JP2012061984A - Leg device for aircraft - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a leg device for aircraft, in which seal member exchanging work is efficiently carried out in a state that the leg device is attached to an aircraft.SOLUTION: When a sliding direction of an inner cylinder 3 inside an outer cylinder 2 is a vertical direction, the leg device for aircraft includes: the outer cylinder 2; the inner cylinder 3 which slides around an axis of the outer cylinder 2 in a rotatable state; an upper locking member 4 which is fixed to the inner cylinder 3 moves inside the outer cylinder 2 together with the inner cylinder 3; a lower locking member 5, fitted to an inner periphery of the outer cylinder, for regulating relative rotation of the upper locking member 4 by locking with the upper locking member 4; a regulating member 6 for regulating the lower locking member 5 to rotate relatively to the outer cylinder 2; sealing members 71 and 72 for maintaining sealing of liquid inside the outer cylinder 2; and a support member 8 and a lower bearing 9, which support the sealing members 71 and 72. The leg device is passed through the regulating member 6 to the lower locking member 5, the support member 8 and the lower bearing 9, and a concave section 9b is provided at a lower face of the lower bearing.

Description

  The present invention relates to an aircraft leg device including a steering mechanism, and more particularly to an aircraft leg device capable of efficiently performing an operation of replacing a seal member in a state where the leg device is attached to an aircraft.

  In an aircraft, an aircraft leg device is usually provided with a steering mechanism in order to change the direction in which the aircraft travels while traveling on the ground. Aircraft leg devices equipped with a steering mechanism are often composed of an outer cylinder that serves as a cylinder and an inner cylinder that serves as a piston. In general, the inner cylinder can rotate during compression and the inner cylinder can rotate during expansion. It has a mechanism to regulate

  As a result, since the inner cylinder can rotate during compression, that is, while traveling on the ground, the steering mechanism can steer the wheel (change the direction), and during expansion, that is, after takeoff and before landing, the inner cylinder By restricting the rotation of the vehicle, the direction of the wheel is centered and fixed so that the airframe goes straight.

  In an aircraft leg device equipped with a steering mechanism, an engagement means is frequently used as a means for allowing the inner cylinder to rotate during compression and for restricting the rotation of the inner cylinder during expansion. When using the engaging means, when the direction in which the inner cylinder slides in the outer cylinder is the vertical direction, the upper engaging member is usually fixed to the inner cylinder and the lower engaging member is inserted into the outer cylinder. To fix. At the time of compression, the engagement between the upper engagement member and the lower engagement member is released so that the inner cylinder can be rotated, and at the time of expansion, the upper engagement member and the lower engagement member are engaged to engage the inner cylinder. Regulating rotation

  In an aircraft leg device provided with a steering mechanism, various proposals have been made in the past in order to allow the inner cylinder to rotate when compressed by the engaging means and to restrict the rotation of the inner cylinder when extended. . In Patent Document 1, when the direction in which the inner cylinder slides in the outer cylinder is defined as the vertical direction, the outer cylinder, the inner cylinder that slides around the axis of the outer cylinder, and the inner cylinder Fixed and moves in the outer cylinder together with the inner cylinder, fixed to the upper cam cylinder (upper engagement member) whose lower surface is the cam surface and the inner peripheral surface of the outer cylinder, and relative to the cam surface of the upper cam cylinder on the upper surface A lower cam cylinder (a lower engaging member) that has a cam surface that engages with the cam surface of the upper cam cylinder and restricts the upper cam cylinder from rotating relative to the outer cylinder axis. An aircraft leg device having been proposed.

  In the aircraft leg device proposed in Patent Document 1, the fitting (engagement) of the upper cam cylinder and the lower cam cylinder is released at the time of compression so that the inner cylinder can be rotated, and the upper cam cylinder and the lower cam cylinder are fitted at the time of extension. The relative rotation of the inner cylinder with respect to the outer cylinder is restricted by engagement (engagement), and the wheel can be centered.

Japanese Utility Model Sho 62-156599

  In the aircraft leg device using the upper cam cylinder and the lower cam cylinder as the engaging means proposed in Patent Document 1, when the lower cam cylinder is fixed to the outer cylinder, the lower cam cylinder is arranged around its axis with respect to the outer cylinder. In many cases, a regulating member that regulates relative rotation is used. In this case, a seal member that holds the fluid in the outer cylinder in an airtight manner is provided below the lower cam cylinder.

  FIG. 1 is a cross-sectional view of a main part of an aircraft leg device including a conventional steering mechanism. In the aircraft leg device shown in the figure, when the compression is performed, the upper cam cylinder and the lower cam cylinder are disengaged so that the inner cylinder can be rotated. The relative rotation of the is regulated.

  The aircraft leg device shown in the figure has a vertical direction in which the inner cylinder slides in the outer cylinder, and an upper cylinder (not shown) that can be attached to the aircraft body and can rotate about the axis of the outer cylinder 2. An inner cylinder 3 that slides in a stable state, an upper cam cylinder 4 that is fixed to the inner cylinder 3 and moves in the outer cylinder 2 together with the inner cylinder 3, and a lower cam cylinder 5 that is fitted to the inner peripheral surface of the outer cylinder 2 A regulating member 6 that regulates relative rotation of the lower cam cylinder 5 around its axis with respect to the outer cylinder 2, seal members 71 and 72 that hermetically hold the fluid in the outer cylinder 2, and seal members 71 and 72 , A support member 8 and a lower bearing 9 which are fitted to the outer peripheral surface of the inner cylinder 3 and the inner peripheral surface of the outer cylinder 2 and are continuously provided below the lower cam cylinder 5, and the lower cam cylinder 5, the support member 8 and Gland nut that restricts the lower bearing 9 from moving downward 0 and a.

  The lower surface of the upper cam cylinder 4 is a cam surface 4a, and the lower cam cylinder 5 is a cam surface 5a opposite to the cam surface of the upper cam cylinder. By fitting the cam surfaces of the upper cam cylinder 4 and the lower cam cylinder 5, relative rotation of the upper cam cylinder 4 around the axis of the outer cylinder 2 is restricted. Further, the aircraft leg device shown in the figure includes spare seal members 111 and 112 in a groove provided on the outer peripheral surface of the lower bearing 9. The inner cylinder 3 that slides in the outer cylinder 2 includes an inner cylinder main body 31 and an upper bearing 32 that directly contacts the outer cylinder 2. Further, the upper cam cylinder 4 fixed to the inner cylinder 3 is fixed to the outer peripheral surface of the inner cylinder main body 31 below the upper bearing 32 and moves together with the inner cylinder 3.

  FIG. 2 is a perspective view showing a state in which a main part of an aircraft leg device having a conventional steering mechanism is disassembled. In the figure, an outer cylinder 2, a lower cam cylinder 5, a regulating member 6, a support member 8, a lower bearing 9 and a gland nut 10 are shown.

  In the aircraft leg device having the conventional steering mechanism, as shown in FIG. 2, the regulating member 6 that regulates the rotation of the lower cam cylinder 5 relative to the outer cylinder 2 is provided on the outer peripheral surface of the lower cam cylinder 5. Assembled into a space formed by the recessed portion 5c and the recessed portion 2b provided on the inner peripheral surface of the outer cylinder 2. Further, a flange portion 5b is provided at the lower end of the lower cam cylinder, and the lower cam cylinder 5, the support member 8, and the lower cam cylinder 5 are brought into contact with the flange portion 5b by a step 2c provided on the inner peripheral surface of the outer cylinder 2. The movement of the bearing 9 is restricted.

  When an aircraft leg device having a steering mechanism having such a configuration is used while being mounted on an airframe, fluid that is airtightly held in the outer cylinder 2 may leak due to deterioration or damage of the seal members 71 and 72. In this case, if the maintenance facility at the airport where the aircraft is landing stores spare aircraft leg equipment, the entire aircraft leg equipment is replaced, and the aircraft leg equipment that has leaked fluid is a dedicated maintenance facility. The seal members 71 and 72 are exchanged. On the other hand, if the maintenance facility at the airport where the aircraft is landing does not store spare aircraft leg devices, it is necessary to replace the seal members 71 and 72 with the leg devices attached to the aircraft.

The procedure for replacing the seal member with the leg device attached to the aircraft is as follows.
(1) Support the aircraft body with a jack.
(2) The fluid kept airtight in the outer cylinder 2 is extracted.
(3) The jack pad part which the inner cylinder 3 has in the lower part is pushed up with a jack, and the inner cylinder 3 is supported.
(4) The mounting bolt 12 that fixes the gland nut 10 to the outer cylinder 2 is loosened to retract the gland nut 10 downward, and the lower cam cylinder 5, the support member 8, and the lower bearing 9 can be moved downward.

(5) The jacks that support the inner cylinder 3 are operated to lower the inner cylinder 3, and the seal members 71 and 72 in a state where the seal members 71 and 72, the support member 8 and the lower bearing 9 are pulled out of the outer cylinder 2. Is removed and replaced with spare seal members 111 and 112.
(6) The jack that supports the inner cylinder 3 is operated to raise the inner cylinder 3, and the seal members 71 and 72, the support member 8 and the lower bearing 9 replaced with the spare seal members are returned into the outer cylinder 2, The regulating member 6 is assembled in a space formed by the recess 5c provided on the outer peripheral surface of the lower cam cylinder and the recess 2b provided on the inner peripheral surface of the outer cylinder 2.
(7) The mounting bolt 12 is tightened to fix the gland nut 10, the jack that pushes up the jack pad portion of the inner cylinder 3 is removed, the fluid is sealed in the outer cylinder 2, and then the jack that supports the machine body is removed. .

  Here, when the jack that supports the inner cylinder 3 is operated in the procedure (5) to lower the inner cylinder 3, the lower cam cylinder 5 fitted to the inner cylinder 3 and the recess 5c on the outer peripheral surface thereof are arranged. The regulating member 6 is lowered. When returning the lowered lower cam cylinder 5 into the outer cylinder 2 in the procedure (6), the space formed by the recess 5c on the outer peripheral surface of the lower cam cylinder and the recess 2b on the inner peripheral surface of the outer cylinder is formed. Therefore, the position of the recess 5c is adjusted by rotating the lower cam cylinder 5 in which the regulating member 6 is disposed in the recess 5c. Need to be raised in state.

  However, when the lowered lower cam cylinder 5 is returned into the outer cylinder 2 in the procedure (6), a shift between the position of the recess 5c on the outer peripheral surface of the lower cam cylinder and the position of the recess 2b on the inner peripheral surface of the outer cylinder is visually confirmed. Since it cannot be done, misalignment occurs frequently. When the positional deviation occurs, the step 2c provided on the upper part of the regulating member 6 and the inner peripheral surface of the outer cylinder interferes, and the lower cam cylinder 5 cannot be assembled. For this reason, when a positional shift occurs, it is necessary to adjust the position by rotating the lower cam cylinder 5 while operating the jack to lower the inner cylinder 3 and pulling the lower cam cylinder 5 out of the outer cylinder 2.

  Therefore, when the seal members 71 and 72 are replaced with the leg device attached to the aircraft, the jack is used to match the position of the recess 5c on the outer peripheral surface of the lower cam cylinder with the position of the recess 2b on the inner peripheral surface of the outer cylinder. Operate to lower the inner cylinder 3 and pull the lower cam cylinder 5 out of the outer cylinder 2, then rotate the lower cam cylinder 5 to correct the position, and then operate the jack to raise the inner cylinder 3 and lower cam The procedure of returning the cylinder 5 into the outer cylinder has been repeatedly performed. For this reason, the operation | work which replaces the sealing members 71 and 72 in the state which attached the leg apparatus to the aircraft repeated the descent | fall and the raise of the inner cylinder 3 by jack operation, Therefore Inefficiency and time required.

  The present invention has been made in view of such circumstances, and restricts the lower engagement member (lower cam cylinder) from rotating relative to the outer cylinder when the leg device is attached to the aircraft. It is an object of the present invention to provide an aircraft leg device that can easily assemble a member at a predetermined position and can efficiently perform an operation of replacing a seal member.

  As a result of intensive studies to solve the above problems, the present inventor communicated the regulating member with the lower cam cylinder, the supporting member, and the lower bearing, and provided a recess on the lower surface of the lower bearing, thereby providing a leg device for the aircraft. It has been found that a regulating member that regulates the rotation of the lower cam cylinder relative to the outer cylinder can be easily assembled at a predetermined position in a state in which the seal member is attached, and the work of replacing the seal member can be performed efficiently. .

  The present invention has been completed on the basis of the above knowledge, and the gist thereof is the aircraft leg device of the following (1) and (2).

(1) When the direction in which the inner cylinder slides in the outer cylinder is the vertical direction, the outer cylinder, the inner cylinder that slides around the axis of the outer cylinder, and the inner cylinder are fixed. An upper engagement member that moves in the outer cylinder together with the inner cylinder, and is fitted to an inner peripheral surface of the outer cylinder, engages with the upper engagement member, and moves around the axis of the outer cylinder A lower engagement member that restricts relative rotation of the engagement member; a restriction member that restricts relative rotation of the lower engagement member about its axis relative to the outer cylinder; and the outer cylinder A sealing member that holds the fluid inside hermetically, and the sealing member that holds the sealing member, is fitted to the outer peripheral surface of the inner cylinder and the inner peripheral surface of the outer cylinder, and is provided below the lower engaging member. An aircraft leg device having a support member and a lower bearing,
An aircraft leg device characterized in that the restriction member communicates with the lower engagement member, the support member, and the lower bearing, and a recess is provided on a lower surface of the lower bearing.

(2) The upper engagement member is an upper cam cylinder whose lower surface is a cam surface, and the lower engagement member has a cam surface facing the cam surface of the upper cam cylinder on the upper surface, and the cam The aircraft according to (1), wherein the aircraft is a lower cam cylinder that restricts relative rotation of the upper cam cylinder around an axis of the outer cylinder by fitting a surface with a cam surface of the upper cam cylinder. Leg equipment.

  In the aircraft leg device of the present invention, the regulating member is communicated with the lower engagement member, the support member, and the lower bearing, and the concave member is provided on the lower surface of the lower bearing, so that the seal member is attached in a state where the leg device is attached to the aircraft. When replacing the seal member, the restricting member can be easily assembled at a predetermined position, and the work of replacing the seal member can be performed efficiently.

It is sectional drawing of the principal part of the aircraft leg apparatus provided with the conventional steering mechanism. It is a perspective view which shows the state which decomposed | disassembled the principal part of the aircraft leg apparatus provided with the conventional steering mechanism. It is a schematic sectional drawing which shows the structural example of the aircraft leg apparatus of this invention. It is sectional drawing which shows the principal part of the structural example of the aircraft leg apparatus of this invention, and is a detailed view in the B section of the said FIG. It is a perspective view which shows the state which decomposed | disassembled the principal part of the structural example of the aircraft leg apparatus of this invention.

  Hereinafter, an aircraft leg device of the present invention and a configuration example thereof will be described with reference to the drawings.

  FIG. 3 is a schematic cross-sectional view showing a configuration example of the aircraft leg device of the present invention. The aircraft leg apparatus shown in FIG. 3 includes an outer cylinder 2 serving as a cylinder, an inner cylinder 3 serving as a piston, a shaft support member 13 swingably provided on the outer peripheral surface of the outer cylinder 2, a shaft support member, The upper torque arm 14 is connected, and the lower torque arm 15 is connected to the lower portion of the upper torque arm 14 and the inner cylinder 3. The aircraft leg device shown in FIG. 3 is used with the upper part of the outer cylinder 2 attached to the aircraft body and with the wheels 16 attached to the lower part of the inner cylinder 3 as indicated by a two-dot chain line. In addition, a jack pad portion 31a that is pushed up by a jack when the seal member is replaced with the leg device attached to the aircraft is provided at the lower portion of the inner cylinder 3. Next, the main part of the aircraft leg device having such an outline will be described.

  FIG. 4 is a cross-sectional view showing a main part of a configuration example of the aircraft leg device of the present invention, and is a detailed view of part B of FIG. In this figure, the direction in which the inner cylinder slides in the outer cylinder is the vertical direction, and the outer cylinder 2, the inner cylinder 3 that slides around the axis of the outer cylinder 2, and the inner cylinder 3 are fixed. The upper cam cylinder 4 that moves in the outer cylinder 2 together with the inner cylinder 3, the lower cam cylinder 5 fitted to the inner peripheral surface of the outer cylinder 2, and the lower cam cylinder 5 around the axis of the outer cylinder 2 The regulating member 6 that regulates relative rotation, the sealing members 71 and 72 that hold the fluid in the outer cylinder 2 in an airtight manner, the sealing members 71 and 72, and the outer peripheral surface of the inner cylinder 3 and the inside of the outer cylinder 2 A support member 8 and a lower bearing 9 which are fitted to the peripheral surface and are provided continuously below the lower cam cylinder 5, and a ground nut 10 which restricts the lower cam cylinder 5, the support member 8 and the lower bearing 9 from moving downward. It shows.

  The lower surface of the upper cam cylinder 4 is a cam surface 4 a, and the upper cam cylinder 5 is a cam surface 5 a that faces the cam surface of the upper cam cylinder 4. By fitting the cam surfaces of the upper cam cylinder 4 and the lower cam cylinder 5, relative rotation of the upper cam cylinder 4 around the axis of the outer cylinder is restricted. Further, the aircraft leg device shown in the figure includes spare seal members 111 and 112 in a groove provided on the outer peripheral surface of the lower bearing 9. The inner cylinder 3 that slides in the outer cylinder 2 includes an inner cylinder main body 31 and an upper bearing 32 that directly contacts the outer cylinder 2. The upper cam cylinder 4 fixed to the inner cylinder 3 is fixed to the outer peripheral surface of the inner cylinder body 31 below the upper bearing 32 and moves together with the inner cylinder 3.

  In the aircraft leg device having such a configuration, the mechanism that enables the inner cylinder 3 to rotate during compression and restricts the rotation of the inner cylinder 3 during expansion is realized as follows.

  As shown in FIGS. 3 and 4, when the inner cylinder 3 is positioned at the lower end (when extended), the lower cam cylinder 5 and the upper cam cylinder 4 are connected to the outer cylinder 2 by the fitting of the upper cam cylinder 4 and the lower cam cylinder 5. Relative rotation around the axis is restricted. Here, since the upper part of the outer cylinder 2 is fixed to the airframe and the lower cam cylinder 5 is restricted from rotating relative to the outer cylinder 2 by the restriction member 6, the upper cam cylinder 4 is the axis of the outer cylinder 2. The inner cylinder 3 to which the upper cam cylinder 4 is fixed is also restricted from rotating around the axis of the outer cylinder 2. At this time, the inner cylinder 3 is centered by the fitting of the upper cam cylinder 4 and the lower cam cylinder 5.

  On the other hand, when the inner cylinder 3 slides upward from the lower end (during compression), the upper cam cylinder 4 slides upward together with the inner cylinder 3 and the fitting between the upper cam cylinder 4 and the lower cam cylinder 5 is released. . As a result, the lower cam cylinder 5 and the upper cam cylinder 4 can rotate relative to each other around the axis of the outer cylinder 2, so that the inner cylinder 3 can rotate. In this case, since the shaft support member 13 is coupled to a steering device (not shown), the force applied to the shaft support member 13 by the steering device is transmitted to the upper torque arm 14, the lower torque arm 15, and the inner cylinder 3. The direction of the wheel 16 attached to the lower part of the inner cylinder 3 is changed.

  Next, the arrangement of the regulating member 6 and the recess 9b provided on the lower surface of the lower bearing in the aircraft leg device of the present invention will be described.

  FIG. 5 is a perspective view showing a state in which the main part of the configuration example of the aircraft leg device of the present invention is disassembled. In the figure, an outer cylinder 2, a lower cam cylinder 5, a regulating member 6, a support member 8, a lower bearing 9 and a gland nut 10 are shown.

  The aircraft leg device according to the present invention is characterized in that the regulating member 6 communicates with the lower engagement member (lower cam cylinder 5), the support member 8 and the lower bearing 9, and a recess 9b is provided on the lower surface of the lower bearing 9. And In the configuration example of the aircraft leg device of the present invention, as shown in FIG. 5, the regulating member 6 includes a recess 2 b on the inner peripheral surface of the outer cylinder, a recess 5 c on the outer peripheral surface of the lower cam cylinder (lower engagement member), By disposing in the space formed by the recess 8a on the outer peripheral surface of the support member and the recess 9a on the upper surface of the lower bearing, the regulating member 6 is placed on the lower engagement member (lower cam cylinder 5), the support member 8 and the lower bearing 9. Communicate. A groove is provided as a recess 9b on the lower surface of the lower bearing.

  By connecting the regulating member 6 to the lower cam cylinder 5 (lower engaging member), the supporting member 8 and the lower bearing 9, as the lower bearing 9 rotates, the rotational force passes through the regulating member 6 and the supporting member. 8 and the lower cam cylinder 5 (lower engagement member), and the support member 8 and the lower cam cylinder 5 (lower engagement member) rotate. For this reason, if the lower bearing 9 is rotated using the recessed part 9b provided in the lower surface of the lower bearing, the lower cam cylinder 5 can be rotated accordingly.

  That is, when the seal members 71 and 72 are replaced with the leg device attached to the aircraft, the inner cylinder 3 is operated by operating the jack by rotating the lower bearing 9 using the recess 9b provided on the lower surface of the lower bearing. The lower cam cylinder 5 (lower engagement member) can be rotated to adjust the position of the recess without lowering the lower cam cylinder 5 (lower engagement member) and pulling it out of the outer cylinder 2. Therefore, in the aircraft leg device of the present invention, the lower cam cylinder 5 (lower engaging member) is relative to the outer cylinder 2 in a state in which the leg device is attached to the aircraft, as will be described in detail in the following embodiments. The regulating member 6 that regulates rotation can be easily assembled at a predetermined position, and the work of exchanging the seal members 71 and 72 can be performed efficiently.

  As the shape of the recess 9b provided on the lower surface of the lower bearing, various shapes can be adopted as long as the lower bearing 9 can be rotated using a jig. For example, as shown in FIGS. 4 and 5, a groove may be provided on the lower surface, and a hole may be provided on the lower surface. Further, as a jig used for rotating the lower bearing 9, a jig having a convex portion having a shape opposite to the shape of the concave portion 9b provided in the lower bearing, a round bar, or a square bar can be used.

  The recess 9b provided on the lower surface of the lower bearing is preferably provided at a position corresponding to a position where the regulating member 6 communicates with the lower bearing 9. As shown in FIG. 4 and FIG. 5, if the concave portion 9b provided on the lower surface of the lower bearing is positioned directly below the concave portion 9a in the lower bearing 9 for communicating the restricting member 6, the leg device is attached to the aircraft. When the seal member 71 or 72 is exchanged, the position of the recess 9a that allows the restriction member 6 to communicate can be easily estimated from the position of the recess 9b provided on the lower surface of the lower bearing that can be visually recognized. Thereby, the operation | work which attaches the control member 6 to a predetermined position can be performed still more easily.

  The aircraft leg device of the present invention preferably employs a cam cylinder as an upper engagement member and a lower engagement member that restrict relative rotation around the axis of the outer cylinder 2 by engagement. As shown in FIG. 4, the upper engagement member is the upper cam cylinder 4 whose lower surface is a cam surface, and the lower engagement member has a cam surface opposite to the cam surface of the upper cam cylinder 4 on the upper surface. The lower cam cylinder 5 restricts the relative rotation of the upper cam cylinder 4 around the axis of the outer cylinder 2 by fitting the cam surface with the cam surface of the upper cam cylinder 4. This is because the manufacturing cost of the aircraft leg device can be reduced, and the structure of the aircraft leg device can be simplified.

  In the aircraft leg device of the present invention, a round bar or a square bar can be adopted as the regulating member 6. As shown in FIG. 4 and FIG. 5, when the round bar-shaped regulating member 6 is adopted, the outer cylinder 2, the lower cam cylinder 5, the support member 8, and the recess for housing the regulating member 6 in the lower bearing 9 are relatively easy. Can be processed. For this reason, in the aircraft leg device of the present invention, it is preferable to adopt a round bar shape as the regulating member 6.

  An embodiment of the work of exchanging the seal member in a state where the leg device is attached to the aircraft in the aircraft leg device of the present invention will be described.

  In the example, the seal member was replaced with the aircraft leg apparatus of the present invention shown in FIGS. First, after supporting the aircraft body with a jack, the fluid kept airtight in the outer cylinder 2 was extracted, and then the jack pad portion 31a of the inner cylinder 3 was pushed up with the jack to support the inner cylinder 3.

  After the inner cylinder 3 is supported by the jack, the mounting bolt 12 for fixing the gland nut 10 to the outer cylinder 2 is loosened to retract the gland nut 10 downward, and the lower cam cylinder 5, the support member 8 and the lower bearing 9 are moved downward. It was possible to move. In this state, the jack that supports the inner cylinder 3 was operated to lower the inner cylinder 3, and the seal members 71 and 72, the support member 8, the lower bearing 9, and the ground nut 10 were pulled down to the outside of the outer cylinder 2. After the seal member or the like was pulled out of the outer cylinder 2, the seal members 71 and 72 disposed on the outer peripheral surface or the inner peripheral surface of the support member 8 and the lower bearing 9 were removed and replaced with spare seal members 111 and 112.

  After exchanging the seal members 71 and 72 with the spare seal members 111 and 112, the jack that supports the inner cylinder 3 is operated to raise the inner cylinder 3, and the seal members 71 and 72 exchanged with the spare seal member, the support member 8 and the lower bearing 9 were returned into the outer cylinder 2. At this time, in order to assemble the regulating member 6 in the space formed by the outer cylinder 2, the lower cam cylinder 5, the supporting member 8 and the lower bearing 9, the lower cam cylinder 5, the supporting member 8 and the lower bearing in which the regulating member 6 is disposed in the recess. 9 is rotated to adjust the position so that the position of the recess 2b on the inner peripheral surface of the outer cylinder matches the position of the recess formed by the lower cam cylinder 5, the support member 8, and the lower bearing 9. Since the displacement of the recess 2b position on the inner peripheral surface of the outer cylinder and the position of the recess formed by the lower cam cylinder 5, the support member 8 and the lower bearing 9 cannot be visually recognized, misalignment occurs frequently.

  In the aircraft leg device of the invention, the inner cylinder 3 is raised and the sealing members 71 and 72 exchanged with the spare seal member, the support member 8 and the lower bearing 9 are returned into the outer cylinder 2 with the jig. The rotational force is applied to the concave portion 9b provided on the lower surface of the lower bearing, and the support member 8 and the lower cam cylinder 5 are rotated along with the rotation of the lower bearing 9, whereby the lower cam cylinder 5, the support member 8 and the lower bearing 9 are rotated. It is possible to adjust the position of the recess formed by the above.

  That is, when the inner cylinder 3 is raised and the seal members 71 and 72 exchanged with the spare seal member, the support member 8 and the lower bearing 9 are returned into the outer cylinder 2, the position of the recess 2b on the inner peripheral surface of the outer cylinder Even in a state in which the position of the recess formed by the lower cam cylinder 5, the support member 8 and the lower bearing 9 is shifted, the seal members 71 and 72 exchanged with the spare seal member by lowering the inner cylinder 3, and the support members 8 and the lower bearing 9 can be made to coincide with the position of the recess 2b on the inner peripheral surface of the outer cylinder and the position of the recess formed by the lower cam cylinder 5, the support member 8, and the lower bearing 9 without lowering the outer bearing 2 to the outside. .

  After the regulating member 6 is assembled at a predetermined position and the inner cylinder 3 is raised by operating the jack, the fixing bolt 12 is tightened to fix the ground nut 10 to the outer cylinder 2, and the jack pad portion 31a of the inner cylinder is secured. The jack that pushes up was removed. Furthermore, after the fluid was sealed in the outer cylinder 2, the jack supporting the airframe was removed.

  As described above, when the seal members 71 and 72 are replaced with the leg device attached to the aircraft, the inner cylinder 3 is raised and replaced with the lower cam cylinder 5 (lower engagement member) and the spare seal member. If the seal members 71 and 72, the support member 8 and the lower bearing 9 are returned into the outer cylinder 2, the positions of the recesses of the outer cylinder 2 and the lower cam cylinder 5 may not match. In this case, the aircraft leg apparatus according to the present invention lowers the inner cylinder 3 to move the lower cam cylinder 5 (lower engaging member), the replaced seal members 71 and 72, the support member 8 and the lower bearing 9 to the outer cylinder 2. In a state where the inner cylinder 3 is raised and the lower cam cylinder 5 (lower engaging member), the replaced seal members 71 and 72, the support member 8 and the lower bearing 9 are returned into the outer cylinder 2 without being pulled out. By rotating the lower bearing 9, the support member 8 and the lower cam cylinder 5 (lower engagement member) can be rotated, and the concave portions of the outer cylinder 2 and the lower cam cylinder 5 can be aligned.

  Therefore, in the aircraft leg device of the present invention, the regulating member 6 can be attached without repeating the operation of lowering and raising the inner cylinder 3 with a jack, unlike the conventional aircraft leg device. 6 can be easily assembled at a predetermined position, and the work of exchanging the seal members 71 and 72 can be performed efficiently.

  In the aircraft leg device of the present invention, the regulating member is communicated with the lower engagement member, the support member, and the lower bearing, and the concave member is provided on the lower surface of the lower bearing, so that the seal member is attached in a state where the leg device is attached to the aircraft. When replacing the seal member, the restricting member can be easily assembled at a predetermined position, and the work of replacing the seal member can be performed efficiently.

  Therefore, when the aircraft leg device of the present invention is applied to a leg device having an aircraft steering mechanism, the time required for maintenance work of the aircraft can be reduced and the operating rate of the aircraft can be improved.

1: aircraft leg device, 2: outer cylinder, 2b: recess of outer cylinder, 2c: step of outer cylinder,
3: inner cylinder, 31: inner cylinder main body, 31a: jack pad part,
32: Upper bearing, 4: Upper cam cylinder (upper engagement member),
4a: cam surface of the upper cam cylinder, 5: lower cam cylinder (lower engaging member),
5a: cam surface of the lower cam cylinder, 5b: flange portion,
5c: a recess on the outer peripheral surface of the lower cam cylinder, 6: a regulating member,
71 and 72: seal member, 8: support member, 8a: recess of support member,
9: Lower bearing, 9a: Recess on the upper surface of the lower bearing,
9b: recess on the lower surface of the lower bearing, 10: ground nut,
111 and 112: spare seal members, 12: mounting bolts,
13: Shaft support member, 14: Upper torque arm, 15: Lower torque arm,
16: Wheel

Claims (2)

When the direction in which the inner cylinder slides in the outer cylinder is the vertical direction,
An outer cylinder,
An inner cylinder that slides in a rotatable state about the axis of the outer cylinder;
An upper engaging member fixed to the inner cylinder and moving in the outer cylinder together with the inner cylinder;
A lower engagement member that is fitted to the inner peripheral surface of the outer cylinder, engages with the upper engagement member, and restricts relative rotation of the upper engagement member around the axis of the outer cylinder;
A regulating member that regulates relative rotation of the lower engagement member about its axis with respect to the outer cylinder;
A seal member for hermetically holding the fluid in the outer cylinder;
An aircraft leg that holds the seal member, has a support member and a lower bearing that are fitted to the outer peripheral surface of the inner cylinder and the inner peripheral surface of the outer cylinder, and are provided below the lower engagement member. A device,
The restriction member communicates with the lower engagement member, the support member, and the lower bearing,
An aircraft leg device, wherein a recess is provided on a lower surface of the lower bearing.   The upper engagement member is an upper cam cylinder whose lower surface is a cam surface, and the lower engagement member has a cam surface on the upper surface facing the cam surface of the upper cam cylinder, and the cam surface and the 2. The aircraft leg device according to claim 1, wherein the aircraft leg device is a lower cam cylinder that regulates relative rotation of the upper cam cylinder around the axis of the outer cylinder by fitting with a cam surface of the upper cam cylinder. 3.

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