CN219361319U - Aircraft landing gear retracting mechanism - Google Patents

Abstract

The utility model relates to the technical field of aircraft landing gears, in particular to an aircraft landing gear retraction mechanism; the utility model relates to an aircraft landing gear retraction mechanism, which comprises a universal connecting shaft, wherein the outer side wall of the universal connecting shaft is provided with a retraction mechanism and a damping mechanism, the damping mechanism comprises a first support column, the bottom of the first support column is provided with a mounting groove, an air bag is arranged in the mounting groove, the rear side of the first support column is provided with an air compressor and an air storage tank, the air compressor is communicated with the air bag, the mounting groove is internally provided with a limiting disc, the limiting disc is arranged at the bottom of the air bag, and air in the air storage tank can be injected into the air bag through the air compressor, or air in the air bag is injected into the air storage tank, so that the hardness of the air bag is changed, and the damping coefficient of the device is adjusted, so that the effect of improving the landing degree of an aircraft is realized.

Description

Aircraft landing gear retracting mechanism

Technical Field

The utility model relates to the technical field of aircraft landing gears, in particular to an aircraft landing gear retraction mechanism.

Background

In order to ensure that the aircraft drops steadily, all can install damping device on the retracting mechanism of aircraft undercarriage, but the damping device who installs on the retracting mechanism is the spring shock attenuation mostly, but the shock absorption coefficient of spring shock attenuation is fixed, and hardness is higher, is difficult to fully absorb the impact force that the aircraft produced in the moment of landing when the aircraft drops, has reduced the comfort level that the aircraft was taken, aims at above-mentioned condition, carries out technical innovation on current aircraft undercarriage retracting mechanism basis.

Disclosure of Invention

The utility model aims to provide an aircraft landing gear retraction mechanism which solves the problems in the background art.

In order to achieve the above purpose, the present utility model provides the following technical solutions: the utility model provides an aircraft undercarriage receive and releases mechanism, includes the universal joint axle, the lateral wall of universal joint axle is provided with receive and release mechanism and damper, damper includes first support column, the mounting groove has been seted up to the bottom of first support column, be provided with the gasbag in the mounting groove, the rear side of first support column is provided with air compressor and gas holder, air compressor is linked together with the gasbag, be provided with the spacing dish in the mounting groove, the spacing dish sets up the bottom at the gasbag, the bottom of spacing dish is provided with the second support column, the bottom of spacing dish is provided with the spring, the spring sets up in mounting groove inside wall bottom, the spout has all been seted up to the left and right sides of second support column through first pivot all, the stopper sets up in the spout, receive and release mechanism is located the front side of first support column.

Preferably, the retracting mechanism comprises a first connecting plate, a second connecting plate is arranged on the outer side wall of the first connecting plate through a second rotating shaft, a third connecting plate is arranged on the outer side wall of the second connecting plate through a third rotating shaft, and a hydraulic cylinder is arranged on the top of the third connecting plate through a fourth rotating shaft.

Preferably, the top of universal joint axle is provided with the second connecting seat through the fifth pivot, the bottom of universal joint axle is provided with first connecting seat through the sixth pivot, first connecting seat sets up the top at first support column.

Preferably, the outer side wall of the hydraulic cylinder is provided with a supporting frame through a seventh rotating shaft, and the third connecting plate is arranged on the inner side wall of the supporting frame through an eighth rotating shaft.

Preferably, a motor is arranged at the top of the support frame, and the output end of the motor penetrates through the top of the support frame to be connected with the second connecting seat.

Preferably, the inner side wall of the support frame is provided with a cross hollow column through a ninth rotating shaft, the first support column is arranged in the inner cavity of the cross hollow column, and the first connecting plate is arranged on the front side of the cross hollow column through the tenth rotating shaft.

Compared with the prior art, the utility model has the following beneficial effects:

the utility model relates to an aircraft landing gear retracting mechanism, can be with the air injection gasbag in the gas holder through air compressor, perhaps with the air injection gas holder in the gasbag again to this hardness that changes the gasbag, with this damping coefficient who adjusts the device, with this effect that realizes improving the aircraft landing smoothness;

the limiting disc can be propped against the bottom of the air bag through the spring, so that when the second support column is guaranteed to move upwards under the impact force, the air bag can absorb the impact force produced by the second support column at the first time, and the effect of improving the operation reliability of the device is achieved.

Drawings

FIG. 1 is a schematic view of an aircraft landing gear retraction mechanism according to the present utility model;

FIG. 2 is a right side view of an aircraft landing gear retraction mechanism according to the present utility model;

FIG. 3 is a right side cross-sectional view of an aircraft landing gear retraction mechanism according to the present utility model;

fig. 4 is a front partial cross-sectional view of an aircraft landing gear retraction mechanism according to the present utility model.

In the figure: 1. a first support column; 11. an air bag; 12. an air compressor; 13. a gas storage tank; 14. a limiting disc; 15. a spring; 16. a second support column; 17. a roller; 18. a limiting block; 2. a first connection plate; 21. a second connecting plate; 22. a third connecting plate; 23. a hydraulic cylinder; 3. a universal connecting shaft; 31. a first connection base; 32. a second connecting seat; 4. a support frame; 5. a motor; 6. cross hollow column.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Referring to fig. 1-4, an aircraft landing gear retracting mechanism comprises a universal connecting shaft 3, a retracting mechanism and a damping mechanism are rotatably arranged on the outer side wall of the universal connecting shaft 3, the damping mechanism comprises a first supporting column 1, a mounting groove is formed in the bottom of the first supporting column 1, an air bag 11 is slidably arranged in the mounting groove, an air compressor 12 and an air storage tank 13 are fixedly welded on the rear side of the first supporting column 1, the air compressor 12 is communicated with the air storage tank 13, the air compressor 12 is communicated with the air bag 11, a limiting disc 14 is slidably arranged in the mounting groove, the limiting disc 14 is slidably arranged at the bottom of the air bag 11, a second supporting column 16 is fixedly welded on the bottom of the limiting disc 14, a spring 15 is fixedly welded on the bottom of the inner side wall of the mounting groove, rollers 17 are rotatably arranged on the left and right sides of the second supporting column 16 through a first rotating shaft, the roller 17 rotates through a first rotating shaft, sliding grooves are formed in the left side and the right side of the inner side wall of the mounting groove, limiting blocks 18 are fixedly welded on the left side and the right side of the limiting disc 14, the limiting blocks 18 are arranged in the sliding grooves in a sliding mode, the limiting disc 14 moves up and down stably by means of the limiting blocks 18, the retracting mechanism is located on the front side of the first supporting column 1 and comprises a first connecting plate 2, the outer side wall of the first connecting plate 2 is rotatably provided with a second connecting plate 21 through a second rotating shaft, the second connecting plate 21 realizes overturning motion through the second rotating shaft, the outer side wall of the second connecting plate 21 is rotatably provided with a third connecting plate 22 through a third rotating shaft, the third connecting plate 22 realizes overturning motion through the third rotating shaft, the top of the third connecting plate 22 is rotatably provided with a hydraulic cylinder 23 through a fourth rotating shaft, the hydraulic cylinder 23 can pull the third connecting plate 22 to move through the fourth rotating shaft, the top of universal joint axle 3 is provided with second connecting seat 32 through the rotation of fifth pivot, second connecting seat 32 drives universal joint axle 3 through the fifth pivot and rotates, the bottom of universal joint axle 3 is provided with first connecting seat 31 through the rotation of sixth pivot, universal joint axle 3 drives first connecting seat 31 through the sixth pivot and rotates first connecting seat 31 and rotate, first connecting seat 31 welded fastening sets up at the top of first support column 1, drive first support column 1 through first connecting seat 31 and rotate, the lateral wall of pneumatic cylinder 23 rotates through the seventh pivot and is provided with support frame 4, pneumatic cylinder 23 can realize turning motion in the below of support frame 4 through the seventh pivot, third connecting plate 22 rotates the inside wall that sets up at support frame 4 through the eighth pivot, third connecting plate 22 realizes turning motion in support frame 4 below through the eighth pivot, the top fixed welding of support frame 4 is provided with motor 5, the top that motor 5 output runs through support frame 4 is connected with second connecting seat 32, drive second connecting seat 32 through motor 5 and rotate, the inside wall of support frame 4 is provided with cross hollow column 6 through ninth rotation through the rotation, cross hollow column 6 is realized turning over in the first support column 6 through the first pivot through the rotation of ninth pivot, cross hollow column 6 is realized turning over in the hollow column 6 in the first hollow column 2 through the setting up the hollow column 2, the hollow column is realized turning motion in the first hollow column 2 through the first hollow column 6.

Working principle: the support frame 4 is arranged in the aircraft nose landing gear retraction cabin, after the aircraft takes off, the hydraulic cylinder 23 contracts and pulls the third connecting plate 22 to overturn upwards, the second connecting plate 21 is pulled to overturn forwards and upwards through the third connecting plate 22, the second connecting plate 21 pulls the cross hollow column 6 to overturn forwards through the first connecting plate 2, the hydraulic cylinder 23 is outwards prolonged to release the idler wheel 17 when the aircraft drops, the retraction of the idler wheel 17 is completed, the second connecting seat 32 is driven to rotate through the motor 5, the second connecting seat 32 drives the first connecting seat 31 to rotate through the universal connecting shaft 3, the first connecting seat 31 drives the first supporting column 1 to rotate, the limiting disc 14 is limited by the limiting block 18 to rotate along with the first supporting column 1 when the first supporting column 1 rotates, the limiting disc 14 drives the second supporting column 16 to rotate through the limiting disc 14, the idler wheel 17 is driven to rotate through the second supporting column 16, the steering of the aircraft on the ground is completed, the air in the air storage tank 13 can be injected into the air bag 11 through the air compressor 12, or the air in the air storage tank 11 is injected into the air storage tank 13, the hardness of the air bag 11 is changed, the first connecting seat 31 drives the first supporting column 1 to rotate, the first supporting column 1 rotates, the limiting disc 14 rotates along with the first supporting column 1 rotates, the second supporting column 16 rotates along with the first supporting column 16, the second supporting column 16 rotates along with the first supporting column, the second supporting column rotates, the second supporting column 16 rotates along the first supporting column, the second supporting column through the first supporting column, the second supporting column and the first supporting column and the aircraft, the aircraft rotates the aircraft, the second supporting column and the aircraft can rotate on the aircraft, and the second supporting frame and the aircraft, and the aircraft on the aircraft.

It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.

Claims (6)

1. An aircraft landing gear retraction mechanism comprising a universal connection shaft (3), characterized in that: the utility model provides a universal joint axle (3) lateral wall is provided with jack and damper, damper includes first support column (1), the mounting groove has been seted up to the bottom of first support column (1), be provided with gasbag (11) in the mounting groove, the rear side of first support column (1) is provided with air compressor (12) and gas holder (13), air compressor (12) are linked together with gasbag (11), be provided with spacing dish (14) in the mounting groove, spacing dish (14) set up in the bottom of gasbag (11), the bottom of spacing dish (14) is provided with second support column (16), the bottom of spacing dish (14) is provided with spring (15), spring (15) set up in the mounting groove inside wall bottom, the left and right sides of second support column (16) all are provided with gyro wheel (17) through first pivot, the spout has all been seted up on the inside wall left and right sides of mounting groove, spacing dish (14) set up in the bottom of gasbag (11), the bottom of spacing dish (14) is provided with stopper (18), the spacing dish (14) is provided with one and is located one and is put forward of the side of limiting support column (18).

2. An aircraft landing gear retraction mechanism according to claim 1 wherein: the folding and unfolding mechanism comprises a first connecting plate (2), a second connecting plate (21) is arranged on the outer side wall of the first connecting plate (2) through a second rotating shaft, a third connecting plate (22) is arranged on the outer side wall of the second connecting plate (21) through a third rotating shaft, and a hydraulic cylinder (23) is arranged on the top of the third connecting plate (22) through a fourth rotating shaft.

3. An aircraft landing gear retraction mechanism according to claim 2 wherein: the top of universal joint axle (3) is provided with second connecting seat (32) through the fifth pivot, the bottom of universal joint axle (3) is provided with first connecting seat (31) through the sixth pivot, first connecting seat (31) set up at the top of first support column (1).

4. An aircraft landing gear retraction mechanism according to claim 3 wherein: the outer side wall of the hydraulic cylinder (23) is provided with a supporting frame (4) through a seventh rotating shaft, and the third connecting plate (22) is arranged on the inner side wall of the supporting frame (4) through an eighth rotating shaft.

5. An aircraft landing gear retraction mechanism according to claim 4 wherein: the top of support frame (4) is provided with motor (5), motor (5) output runs through the top of support frame (4) and is connected with second connecting seat (32).

6. An aircraft landing gear retraction mechanism according to claim 5 wherein: the inner side wall of the support frame (4) is provided with a cross hollow column (6) through a ninth rotating shaft, the first support column (1) is arranged in the inner cavity of the cross hollow column (6), and the first connecting plate (2) is arranged on the front side of the cross hollow column (6) through a tenth rotating shaft.