CN215707227U

CN215707227U - Aircraft landing gear transfer equipment

Info

Publication number: CN215707227U
Application number: CN202122244235.3U
Authority: CN
Inventors: 王树强; 龚鑫韬; 顾重源; 方园; 朱江峰; 申登旭
Original assignee: Shanghai Aircraft Manufacturing Co Ltd
Current assignee: Shanghai Aircraft Manufacturing Co Ltd
Priority date: 2021-09-16
Filing date: 2021-09-16
Publication date: 2022-02-01
Anticipated expiration: 2031-09-16

Abstract

The utility model relates to the technical field of aircraft parts, and particularly discloses an aircraft landing gear transferring device. The equipment is used for transferring the landing gear of the airplane and comprises a walking platform and a posture adjusting platform; the walking platform comprises a platform base, a plurality of fork tooth rods are convexly arranged on the side surface of the platform base, and the aircraft landing gear can be erected on the fork tooth rods; the attitude adjusting platform comprises a clamping unit for clamping the landing gear of the airplane, the clamping unit can move in the directions of an X axis, a Y axis and a Z axis relative to the walking platform, and the clamping unit can rotate around the directions of the Y axis and the Z axis relative to the walking platform; the clamping unit is further connected with a drag chain, and the drag chain can be connected with an aircraft landing gear. With the help of the above arrangement, the supporting and clamping actions of the aircraft landing gear can be realized, and the position of the aircraft landing gear can be efficiently and accurately adjusted due to the adjustable position of the clamping unit, so that the efficiency of transferring, dismounting and mounting of the equipment is improved.

Description

Aircraft landing gear transfer equipment

Technical Field

The utility model relates to the technical field of aircraft parts, in particular to an aircraft landing gear transferring device.

Background

At present, the installation of the landing gear of the airplane mainly adopts a manual or hydraulic adjustment installation form, the adjustment difficulty is high, the disassembly and assembly are difficult, and the technical requirement on operators is high. The common undercarriage height adjustment needs to be realized by controlling the stretching of a hydraulic cylinder through a hand pump cylinder, and the height of the installation vehicle cannot be accurately adjusted due to the fact that the control quantity of the hand pump cannot be accurately controlled. The position and the rotation of the horizontal direction of the universal caster are required to be adjusted through the manual control of the three universal casters below the universal caster, the adjustment is inconvenient, and the accurate adjustment cannot be realized.

At present, an automatic installation device of the undercarriage exists, but the automatic installation device of the undercarriage is usually large in main body and complex in structure, and the phenomenon of stability reduction of the device caused by the fact that the gravity center of an undercarriage installation vehicle device is higher easily occurs when the undercarriage is assembled due to the complexity of the structure of the automatic installation device of the undercarriage. And because the height of the automatic installation device is too high, the automatic installation device is often only suitable for large-scale wide-body passenger planes with higher safety height.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide an aircraft landing gear transfer device to solve the problem that the position of a landing gear is difficult to adjust.

In order to achieve the purpose, the utility model adopts the following technical scheme:

an aircraft landing gear transferring device is used for transferring an aircraft landing gear and comprises a walking platform and an attitude adjusting platform; the walking platform comprises a platform base, a plurality of fork tooth rods are convexly arranged on the side surface of the platform base, and the aircraft landing gear can be erected on the fork tooth rods; the attitude adjusting platform comprises a clamping unit for clamping the aircraft landing gear, the clamping unit can move in the X-axis direction, the Y-axis direction and the Z-axis direction relative to the walking platform, and the clamping unit can rotate around the Y-axis direction and the Z-axis direction relative to the walking platform; the clamping unit is further connected with a traction chain, and the traction chain can be connected with the aircraft landing gear.

The posture adjusting platform further comprises a first frame, a second frame, a third frame, a fourth frame and a fifth frame; the first frame can move relative to the platform base in the X-axis direction, the second frame can move relative to the first frame in the Z-axis direction, the third frame can move relative to the second frame in the Y-axis direction, the third frame can rotate relative to the fourth frame in the Z-axis direction, the fourth frame can rotate relative to the fifth frame in the Y-axis direction, and the clamping unit is installed on the fifth frame.

Further, the platform base is provided with a first slide rail, the first frame is fixedly connected with a first slide block, the first slide block is slidably arranged on the first slide rail, a first driving unit is installed on the first frame, and the first driving unit is used for driving the first frame to move back and forth in the X-axis direction relative to the platform base.

Preferably, first frame is equipped with the second slide rail, the second frame has linked firmly the second slider, the second slider cunning is located the second slide rail, install the second drive unit on the second frame, the second drive unit is used for the drive the second frame is relative first frame is reciprocating motion in the Z axle direction.

Preferably, the second frame is provided with a third slide rail, the third frame is fixedly connected with a third slide block, the third slide block is slidably arranged on the third slide rail, a third driving unit is installed on the third frame, and the third driving unit is used for driving the third frame to move in a reciprocating manner in the Y-axis direction relative to the second frame.

Preferably, the third frame is convexly provided with at least one first positioning column, the fourth frame is provided with a guide through hole, the guide through hole extends along the circumferential direction of the Z axis, the first positioning column penetrates through the guide through hole, the third frame is provided with a fourth driving unit, and the fourth driving unit is used for driving the third frame to rotate around the Z axis direction relative to the fourth frame.

Preferably, a second positioning column is convexly arranged on the fifth frame, a guide rail is arranged on the fourth frame, the guide rail extends along the circumferential direction of the Y axis, the second positioning column is slidably arranged on the guide rail, a fifth driving unit is mounted on the fourth frame, and the fifth driving unit is used for driving the fourth frame to rotate around the Y axis direction relative to the fifth frame.

Preferably, a sixth driving unit and a push rod are arranged on the fifth frame, the clamping unit is connected to the push rod, and the sixth driving unit can drive the clamping unit to be close to or far away from the fifth frame through the push rod.

Furthermore, the centre gripping unit includes the holder main part, decides the clamp hoop, moves the clamp hoop and drives the pole, the holder main part connect in on the push rod, just the holder main part with drive the pole with decide the clamp hoop and connect respectively, move the clamp hoop with move the clamp hoop and enclose into the location perforation, the aircraft undercarriage can cross-under in the location perforation, drive the pole and can drive move the clamp hoop and remove, make the location perforation enlarges or reduces.

Preferably, one side of the platform base is provided with an avoiding port, the avoiding port is internally provided with four fork toothed bars perpendicular to the depth direction of the avoiding port, and the bottom end of the platform base is provided with four universal wheels.

The utility model has the beneficial effects that:

by means of the arrangement of the fork tooth rod, the supporting of the aircraft landing gear can be achieved, and the aircraft landing gear erected on the walking platform can be clamped by the clamping unit. The clamping unit can move in the X-axis direction, the Y-axis direction and the Z-axis direction relative to the walking platform and can rotate around the Y-axis direction and the Z-axis direction. Therefore, the position of the aircraft landing gear can be efficiently and accurately adjusted by an operator, and the efficiency of transferring and disassembling the aircraft landing gear transferring equipment is improved by the arrangement. The setting that the drag chain can be connected with the aircraft undercarriage can be applied to the wide-angle of undercarriage and hang, can reduce the height when whole equipment and aircraft undercarriage transport from this, and the space that equipment occupy has been reduced to the aforesaid content, has ensured that equipment can get into the installation region, has improved the efficiency that equipment transported, has realized aircraft undercarriage long distance's transportation and simply transfers the appearance location.

Drawings

FIG. 1 is a schematic structural diagram of an aircraft landing gear transfer device provided by an embodiment of the utility model;

FIG. 2 is a schematic structural diagram of a walking platform provided in the embodiment of the present invention;

fig. 3 is a schematic structural diagram of a first view angle of the pose adjustment platform according to the embodiment of the present invention;

fig. 4 is a schematic structural diagram of a second viewing angle of the pose adjustment platform according to the embodiment of the present invention;

fig. 5 is a schematic structural diagram of a third viewing angle of the pose adjustment platform according to the embodiment of the present invention.

In the figure:

100. a posture adjusting platform; 110. a first frame; 111. a first slider; 112. a second slide rail; 113. a first drive unit; 120. a second frame; 121. a second driving unit; 122. a third slide rail; 130. a third frame; 131. a third driving unit; 132. a fourth drive unit; 133. a first positioning post; 140. a fourth frame; 141. a guide through hole; 142. a guide rail; 143. a fifth driving unit; 150. a fifth frame; 151. a support member; 160. a sixth driving unit; 161. a push rod; 170. a clamping unit; 171. a drag chain; 172. fixing a clamping hoop; 173. a dynamic clamping band; 174. driving the rod; 175. a holder body;

200. a walking platform; 210. a platform base; 211. a first slide rail; 220. a universal wheel; 230. a fork rack rod.

Detailed Description

In order to make the technical problems solved, technical solutions adopted and technical effects achieved by the present invention clearer, the technical solutions of the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

The technical scheme of the utility model is further explained by the specific implementation mode in combination with the attached drawings.

As shown in fig. 1 to 3, the present embodiment provides an aircraft landing gear transfer device for transferring an aircraft landing gear, including a walking platform 200 and a posture adjusting platform 100; the walking platform 200 comprises a platform base 210, a plurality of fork tooth rods 230 are convexly arranged on the side surface of the platform base 210, and the aircraft landing gear can be erected on the fork tooth rods 230; the attitude adjusting platform 100 comprises a clamping unit 170 for clamping the landing gear of the airplane, the clamping unit 170 can move in the directions of an X axis, a Y axis and a Z axis relative to the walking platform 200, and the clamping unit 170 can rotate around the directions of the Y axis and the Z axis relative to the walking platform 200; the gripping unit 170 is also connected to a drag chain 171, the drag chain 171 being connectable to an aircraft landing gear.

The aircraft landing gear can be supported by the arrangement of the fork lever 230, and the aircraft landing gear mounted on the traveling platform 200 can be held by the holding unit 170. The clamping unit 170 can move in the directions of the X axis, the Y axis and the Z axis relative to the walking platform 200 and can rotate around the directions of the Y axis and the Z axis. Therefore, the position of the aircraft landing gear can be efficiently and accurately adjusted by an operator, and the efficiency of transferring and disassembling the aircraft landing gear transferring equipment is improved by the arrangement. The setting that drag chain 171 can be connected with the aircraft undercarriage can be applied to the wide-angle of undercarriage and hang, can reduce the height when whole equipment and aircraft undercarriage transport from this, and the space that equipment occupy has been reduced to the aforesaid content, has ensured that equipment can get into the installation region, has improved the efficiency that equipment transported, has realized aircraft undercarriage long distance's transportation and simply transfers the appearance location.

In the present embodiment, the X-axis direction, the Y-axis direction, and the Z-axis direction are all perpendicular to each other, and the Z-axis direction is perpendicular to the ground.

As shown in fig. 3-5, the pose adjustment platform 100 further comprises a first frame 110, a second frame 120, a third frame 130, a fourth frame 140, and a fifth frame 150; the first frame 110 can move in the X-axis direction with respect to the stage base 210, the second frame 120 can move in the Z-axis direction with respect to the first frame 110, the third frame 130 can move in the Y-axis direction with respect to the second frame 120, the third frame 130 can rotate in the Z-axis direction with respect to the fourth frame 140, the fourth frame 140 can rotate in the Y-axis direction with respect to the fifth frame 150, and the chucking unit 170 is mounted to the fifth frame 150. By means of the structural arrangement, an operator can respectively complete the operation of moving or rotating the clamping unit 170 in multiple directions by controlling the first frame 110, the second frame 120, the third frame 130, the fourth frame 140 or the fifth frame 150, the adjusting process is simplified, the requirement for repeated adjustment is reduced, the adjusting efficiency is greatly improved, and the difficulty in adjusting the position of the landing gear of the airplane is reduced.

Preferably, the platform base 210 is provided with a first slide rail 211, the first frame 110 is fixedly connected with a first slide block 111, the first slide block 111 is slidably disposed on the first slide rail 211, the first frame 110 is provided with a first driving unit 113, and the first driving unit 113 is configured to drive the first frame 110 to reciprocate in the X-axis direction relative to the platform base 210. The first frame 110 is provided with a second slide rail 112, the second frame 120 is fixedly connected with a second slide block, the second slide block is slidably arranged on the second slide rail 112, a second driving unit 121 is installed on the second frame 120, and the second driving unit 121 is used for driving the second frame 120 to reciprocate in the Z-axis direction relative to the first frame 110. The second frame 120 is provided with a third slide rail 122, the third frame 130 is fixedly connected with a third slide block, the third slide block is slidably arranged on the third slide rail 122, a third driving unit 131 is installed on the third frame 130, and the third driving unit 131 is used for driving the third frame 130 to reciprocate in the Y-axis direction relative to the second frame 120.

The arrangement makes the translational motion of the clamping unit 170 in the directions of the X axis, the Y axis and the Z axis simple and clear, the adjustment of the clamping unit 170 with equal numerical displacement can be realized by controlling the first frame 110, the second frame 120 and the third frame 130 to move in different directions, and the first frame 110, the second frame 120 and the third frame 130 which meet the requirements are compact in layout, small in occupied space and not prone to interference, so that the adjustment operation by using the attitude adjusting platform 100 can obtain accurate and reliable results.

Preferably, the third frame 130 is convexly provided with at least one first positioning column 133, the fourth frame 140 is provided with a guide through hole 141, the guide through hole 141 extends along the circumferential direction of the Z axis, the first positioning column 133 passes through the guide through hole 141, the third frame 130 is provided with the fourth driving unit 132, and the fourth driving unit 132 is used for driving the third frame 130 to rotate around the Z axis direction relative to the fourth frame 140. The fifth frame 150 is convexly provided with a second positioning column, the fourth frame 140 is provided with a guide rail 142, the guide rail 142 extends along the circumferential direction of the Y axis, the second positioning column is slidably arranged on the guide rail 142, the fourth frame 140 is provided with a fifth driving unit 143, and the fifth driving unit 143 is used for driving the fourth frame 140 to rotate around the Y axis direction relative to the fifth frame 150.

The cooperation of the first positioning column 133 and the guiding through hole 141 and the cooperation of the second positioning column and the guiding track 142 are utilized to enable the rotation motion of the clamping unit 170 in the Y-axis and Z-axis directions to be accurate and reliable, the orientation angle of the clamping unit 170 can be adjusted by controlling the rotation of the third frame 130 relative to the fourth frame 140 and the rotation of the fourth frame 140 relative to the fifth frame 150, and the third frame 130, the fourth frame 140 and the fifth frame 150 which meet the above requirements are sequentially connected in a rotating manner and avoid the arrangement with each other, so that the problem of interference among the components of the posture adjusting platform 100 is avoided, and the accuracy and reliability of the adjustment operation result are further improved.

Preferably, a sixth driving unit 160 and a push rod 161 are disposed on the fifth frame 150, the clamping unit 170 is connected to the push rod 161, and the sixth driving unit 160 can drive the clamping unit 170 to approach or separate from the fifth frame 150 through the push rod 161. The clamping unit 170 can be close to or far away from the fifth frame 150, so that when the aircraft landing gear transfer device performs dismounting operation, the clamping unit 170 can drive the aircraft landing gear to reciprocate between a dismounting position and a preparation position, the efficiency of the dismounting operation is greatly improved, and the dismounting operation can be smoothly performed.

Further, the clamping unit 170 includes a clamping member body 175, a fixed clampband 172, a movable clampband 173 and a driving rod 174, the clamping member body 175 is connected to the push rod 161, the clamping member body 175 is connected to the driving rod 174 and the fixed clampband 172, the movable clampband 173 and the movable clampband 173 enclose a positioning through hole, the landing gear can be connected to the positioning through hole, and the driving rod 174 can drive the movable clampband 173 to move away from or close to the fixed clampband 172, so that the positioning through hole is enlarged or reduced. The arrangement can complete the clamping and loosening actions of the landing gear of the airplane by expanding or reducing the through hole, thereby ensuring that the clamping operation of the clamping unit 170 on the landing gear erected on the traveling platform 200 can be smoothly and effectively completed.

With continued reference to fig. 2, an avoidance port is formed at one side of the platform base 210, four fork-shaped rods 230 perpendicular to the depth direction of the avoidance port are arranged in the avoidance port, and four universal wheels 220 are arranged at the bottom end of the platform base 210. The four universal wheels 220 facilitate the movement of the platform base 210 in the X-axis direction and the Y-circumference direction. The four forked rods 230 can support and position the landing gear of the airplane by abutting two positions at the bottom of the landing gear wheel from two sides.

In this embodiment, the universal wheels 220 are mecanum wheels, and in other embodiments of this embodiment, the universal wheels 220 are steering wheels.

As shown in fig. 1 and 5, the fifth frame 150 is further provided with a support 151, and the support 151 is used for supporting the aircraft landing gear without tires, and simultaneously completing the supporting action of the aircraft landing gear in the jacking state. The supporting member 151 is widely used in the art, and the specific structure and function thereof are well known to those skilled in the art and will not be described herein.

With continued reference to fig. 3 to 5, in this embodiment, the aircraft landing gear transferring apparatus further includes a control component, and the control component is configured to control the first driving unit 113, the second driving unit 121, the third driving unit 131, the fourth driving unit 132, the fifth driving unit 143, the sixth driving unit 160, and the driving rod 174, so that the actions of the attitude adjusting platform 100 can be automatically completed, the working efficiency of the apparatus is improved, and the workload of an operator is greatly reduced.

In this embodiment, the first driving unit 113, the second driving unit 121, the third driving unit 131, the fourth driving unit 132, the fifth driving unit 143, the sixth driving unit 160, and the driving rod 174 are conventional devices in the art, and the specific structure and the operation principle thereof are not described herein again, and the control component can control the first driving unit 113, the second driving unit 121, the third driving unit 131, the fourth driving unit 132, the fifth driving unit 143, the sixth driving unit 160, and the driving rod 174 to complete corresponding actions, and the operation principle thereof is common knowledge in the art, and is not described herein again.

It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. An aircraft landing gear transfer apparatus for transferring an aircraft landing gear, comprising:

the aircraft landing gear comprises a walking platform (200), wherein the walking platform (200) comprises a platform base (210), a plurality of fork tooth rods (230) are convexly arranged on the side surface of the platform base (210), and the aircraft landing gear can be erected on the fork tooth rods (230);

the attitude adjusting platform (100) comprises a clamping unit (170) for clamping the aircraft landing gear, the clamping unit (170) can move in the X-axis direction, the Y-axis direction and the Z-axis direction relative to the walking platform (200), and the clamping unit (170) can rotate around the Y-axis direction and the Z-axis direction relative to the walking platform (200); the clamping unit (170) is further connected with a drag chain (171), and the drag chain (171) can be connected with the aircraft landing gear.

2. The aircraft landing gear transfer apparatus of claim 1, wherein the attitude platform (100) further comprises a first frame (110), a second frame (120), a third frame (130), a fourth frame (140), and a fifth frame (150); the first frame (110) can move relative to the platform base (210) in the X-axis direction, the second frame (120) can move relative to the first frame (110) in the Z-axis direction, the third frame (130) can move relative to the second frame (120) in the Y-axis direction, the third frame (130) can rotate relative to the fourth frame (140) in the Z-axis direction, the fourth frame (140) can rotate relative to the fifth frame (150) in the Y-axis direction, and the clamping unit (170) is installed on the fifth frame (150).

3. The aircraft landing gear transfer device according to claim 2, wherein the platform base (210) is provided with a first slide rail (211), the first frame (110) is fixedly connected with a first slide block (111), the first slide block (111) is slidably arranged on the first slide rail (211), a first driving unit (113) is mounted on the first frame (110), and the first driving unit (113) is used for driving the first frame (110) to reciprocate in the X-axis direction relative to the platform base (210).

4. An aircraft landing gear transfer device according to claim 2, wherein the first frame (110) is provided with a second slide rail (112), the second frame (120) is fixedly connected with a second slide block, the second slide block is slidably arranged on the second slide rail (112), and a second driving unit (121) is mounted on the second frame (120), and the second driving unit (121) is used for driving the second frame (120) to reciprocate in the Z-axis direction relative to the first frame (110).

5. An aircraft landing gear transfer device according to claim 2, wherein the second frame (120) is provided with a third slide rail (122), the third frame (130) is fixedly connected with a third slide block, the third slide block is slidably arranged on the third slide rail (122), a third driving unit (131) is mounted on the third frame (130), and the third driving unit (131) is used for driving the third frame (130) to reciprocate in the Y-axis direction relative to the second frame (120).

6. The aircraft landing gear transfer device according to claim 2, wherein the third frame (130) is convexly provided with at least one first positioning column (133), the fourth frame (140) is provided with a guide through hole (141), the guide through hole (141) extends along the circumferential direction of the Z axis, the first positioning column (133) penetrates through the guide through hole (141), the third frame (130) is provided with a fourth driving unit (132), and the fourth driving unit (132) is used for driving the third frame (130) to rotate around the Z axis direction relative to the fourth frame (140).

7. The aircraft landing gear transferring device according to claim 2, wherein the fifth frame (150) is convexly provided with a second positioning column, the fourth frame (140) is provided with a guide rail (142), the guide rail (142) extends along the circumferential direction of the Y axis, the second positioning column is slidably arranged on the guide rail (142), a fifth driving unit (143) is mounted on the fourth frame (140), and the fifth driving unit (143) is used for driving the fourth frame (140) to rotate around the Y axis direction relative to the fifth frame (150).

8. An aircraft landing gear transfer device according to claim 2, wherein a sixth drive unit (160) and a push rod (161) are provided on the fifth frame (150), the clamping unit (170) is connected to the push rod (161), and the sixth drive unit (160) can drive the clamping unit (170) towards or away from the fifth frame (150) via the push rod (161).

9. Aircraft landing gear transfer apparatus according to claim 8, wherein the gripper unit (170) comprises a gripper body (175), a fixed clampband (172), a movable clampband (173) and a driver rod (174), the gripper body (175) being connected to the ram (161) and the gripper body (175) being connected to the driver rod (174) and the fixed clampband (172), respectively, the movable clampband (173) and the movable clampband (173) enclosing a positioning aperture through which the aircraft landing gear can be threaded, the driver rod (174) being capable of driving the movable clampband (173) to move, causing the positioning aperture to expand or contract.

10. The aircraft landing gear transferring device according to any one of claims 1 to 9, wherein an avoiding opening is formed in one side of the platform base (210), four fork tooth rods (230) perpendicular to the depth direction of the avoiding opening are arranged in the avoiding opening, and four universal wheels (220) are arranged at the bottom end of the platform base (210).