / or the second end 22 of the upper torque rod 18 and the second end 28 of the lower torque rod 24. In the illustrated embodiment, the quick release assembly is used in the lower connection portion C, as shown in Fig. 2, which can confer an advantage when compared to other configurations due to the fact that the configuration can prevent damage to other structures by the torque rod elements 18, 24.
    [0023] As will also be described in more detail below, the quick release assembly 30 may include a locking pin (for example, locking pins 32, 34 of FIG. 3) arranged on a first element, where the first element is one of the upper portion 14, the upper torque rod 18, the lower torque rod 24 or the lower portion 16 and a cooperation structure (for example, cooperation structures 36, 38 of Fig. 3) arranged on a second element , wherein the second element is another of the upper portion 14, the upper torque rod element 18, the lower torque rod element 24 or the lower portion 16. The locking pin can be axially driven into an engaged position, in that the locking pin cooperates with the cooperation structure of the second element when the locking pin and the cooperation structure are aligned (or two locking pins 32, 34 cooperate with two aligned cooperation structures 36, 38) to co Connect the first and second elements together. The locking pin can be axially movable against this deviation from the engaged position to an undocked position to disconnect the first and second elements.
    [0024] In the illustrated embodiment of Figs. 2-5, the first element is the lower torque rod element 24 and the second element is the lower portion 16. The lower torque rod element 24 includes a pair of locking pins 32, 34 and the lower portion 16 includes a pair of cooperation structures 36, 38 correspondent. Consequently, the locking pins 32, 34 are arranged on the lower torque rod element 24 and the cooperating structures 36, 38, which are configured to selectively receive the locking pins 32, 34 arranged on the lower portion 16. More specifically, in the embodiment illustrated in Figs. 2-5, locking pins 32, 34 are arranged on the first end 26 of the lower torque rod element 24. Alternatively, although not shown, a locking pin or pins can be arranged on the lower portion 16, the second end 28 of the lower torque rod element 24, the second end 22 of the upper torque rod element 18, the first end 20 of the upper torque rod element 18 or the upper portion 14.
    [0025] The locking pins 32, 34 of the illustrated modality are slidably movable between respective snapped or extended positions and respective snapped or retracted positions with the 32 pins, 34 pushed into their snapped positions. In particular, the pins 32, 34 can be moved manually against deflection to the undocked positions for disconnecting otherwise connected components. When in a locking condition (shown in Figs. 2 and 3), the pins 32, 34 of the lower torque rod element 24 are in their engaged positions and cooperatively fit into the cooperation structures 36, 38 arranged on the lower portion 16 to connect the lower torque rod element 24 and the lower portion 16. When in an undocked condition (shown in FIG. 4), pins 32, 34 are removed from the cooperating structures 36, 38 and the torque rod element lower torque 24 is removed from lower portion 16.
    [0026] To arrive from the locked condition to the undocked condition, the pins 32, 34 are forcibly displaced or pulled against the deviation (for example, the deviation by the springs 66) from their engaged positions to their undocked positions, thus allowing that the lower torque rod element 24 is moved away from the lower connecting portion C. Even in the disengaged condition, pins 32, 34 return to their engaged positions in the absence of sufficient force applied to prevent them from returning to their locked positions due to the deviation of pins 32, 34 to their locked positions. To reconnect the lower torque rod element 24 and the lower portion 16 (i.e., move from undocked to locked condition), pins 32, 34 are again forcibly retracted from their docked positions to their undocked positions, then , aligned with the cooperation structures 36, 38 and released to allow deviation to cooperatively fit pins 32, 34 with the cooperation structures 36, 38.
    [0027] When the locking pin or pins are arranged elsewhere, such as on the first end 26 of the upper torque rod element 18, the upper portion 14, the second end 22 of the upper torque rod element 18, the second end 28 of the lower torque rod element 24 or the lower portion 16, the cooperating structure or structures can be arranged on a counterpart of the upper portion 14, the first end 20 of the upper torque rod element 18, the second end 28 of the lower torque rod element 24, the second end 22 of the upper torque rod element 18 or the first end of the lower torque rod element 24. In these alternative configurations, the pin or pins can be manually movable for disconnection from one of the first end 20 of the upper torque rod element 18, the upper portion 14, the second end 22 of the upper torque rod element 18, the second end 28 of the lower torque rod element 24 or the lower portion 16 of said other of the upper portion 14, the first end 20 of the upper torque rod element 18, the second end 28 of the lower torque rod element 24, the second end 22 of the upper torque rod element 18 or the first end 26 of the lower torque rod element 24.
    [0028] As shown in FIG. 1, the upper portion 14 may include a cylinder 50 with a steering ring 52. The lower portion 16 may include a reciprocal or telescopic piston 54 received within or in relation to cylinder 50 of the upper portion 14. The wheel frame or fork 56 can be fixedly attached to piston 54 for movement with piston 54 and thus in reciprocal relationship with the upper portion 14. The wheel frame or fork 56 can rotatively support a wheel 58. As shown, the torque rod 11, comprised of the torque rods 18, 24, connects the steering ring 52 to the wheel frame 56 to transmit steering forces from the steering ring 52 to the fork 56 to drive the wheel 58. In particular, when the oriented direction of the steering ring 52 is controlled by a steering actuator 60, this direction is transmitted through the rods 18, 24 to the wheel frame 56 and the wheel 58. The rods 18, 24 transmit such steering forces, while allowing a relative reciprocal movement of the wheel frame 56 and the wheel 58 through piston 54 (i.e., in relation to the upper portion 14).
    [0029] Sometimes, however, it is desirable to disconnect the wheel frame 56 from the torque rod 11 to allow free rotation of the wheel frame 56 and that the wheel 58 rotates freely in relation to the upper portion 14 and, in particular, the ring steering wheel 52. For example, free steering of wheel 58 could be desired after landing, when the aircraft is being towed by a tractor or other land vehicle. This can be provided by providing a removable connection (for example, in one or more of the connection portions A, B or C) for the rods 18, 24 and such removable connection can be facilitated via the quick release assembly 30 described herein.
    [0030] In the embodiment in Figures 2-5, the quick release assembly 30 is provided on the lower torque rod 24 at the first end 26 thereof. As best shown in FIG. 5, the lower torque rod 24 is configured as a frame or fork with two teeth at the first end 26 which has first and second spaced fork arms 62, 64 and, consequently, the end 26 can be referred to as a toothed or toothed end . The quick release assembly 30 of this embodiment includes two pins, that is, locking pins 32, 34. The first locking pin 32 is placed on the first rod 62 and the second locking pin 34 is placed on the second rod 64. In this configuration, pins 32, 34 protrude towards each other when in their respective engaged positions and are disengaged from each other (i.e., separated) when moved to their respective disengaged positions. Consequently, the lower torque rod 24, and particularly the forked end 26, is configured as a clamping structure.
    [0031] The lower portion 16 includes the cooperation structures 36, 38 which are configured to receive, cooperatively, the pins 32, 34. In particular, the lower portion 16 has a projection or projection portion 56a formed on the frame wheel 56. In the illustrated embodiment, the projection portion 56a is formed as a structure with a single tooth that is sandwiched or clamped between the end of the fork with two teeth 26 comprised on the arms 62, 64. Consequently, the portion of projection 56a may alternatively be referred to as a tight frame. Of course, as will be appreciated by those skilled in the art, the protrusion portion 56a need not be limited to being formed as a single tooth structure and could alternatively be formed as a toothed structure (for example, a two tooth structure ). Likewise, the clamping structure (i.e., the lower torque rod 24) and, in particular, the two-toothed end 26 thereof, need not be limited to being formed as a two-toothed structure and could, alternatively , be formed as a structure with a single tooth or three or more teeth.
    [0032] Examples of torque rod elements having alternative toothed structures (for example, clamping structures with at least three teeth) are illustrated in FIGS. 7-9. In particular, the torque rod or clamping structure 24 'shown in FIG. 7 includes four teeth 24a ', 24b', 24c 'and 24d' 'suitable for cooperatively fitting into a cooperation structure or tight structure with two or three teeth 25'. The torque rod or clamping structure 24 '' shown in FIG. 8 includes three teeth 24a '', 24b "and 24c '' suitable to fit cooperatively in a tight or cooperative structure with two teeth 25 ''. Similar to Fig. 7, the torque rod or clamping structure 24 '' ' illustrated in Fig. 9 includes four teeth 24a '' ', 24b' '', 24c '' 'and 24d' '' suitable for cooperatively fitting into a clamping or cooperating structure with three 25 '' teeth. other than those illustrated are possible and are considered within the scope of this description.
    [0033] Also, in the illustrated embodiment, the locking pins 32, 34 are each continuously pushed into their respective locked positions (that is, the positions shown in FIGS. 3 and 4), by helical springs 66. The locking pins 32, 34 are pushed into their spring-loaded position 66 even when the torque rod element 24 is disconnected from the lower portion 16 (that is, even when the lower torque rod element 24 is disconnected from the protrusion 56a) . The pins 32, 34 are axially movable between their engaged positions, with the pins 32, 34 projecting for interconnection with the cooperation structures 36, 38 on the projection 56a of the lower portion 16 and the undocked positions, in which the lower torque rod 24 can be disconnected from the lower portion 16 (or reconnected together). Helical springs 66 deflect locking pins 32, 34 to their engaged positions, but pins 32, 34 are movable against deflection of helical springs 66, such as by a manually applied thrust force, to their disengaged positions. The springs 66 can each have sufficient spring force to return the respective pins 32, 34 to the engaged position whenever an insufficient external force (or no force) is applied to the pins 32, 34.
    [0034] As shown, each of the locking pins 32, 34 of the illustrated embodiment has an insertion end 70 capable of being received in a corresponding cooperation structure 36, 38 when the pins 32, 34 are in their locked positions. The cooperation structures 36, 38 are defined by and / or on the projection 56a. More particularly, in the illustrated embodiment, the projection 56a includes a through hole 72. At each end of the through hole 72, sleeve-type bushings 74 are partially received in the through hole 72 to provide a locking surface for the pins 32, 34. The bushings 74 of the illustrated embodiment include a shaft part 74a received in through hole 72 and a head part 74b for seating the bush 72 against the protrusion 56a. The shaft part 74a defines a hole 75 in which the corresponding pin 32 or 34 is slidably received when pins 32, 34 are engaged. Naturally, it will be appreciated by those skilled in the art that cooperation structures 36, 38 can have alternative configurations (for example, through hole 72 can be replaced by two different holes or recesses, the receiving openings for pins 32, 34 can formed by a sleeve-like wall extending out of the projection 56a, etc.).
    [0035] Opposite the insertion end 70, the locking pins 32, 34 can each include a cable or cable portion 78 to facilitate pulling the locking pins 32, 34 manually from the engaged positions to the undocked positions against the spring thrust 66. The spring force 66 can be adjusted or configured so that locking pins 32, 34 connect connection portion C firmly and cable portions 78 can be pulled by human force when the connection C is detached. Cable portions 78 allow relatively easy handling of pins 32, 34.
    [0036] The locking pins 32, 34 illustrated are configured in such a way that the first or inner ends 66a of the springs 66 act against radial flanges 80 of the locking pins 32, 34. The flanges 80 move with their respective locking pins 32, 34. Seconds or outer ends 66b of the springs 66 act against respective head portions 82 of the torque rod element 24, which do not move with the locking pins 32, 34. More specifically, a sliding tube 84 may depend annularly of the radial flange 80 to define an annular space 86 radially around each pin 32, 34. Once the sliding tube 84 is connected or mounted to its respective pin 32, 34 and moves with it, the sliding tube 84 it can be referred to as an annular movement wall or movable sliding tube. Head portions 82 form seating locations against which the cable portions 78 of pins 32, 34 can rest when in the engaged position.
    [0037] A cap 88 or bushing 88, which includes the head portion 82 in the illustrated embodiment, has a wall portion 90 that depends anually on the head portion 82 to better define the annular space 86. The wall portion 90 is received through an opening 91 defined in each of the arms 62, 64. The diameter of the openings 91 defined in the arms 62, 64 can be the same or substantially the same as the diameter of the through hole 72 defined in the projection 56a of the wheel frame 56. An internal surface of the wall part 90 defines a hole 93 in which the sliding tube 84 is received in a sliding manner. A hole size of stationary cover 88 (i.e., hole size of hole 93) and a hole size of chuck 74 (i.e., hole size of hole 75) can be substantially the same size, while sectional area or outer diameter of the sliding tube 84 can be almost the same or slightly smaller than the diameter of the stationary cover 88 and the bushing 74 to facilitate relative sliding of the sliding tube 84.
    [0038] The cap 88 also includes a face 92 of the bushing disposed an axial end opposite the side of the head part 82. The face of the bushing 92 rests against the lower torque rod 24 (i.e., one of the arms 62, 64) to securely attach stationary cover 88 on each pin 32, 34 to its corresponding arm 62, 64. Cover 88, which is mounted or connected to its corresponding arm 62, 64, can be referred to as a fixed annular wall or a stationary cover . The face of the bushing 92 can be welded or otherwise fixed to the arms 62 or 64 to fix the stationary cover 88 to the arm 62 or 64. Naturally, as will be appreciated by those skilled in the art, the cover 88 can have other configurations and / or it can be attached to the arms 62, 64 in other ways. In the illustrated embodiment, the face of the bushing 92 engages and thus forms a contact chamber for the bushing 74 on the corresponding protrusion 56a.
    [0039] The cover 88 can have two functions. One can be housing and guiding function for sliding tube 84. In particular, cap 88 provides a housing for sliding tube 84 and also provides a guiding surface for guiding the sliding movement of sliding tube 84 within stationary cap 88. The sliding tube 84 is received telescopically within the stationary cover 88 to define the annular space 86 as an annularly closed space and moves telescopically with respect to it when the respective pin 32, 34 is moved between its engaged and disengaged positions. In particular, the spring 66 is received in the annular space 86 around pin 32 or 34 and is thus completely enclosed or surrounded by a housing formed by pin 32 or 34, the sliding tube 84 and the stationary cap 88. Another function it is a seating function for the spring 66, which allows the spring 66 to condition or propel the sliding tube 84 into the engaged position. In particular, the head portion 82 of the cap 88 constitutes a wall surface from which the spring 66 can exert a spring force on the sliding tube 84.
    [0040] With reference to FIG. 3, the sliding tube 84 which has a radial flange 80 and the opening 80a fits over a pin point 94 and is seated against a shoulder 96 of the respective pin 32, 34. A nut 100 is threaded on the tip 94 to firmly secure the sliding tube 84 and the pin 32 or 34 together. As shown, the sliding tube 84 can include the insertion end 70 that annules the nut 100 and the tip 94. The hole sizes of through hole 72 and openings 91, which can be substantially the same, may be slightly larger than than the sectional area of the insertion end 70 and the sliding tube 84.
    [0041] The sliding tube 84 can act as a bushing for the cooperation structures 36 or 38, as described in more detail below and can additionally constitute a support surface on which a grease or other lubricant can be provided to facilitate movement sliding between bushing 74 and stationary cover 88 and, more generally, between pins 32, 34 and respective arms 62, 64. As shown, lubrication fittings 102 in FIG. 4 can be provided on the arms 62, 64 with a corresponding passage (not shown) for insertion or forcing a grease on the outer surface of the sliding tube 84 (ie the surface that rests against or moves in relation to the stationary cover 88) .
    [0042] Locking pins 32, 34 in their locked positions and in cooperation or interconnection with the cooperation structures 36, 38, connect the lower torque rod element 24 and the lower portion 16 together and form a rotating union in the portion lower connecting link C, allowing relative rotation between the lower torque rod element 24 and the lower portion 16. In particular, an axis of each of the pins 32, 34 forms a rotary axis between the first end 26 of the torque rod lower 24 and lower portion 16, in particular the projection 56a thereof. Similarly, if the locking pins are arranged between the upper portion 14 and the first end 20 of the upper torque rod 18 or between the second ends 22, 28 of the torque rods, the pins 32, 34 will form rotating connections on their axes between these components (ie, in connection portions A and B). In the embodiment of Figs. 2-5, both pins 32, 34, which are arranged so that their respective axes are collinear with respect to each other, form a rotating connection between the lower torque rod 24 and the lower portion 16.
    [0043] Unlike quick release mechanisms of the prior art, spring 66 deflects locking pins 32, 34 in the engaged positions. That is, except for the movement from the engaged to the disengaged position, the locking pins 32, 34 are not otherwise removable from the torque rod element 24. This represents a compact assembly because the engaging / disengaging structures are placed in the arm housing 62, 64 efficiently. In addition, the present invention does not allow locking pins 32, 34 to be loosened by means of stop structures by the sliding tube 84 and the cap head part 88 beyond the spring force of spring 66 or otherwise inconvenient for the user. This is advantageous in that the device is self-contained and remains self-contained even when pins 32, 34 are in their respective undocked positions. There are also no loose parts (for example, a hanging rope) that will become lost or damaged or cause damage to other landing gear structures. An additional advantage is that the same number or a smaller number of parts are required compared to devices of the connection of the prior art which, ultimately, results in a reduction in weight and cost. Furthermore, operation of the quick release assembly 30 requires only pulling the pins 32, 34 when disconnecting the connection portion C. The fitting and detaching operation of the present invention is very easy for the user. In contrast, some conventional locking pins require the user to press a button on a locking pin and then pull the pin from the connecting part.
    [0044] With reference to FIG. 6, a quick release assembly 30 'is shown according to an alternative embodiment. Except as indicated below, the quick release set 30 'can be the same as the quick release set 30 discussed above. Therefore, just like reference numbers are used to identify similar parts and like reference numbers with a main symbol are used to identify similar matching parts. The main difference between the quick clamping set 30 'and the quick closing set 30 is the use of a conical interface between the 32-pin', 34 'and the cooperation structures 36', 38 'in the quick-release set 30' . In the quick release assembly 30, the insertion end 101 of the sliding tube 84 has a generally cylindrical outer profile which cooperates with a corresponding generally cylindrical inner profile of the wall bushing portions 74a. In contrast, the quick release assembly 30 'has 70' end insertion of the sliding tubes 84 'with a tapered outer profile that cooperates with an inner tapered profile of the 74a wall portion ". As a result, the sliding tube 84' to 66 for the corresponding bushings springs 74 'to block the connecting portion. Due to the coupling plugs, a gap between the sliding tubes 84' and the corresponding bushings 74 'is reduced by the force of the springs at 66' and the connection is more firmly fixed without space.The cone angle (or the use of any taper) can be adjusted to control the freedom of movement between the articulated components (ie between the 32 pins ', 34' and the cooperation structures 36 ', 38'). The present invention makes the stem 62, 64 and 56a of the shoulder easy to align when connecting connection 24 and the shoulder 56a.
    [0045] Although the quick release assemblies described here have been described with reference to aircraft landing gear, it will be appreciated that these could be used as a general connection structure in other applications and environments. In addition, it will be appreciated that several of the features described above and other aspects and functions or alternatives or varieties thereof, can be desirably combined in many other different systems or applications. Also, that various presently unforeseen alternatives, modifications, variations or improvements can subsequently be made by those skilled in the art, which are also intended to be covered by the following claims.
    权利要求:
    Claims (14)
    [0001]
    1. Quick-release assembly comprising: a clamping structure that has at least two toothed portions; a tight structure having at least one bushing (74) which defines a bushing hole (75) and a locking pin (32, 34) arranged in each of the at least two toothed portions, the locking pin (32, 34 ) including a spring (66, 66a), characterized by the fact that the locking pin (32, 34) includes a cable portion (78), a stationary cover (88) attached to the toothed part and having a stationary cover hole (93), a sliding tube (84) that slides inside the stationary cover (88) and together with the cable portion (78) between an engaged position and an undocked position, in which the spring (66, 66a) deflects the sliding tube (84) towards the engaged position; and in which hole sizes of the stationary cover hole (93) of the stationary cover (88) of the clamping structure and the chuck hole (75) of the at least one chuck (74) of the clamped structure are substantially the same size and one the sectional area of one connecting side of the sliding tube (84) is slightly smaller than the hole size of the stationary cover (88) of the clamping structure and the bushing (74) of the clamped structure.
    [0002]
    2. Quick-release assembly according to claim 1, characterized in that the sliding tube (84) and the tight structure bushing are tapered to fit cooperatively with each other when each locking pin (32, 34) is in the docked position.
    [0003]
    3. Quick release assembly according to claim 1, characterized in that the clamping structure has at least one portion with three teeth and the clamping structure has at least one portion with two teeth and the locking pins ( 32, 34) are arranged on both sides of the clamping structure.
    [0004]
    4. Quick release assembly according to claim 3, characterized in that the clamping structure has a portion with four teeth and the clamping structure has a portion with three teeth.
    [0005]
    5. Quick release assembly according to claim 1, characterized in that the clamping structure is placed on a first end and / or a second end of a lower torque rod of a landing gear shock absorber. aircraft (12), the tight frame is placed on a protrusion (56a) of a wheel frame and / or a second end of an upper torque rod (24) of the aircraft's landing gear damper (12).
    [0006]
    6. Quick-release assembly according to claim 1, characterized in that the clamping structure is placed on a first end and / or a second end of the upper torque rod (24) of a train damper. landing of the aircraft (12), the tight structure is placed on a protrusion (56a) of a ring (52) and / or a second end of a lower torque rod (24) of the aircraft landing gear damper (12) .
    [0007]
    7. Quick-release assembly according to claim 1, characterized by the fact that it is in combination with an aircraft landing gear damper, the damper has an upper portion (14) and a lower portion (16) that is telescoping and rotatingly movable with respect to the upper portion (16), an upper torque rod element (18) has a first end (20) connected to the upper portion (14), a lower torque rod element (24) has a first end (26) connected to the lower portion (16), second ends (22, 28) of the torque rod elements (18, 24) are connected together to prevent relative rotation between the upper and lower portions (14, 16), wherein the tight structure is one of the upper portion (14), the upper torque rod element (18), the lower torque rod element (24) or the lower portion (16), and the tight structure is another between the upper portion (14), the upper torque rod element (18), the lower torque rod element (24) or the lower portion (16); and where the locking pin (32, 34) is axially driven into the engaged position, where the locking pin (32, 34) cooperates with the tightened structure when the locking pin (32, 34) and the tightened structure are aligned to connect the clamping structure and the clamped structure together, the locking pin (32, 34) axially movable against deflection from the engaged position to the disengaged position to disconnect the clamping structure and the tightened structure.
    [0008]
    8. Aircraft landing gear set, characterized by the fact that it comprises: an upper portion (14); a lower portion (16) telescopic and rotatably movable with respect to the upper portion (14); an upper torque rod (18) having a first end (20) connected to the upper portion (14) and a second end (22); a lower torque rod (24) having a first end (26) connected to the lower portion (16) and a second end (28), the second ends (22, 28) of the upper and lower torque rods (18, 24 ) connected together to prevent relative rotation between the upper and lower portions (14, 16); and a quick release assembly that connects one of the first end (20) of the upper torque rod (18) and the upper portion (14), the first end (26) of the lower torque rod (24) and the lower portion (16) or the second end (22) of the upper torque rod (18) and the second end (28) of the lower torque rod (24), the quick release assembly including: a locking pin (32, 34) disposed on one of the first end (20) of the upper torque rod (18), the upper portion (14), the first end (26) of the lower torque rod (24), the lower portion (16), the second end (22) of the upper torque rod (18) or the second end (28) of the lower torque rod (24), the locking pin (32, 34) slidably movable between an engaged position and an undocked position, with the locking pin (32, 34) driven into the engaged position, where the locking pin (32, 34) cooperates with a cooper structure action (36, 38) disposed in another among the first end (20) of the upper torque rod (18), the upper portion (14), the first end (26) of the lower torque rod (24), the lower portion (16), the second end of the upper torque rod (18) or the second end of the lower torque rod (24) when the locking pin is aligned with the cooperating structure (36, 38); and the locking pin (32, 34) manually movable against the thrust to the disengaged position to disconnect one of the first end (20) of the upper torque rod (18), the upper portion (14), the first end of the rod lower torque (24), the lower portion (16), the second end of the upper torque rod or the second end of the lower torque rod (24) of said other among the first end (20) of the upper torque rod, the upper portion (14), the first end of the lower torque rod (24), the lower portion (16), the second end of the upper torque rod (18) or the second end of the lower torque rod (24). wherein the locking pin (32, 34) includes a cable portion (78), a stationary cover (88), a sliding tube (84) that slides inside the stationary cover and together with the cable portion between the engaged position and undocked position and a spring (66, 66a) that axially pushes the locking pin to the engaged position, the spring received radially within the slide tube and completely enclosed within the cable portion and the slide tube.
    [0009]
    9. Aircraft landing gear assembly according to claim 8, characterized by the fact that an axis of the locking pin (32, 34) forms a rotary axis between said one of the first end (20) of the upper torque (18), the upper portion (14), the first end (26) of the lower torque rod (24), the lower portion (16), the second end of the upper torque rod (18) or the second end of the lower torque rod (24) and another of said first end (20) of the upper torque rod (18), the upper portion (14), the first end of the lower torque rod (24), the lower portion (16 ), the second end of the torque rod (18) or the second end of the lower torque rod (24).
    [0010]
    10. Aircraft landing gear assembly according to claim 8, characterized by the fact that the hole size (93) of the stationary cover (88) and a bushing (88) of the cooperation structure (36, 38) are substantially the same size and a sectional area on one connecting side of the sliding tube (84) is slightly smaller than the hole size (93) of the stationary cover (88) and the bushing (88) of the cooperation structure (36 , 38).
    [0011]
    11. Aircraft landing gear assembly according to claim 8, characterized by the fact that the sliding tube (84) and the bushing (88) of the cooperation structure (36, 38) are tapered to fit one in another cooperatively when the locking pin (32, 34) is in the engaged position.
    [0012]
    12. Aircraft landing gear assembly according to claim 8, characterized in that a first element has at least a portion with three teeth and a second element has at least a portion with two teeth and the locking pin (32, 34) is one of two locking pins (32, 34) disposed on both sides of the first element. where the first element is one of the upper portion (14), the upper torque rod (18), the lower touch rod (24) or the lower portion (16), and where the second element is another among the upper portion (14), the upper torque rod (18), the lower touch rod (24) or the lower portion (16).
    [0013]
    13. Aircraft landing gear assembly according to claim 12, characterized in that the first element has a portion with four teeth and the second element has a portion with three teeth.
    [0014]
    14. Aircraft landing gear assembly according to claim 11, characterized by the fact that it also includes: a second locking pin (34) disposed on the first element; a second cooperation structure (38) arranged on the second element; the second locking pin (34) axially driven into an extended position, wherein the second locking pin (34) cooperates with the second cooperating structure (38) of the second element when the second locking pin (34) and the second cooperation structure (38) are aligned to connect the first and second elements together, the second locking pin (34) axially movable against deviation from the extended position to a retracted position, the first and second locking elements (32, 34) in the retracted positions allowing disconnection of the first and second elements, where the first element is one of the upper portion (14), the upper torque rod (18), the lower touch rod (24) or the lower portion (16), and wherein the second element is another among the upper portion (14), the upper torque rod (18), the lower touch rod (24) or the lower portion (16).
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    同族专利:
    公开号 | 公开日
    CA2814491A1|2012-04-26|
    US20120132742A1|2012-05-31|
    BR112013009394A2|2016-07-26|
    JP2014504224A|2014-02-20|
    CN103596843A|2014-02-19|
    MX2013004324A|2013-09-02|
    WO2012054360A3|2013-10-24|
    US9120566B2|2015-09-01|
    EP2630036A4|2015-04-08|
    CA2814491C|2019-05-14|
    EP2630036A2|2013-08-28|
    MX341498B|2016-08-22|
    EP2630036B1|2018-03-28|
    CN103596843B|2017-04-26|
    JP6158706B2|2017-07-05|
    WO2012054360A2|2012-04-26|
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    法律状态:
    2018-12-26| B06F| Objections, documents and/or translations needed after an examination request according art. 34 industrial property law|
    2019-11-26| B06U| Preliminary requirement: requests with searches performed by other patent offices: suspension of the patent application procedure|
    2020-09-08| B09A| Decision: intention to grant|
    2020-12-22| B16A| Patent or certificate of addition of invention granted|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 14/10/2011, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US39425010P| true| 2010-10-18|2010-10-18|
    US61/394,250|2010-10-18|
    PCT/US2011/056483|WO2012054360A2|2010-10-18|2011-10-14|Quick release assembly for aircraft landing gear|
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