CN212709945U

CN212709945U - Promote aircraft undercarriage's of steadiness brake seat

Info

Publication number: CN212709945U
Application number: CN202020572602.5U
Authority: CN
Inventors: 袁国兴
Original assignee: Guizhou Zhongyiborun Machinery Equipment Co ltd
Current assignee: Guizhou Zhongyiborun Machinery Equipment Co ltd
Priority date: 2020-04-17
Filing date: 2020-04-17
Publication date: 2021-03-16
Anticipated expiration: 2030-04-17

Abstract

The utility model discloses a promote brake seat of aircraft undercarriage of steadiness, including the mounting panel, the bottom of mounting panel is provided with the aircraft undercarriage, the spout has all been seted up, two to the inside both sides of mounting panel the equal sliding connection in inside of spout has the sliding block, the inside sliding connection of sliding block has the sliding plate, one side fixedly connected with straight-tooth plate of sliding plate, the front and the equal fixedly connected with connecting block in the back of sliding plate, the equal fixedly connected with support frame in both sides at mounting panel top, the first hydraulic stem of top fixedly connected with of support frame inner wall, the utility model relates to an undercarriage technical field. This promote aircraft landing gear's of steadiness brake seat is died the aircraft landing gear chucking lock through two piece relative motions that stabilize, has increased the stability of aircraft landing gear, prevents the phenomenon of skidding to saved the manpower, do not need artifical transport cushion to stabilize, also reduced work load.

Description

Promote aircraft undercarriage's of steadiness brake seat

Technical Field

The utility model relates to an undercarriage technical field specifically is a promote brake seat of aircraft undercarriage of steadiness.

Background

The landing gear is an accessory device which is used for supporting the airplane and moving on the ground (water surface) when the lower part of the airplane is used for taking off and landing or sliding on the ground (water surface), and the landing gear is the only part for supporting the whole airplane, so that the landing gear is an inseparable part of the airplane; without it, the aircraft cannot move on the ground.

The aircraft is in the landing after finishing, and the undercarriage pastes and is in quiescent condition on the ground, may have the phenomenon of skidding, and in order to increase the steadiness of undercarriage, there is staff's transport cushion to place in the both sides of undercarriage usually, blocks the undercarriage, increases the steadiness, but this kind of mode needs artifical transport cushion, if the aircraft sliding distance is longer, the distance of artifical transport is also long, inconvenient while still very waste time and energy.

SUMMERY OF THE UTILITY MODEL

Not enough to prior art, the utility model provides a promote aircraft landing gear's of steadiness brake seat has solved the inconvenient problem of wasting time and energy still very of artifical transport cushion simultaneously.

In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: a brake seat of an aircraft landing gear for improving stability comprises a mounting plate, wherein the bottom of the mounting plate is provided with the aircraft landing gear, two sliding grooves are formed in two sides of the inside of the mounting plate, two sliding grooves are connected with sliding blocks in a sliding mode, the sliding blocks are connected with sliding plates in a sliding mode, a straight-tooth plate is fixedly connected to one side of each sliding plate, connecting blocks are fixedly connected to the front side and the back side of each sliding plate, supporting frames are fixedly connected to two sides of the top of the mounting plate, the top of the inner wall of each supporting frame is fixedly connected with a first hydraulic rod, the first hydraulic rod is connected with an external power supply through a control switch, a grabbing frame is fixedly connected to the bottom of the first hydraulic rod, U-shaped grooves are fixed to two sides of the top of the mounting plate and located on one side where the two supporting frames are separated from each other, the outer fixed surface of first rotation pole is connected with rotary gear, the one end of first rotation pole runs through U type groove and extend to the back in U type groove, first rotation pole extends to the first worm wheel of outer fixed surface of U type groove back one end.

Further, the both sides at mounting panel top just are located two the equal fixedly connected with backup pad in the relative one side of support frame, two rotate between the relative one side of backup pad and be connected with the second dwang.

Further, the outer fixed surface of second dwang is connected with the second worm wheel, the both ends of second dwang run through two respectively the backup pad extends to two one side that the backup pad separates, the first worm of the equal fixedly connected with in both ends of second dwang, the surface of two first worms meshes with the surface of two first worm wheels respectively.

Further, the top of mounting panel just is located two one side fixedly connected with rotating electrical machines that the backup pad is relative, rotating electrical machines pass through control switch and are connected with external power, and rotating electrical machines is servo motor can just reverse, rotating electrical machines's output shaft fixedly connected with second worm, the surface of second worm and the surface meshing of second worm wheel, the top of mounting panel just is located rotating electrical machines's positive fixedly connected with balancing weight.

Furthermore, the bottoms of the two sliding plates are fixedly connected with stabilizing blocks, and the bottoms of the two stabilizing blocks are fixedly connected with friction blocks.

Furthermore, the two sides of the bottom of the mounting plate are fixedly connected with second hydraulic rods through auxiliary blocks, the second hydraulic rods are connected with an external power supply through control switches, the other ends of the second hydraulic rods are fixedly connected with insertion blocks, and the tops of the insertion blocks are slidably connected to the bottom of the mounting plate.

Compared with the prior art, the beneficial effects of the utility model are that:

the brake seat of the aircraft landing gear for improving the stability stops after the aircraft landing gear slides, the two first hydraulic rods are started to extend to drive the two grabbing frames to move downwards, and then the two sliding plates slide downwards due to the self gravity through the matching of the connecting blocks, so that the two sliding plates slide downwards to drive the two stabilizing blocks to move downwards to further drive the two friction blocks to move downwards to be attached to the ground, and the two sliding plates move downwards to drive the two straight tooth plates to move downwards to be respectively overlapped on the outer surfaces of the two rotary gears and are respectively meshed with the two rotary gears;

by starting the rotating motor, the rotating motor rotates to drive the second worm to rotate, the second worm rotates to drive the second worm wheel to rotate, the two first worms are indirectly driven to rotate by the second rotating rod, the two first worms rotate to drive the two first worm wheels to rotate, the two first rotating rods drive the two rotating gears to rotate, the two rotating gears rotate to drive the two straight tooth plates to move relatively, and further, the two straight tooth plates are used in cooperation with the sliding blocks and the sliding grooves, so that the straight tooth plates move relatively to drive the two sliding plates to move relatively, further, the two stabilizing blocks move relatively to lock two sides of the aircraft landing gear, then, the two inserting blocks are driven to move relatively to be inserted into limiting holes in the two sliding plates, so that the sliding plates cannot move left and right and cannot move up and down, and the aircraft landing gear is locked by the relative movement of the two stabilizing blocks, the stability of aircraft undercarriage has been increased, the phenomenon of skidding prevents to the manpower has been saved, does not need artifical transport cushion to stabilize, has also reduced work load.

Drawings

FIG. 1 is a schematic structural view of the present invention;

fig. 2 is a top view of the mounting plate of the present invention;

fig. 3 is a side view of the support frame of the present invention.

In the figure: the aircraft comprises a mounting plate 1, an aircraft landing gear 2, a sliding chute 3, a sliding block 4, a sliding plate 5, a straight tooth plate 6, a connecting block 7, a supporting frame 8, a first hydraulic rod 9, a grabbing frame 10, a U-shaped groove 11, a first rotating rod 12, a rotating gear 13, a first worm gear 14, a supporting plate 15, a second rotating rod 16, a second worm gear 17, a first worm 18, a rotating motor 19, a second worm 20, a balancing weight 21, a stabilizing block 22, a friction block 23, a second hydraulic rod 24 and an inserting block 25.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-3, the present invention provides a technical solution: a brake seat of an aircraft landing gear for improving stability comprises a mounting plate 1, the bottom of the mounting plate 1 is provided with an aircraft landing gear 2, two sides inside the mounting plate 1 are respectively provided with a sliding groove 3, two sliding grooves 3 are respectively connected with a sliding block 4 in a sliding manner, the sliding block 4 is connected with a sliding plate 5 in a sliding manner, one side of the sliding plate 5 is fixedly connected with a straight-tooth plate 6, the front side and the back side of the sliding plate 5 are respectively fixedly connected with a connecting block 7, two sides of the top of the mounting plate 1 are respectively fixedly connected with a supporting frame 8, the top of the inner wall of the supporting frame 8 is fixedly connected with a first hydraulic rod 9, the bottom of the first hydraulic rod 9 is fixedly connected with a grabbing frame 10, two sides of the top of the mounting plate 1 and one side of the two supporting frames 8, which are separated from each other, a U-shaped groove 11 is respectively and, one end of the first rotating rod 12 penetrates through the U-shaped groove 11 and extends to the back of the U-shaped groove 11, and a first worm wheel 14 is fixedly connected to the outer surface of one end, extending to the back of the U-shaped groove 11, of the first rotating rod 12.

The two sliding plates 5 are internally provided with limiting holes, the straight-tooth plates 6 are positioned right above the rotating gear 13, when the first hydraulic rod 9 is started to drive the grabbing frame 10 to move downwards, the sliding plates 5 do not have acting force for grabbing the frame 10, and can slide downwards due to self gravity, so that the straight-tooth plates 6 move downwards to be lapped on the outer surface of the rotating gear 13 and meshed with the outer surface of the rotating gear 13, and then the straight-tooth plates 6 are controlled to move relatively or away from each other through forward rotation or reverse rotation of the rotating gear 13.

The both sides at 1 top of mounting panel just are located the equal fixedly connected with backup pad 15 in two relative one sides of support frame 8, rotate between the relative one side of two backup pads 15 and are connected with second dwang 16, and backup pad 15 is used for supporting second dwang 16.

The outer fixed surface of second dwang 16 is connected with second worm wheel 17, and the both ends of second dwang 16 run through two backup pads 15 respectively and extend to the one side that two backup pads 15 leave mutually, and the equal first worm 18 of fixedly connected with in both ends of second dwang 16 meshes through two first worms 18 and two first worm wheels 14, and then through the rotation of two first worm wheels 14 of second dwang 16 indirect control, and then drives rotary gear 13 through first dwang 12 and rotate.

The top of mounting panel 1 just is located two relative one side fixedly connected with rotating electrical machines 19 of backup pad 15, and rotating electrical machines 19's output shaft fixedly connected with second worm 20, the top of mounting panel 1 just is located rotating electrical machines 19's positive fixedly connected with balancing weight 21, and the setting of balancing weight 21 is used for balancing rotating electrical machines 19's gravity for the atress of mounting panel 1 both sides is even, can not be heavy on one side light.

The bottom of each sliding plate 5 is fixedly connected with a stabilizing block 22, the bottom of each stabilizing block 22 is fixedly connected with a friction block 23, and the friction force between each friction block 23 and the ground is increased.

The both sides of mounting panel 1 bottom are through supplementary piece fixedly connected with second hydraulic stem 24, and the other end fixedly connected with of second hydraulic stem 24 inserts piece 25, inserts piece 25 and the inside spacing looks adaptation of sliding plate 5, after two sliding plates 5 gliding relative motion again, makes two stabilizing block 22 clip aircraft undercarriage 2, inserts spacing downthehole through inserting piece 25, realizes sliding plate 5's fixed, and then indirectly makes two stabilizing block 22 fixed.

During operation, when the aircraft landing gear 2 stops after sliding, the two first hydraulic rods 9 are started, the two first hydraulic rods 9 extend to drive the two grabbing frames 10 to move downwards, and then the two sliding plates 5 slide downwards due to self gravity through the matching of the connecting block 7, the two sliding plates 5 slide downwards to drive the two stabilizing blocks 22 to move downwards and further drive the two friction blocks 23 to move downwards to be attached to the ground, and the two sliding plates 5 move downwards to drive the two straight-tooth plates 6 to move downwards to be respectively lapped on the outer surfaces of the two rotary gears 13 and to be respectively meshed with the two rotary gears 13;

by the starting of the rotating motor 19, the rotating motor 19 rotates to drive the second worm 20 to rotate, the second worm 20 rotates to drive the second worm wheel 17 to rotate, thereby indirectly driving the two first worms 18 to rotate through the second rotating rod 16, the two first worms 18 rotate to drive the two first worm wheels 14 to rotate, so that the two first rotating rods 12 drive the two rotating gears 13 to rotate, the two rotating gears 13 drive the two straight tooth plates 6 to move relatively, further matching with the use of the sliding block 4 and the sliding chute 3, the relative movement of the straight tooth plate 6 drives the two sliding plates 5 to move relatively, and then make two steady blocks 22 relative motion give the lock with aircraft landing gear 2 both sides, through the start of two second hydraulic stems 24, drive two and insert the piece 25 relative motion, insert in the spacing downthehole of two inside sliding plates 5 to make sliding plate 5 can't remove about also can't reciprocate.

It is noted that, herein, relational terms such as first and second, and the like may be 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. Also, 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.

The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft landing gear brake seat for improving stability, comprising a mounting plate (1), characterized in that: the aircraft landing gear is characterized in that an aircraft landing gear (2) is arranged at the bottom of the mounting plate (1), sliding grooves (3) are formed in two sides of the interior of the mounting plate (1), two sliding blocks (4) are connected to the interior of the sliding grooves (3) in a sliding mode, sliding plates (5) are connected to the interior of the sliding blocks (4) in a sliding mode, a straight-tooth plate (6) is fixedly connected to one side of each sliding plate (5), connecting blocks (7) are fixedly connected to the front side and the back side of each sliding plate (5), supporting frames (8) are fixedly connected to two sides of the top of the mounting plate (1), a first hydraulic rod (9) is fixedly connected to the top of the inner wall of each supporting frame (8), a grabbing frame (10) is fixedly connected to the bottom of each first hydraulic rod (9), U-shaped grooves (11) are fixed to two sides, two all rotate between the front and the back of U type groove (11) inner wall and be connected with first rotation pole (12), the external fixed surface of first rotation pole (12) is connected with rotary gear (13), the one end of first rotation pole (12) is run through U type groove (11) and extend to the back of U type groove (11), first rotation pole (12) extend to the first worm wheel (14) of external fixed surface of U type groove (11) back one end.

2. A brake spider for an aircraft landing gear to improve stability according to claim 1, wherein: the both sides at mounting panel (1) top just are located two equal fixedly connected with backup pad (15), two in one side that support frame (8) is relative rotate between one side that backup pad (15) is relative and be connected with second dwang (16).

3. A brake spider for an aircraft landing gear to improve stability according to claim 2, wherein: the fixed surface of second dwang (16) is connected with second worm wheel (17), the both ends of second dwang (16) run through two respectively backup pad (15) and extend to two one side that backup pad (15) were kept away from mutually, the first worm (18) of the equal fixedly connected with in both ends of second dwang (16).

4. A brake spider for an aircraft landing gear to improve stability according to claim 2, wherein: the top of mounting panel (1) just is located two one side fixedly connected with rotating electrical machines (19) that backup pad (15) is relative, the output shaft fixedly connected with second worm (20) of rotating electrical machines (19), the top of mounting panel (1) just is located the positive fixedly connected with balancing weight (21) of rotating electrical machines (19).

5. A brake spider for an aircraft landing gear to improve stability according to claim 1, wherein: the bottoms of the two sliding plates (5) are fixedly connected with stabilizing blocks (22), and the bottoms of the two stabilizing blocks (22) are fixedly connected with friction blocks (23).

6. A brake spider for an aircraft landing gear to improve stability according to claim 1, wherein: two sides of the bottom of the mounting plate (1) are fixedly connected with second hydraulic rods (24) through auxiliary blocks, and the other ends of the second hydraulic rods (24) are fixedly connected with insertion blocks (25).