Carrying support structure connected with aircraft floor clamp and door frame structure

Abstract

The utility model discloses a carrying support structure connected with an aircraft floor clamp and a door frame structure, which belongs to the technical field of aircraft ground support equipment and comprises an aircraft door frame, a door frame stop block, an aircraft floor, a floor clamp and a support body. The support body comprises a transverse base, a left longitudinal supporting frame, a right longitudinal supporting frame and a transverse connecting shaft, the two sides of the transverse base are clamped into the floor clamp, stop block locking mechanisms are arranged on the two sides of the support body, and the left side and the right side of the support body are clamped into the door frame stop blocks through the stop block locking mechanisms. The aircraft floor clamp and the door frame stop block are connected with the aircraft in a quick-assembly and quick-disassembly mode, additional tools are not needed, the aircraft does not need to be operated, the type of a carrying device is not limited, various mounting seat interfaces are fixedly connected with the carrying device, the aircraft is adaptive to various carrying devices, and double safety locking is achieved. And the connection reliability and safety are improved.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft ground support equipment, and particularly relates to a carrier bracket structure connected with an aircraft floor clip and a door frame structure. Background Technique

[0002] At present, the connection between the carrier device and the aircraft often adopts the following three technologies:

[0003] 1. Non-mechanical structure connection. For example, the docking of a ground boarding bridge with an aircraft adopts a non-contact connection. The boarding bridge adjusts its height and telescopic length according to the opening position of the aircraft cabin door, does not connect with the aircraft, and only realizes the carrier function and the carrier passage through its own structure.

[0004] 2. Fixed platform mechanical connection. Patent CN114180093 installs a fixed platform near the cabin door inside the aircraft cabin. The fixed platform is connected to the aircraft floor through threaded fasteners such as screws, and the boarding ladder is connected to the fixed platform.

[0005] 3. Structural locking connection. The boarding ladder shown in AU2014274618A1 is connected to the random boarding ladder of the aircraft through a bracket, and the bracket is limited on the random boarding ladder of the aircraft through a keyway; the boarding ladder shown in US6854147B1 is connected to the aircraft door frame through a connecting bracket, and the lower telescopic rod and the upper two-side connecting rods of the connecting bracket are connected to the upper and lower coaxial holes on both sides of the aircraft cabin door frame to realize limitation; CN115783228A designs a bracket that uses the guide groove on the aircraft door frame for locking. Both sides of the bracket are limited and locked through the telescopic pins and the specially made holes in the guide grooves on both sides of the aircraft door frame, and the bracket is connected to the boarding ladder through threaded fasteners.

[0006] The first technology is only applicable to the scenario where the airport has a boarding bridge; the second technology requires the removal of the fasteners related to the aircraft floor and then the installation of a fixed platform device. This technology involves operations on the aircraft structure, has strict operation procedures, is not conducive to rapid deployment, and has potential safety hazards; the third technology is only applicable to specific aircraft and for special carrier devices. Adopting this technology requires modification of the key parts on the aircraft door frame, and there is no double safety locking measure for the connection between the bracket and the aircraft. Therefore, we propose a carrier bracket structure connected with an aircraft floor clip and a door frame structure. Content of the Utility Model

[0007] The purpose of the utility model is to provide a carrier bracket structure connected with an aircraft floor clip and a door frame structure, so as to realize the reliable and safe connection between the carrier device and the aircraft, overcome the deficiencies of the existing technical solutions, can be quickly installed on the aircraft, does not affect the aircraft structure, does not perform any operations or modifications on the aircraft, is suitable for a variety of carrier devices, and the bracket is designed with double safety locks to improve the reliability and safety of the connection.

[0008] To achieve the above object, the utility model provides the following technical solution: A carrier bracket structure connected to an aircraft floor clip and a door frame structure, including an aircraft door frame, a door frame stop block, an aircraft floor, a floor clip and a bracket main body. The bracket main body is clamped inside the door frame stop block. The bracket main body includes a horizontal base, left and right longitudinal support frames and a horizontal connecting shaft. A carrier mounting structure is provided outside the bracket main body. One end of the carrier mounting structure is installed with a carrier device. A longitudinal support frame is provided above the horizontal base. A horizontal connecting shaft is provided inside the longitudinal support frame. Both sides of the horizontal base are clamped inside the floor clip. Stop block locking mechanisms are provided on both sides of the bracket main body. The left and right sides of the bracket main body are clamped inside the door frame stop block through the stop block locking mechanisms.

[0009] Preferably, floor clip lock pins are provided on both the left and right sides of the horizontal base. The floor clip lock pins are retractable lock pins. The floor clip lock pins include lock tongues and paddles. One end of the paddle is provided with a guide member. The guide member is slidably connected inside the horizontal base. A compression spring is provided outside the guide member. One end of the floor clip lock pin is slidably connected inside the aircraft floor clip through the compression spring. The other end of the floor clip lock pin is slidably connected inside the horizontal base through the compression spring.

[0010] Preferably, the stop block locking mechanism includes a limit card slot, a limit pin, a limit lock and an unlocking handle. The limit card slots are installed at both ends of the horizontal connecting shaft. A shaped groove is provided inside the limit card slot. The shaped groove is clamped outside the door frame stop block. The unlocking handle is provided at the top of the limit card slot. The unlocking handle is movably connected inside the limit card slot below. One end of the limit pin is provided with an unlocking paddle. The limit lock is located at one end of the limit pin. One end of the limit lock is provided with a locking slope.

[0011] Preferably, the carrier mounting structure includes a mounting seat, a connecting lock hook and a lock hook rotating shaft. One end of the mounting seat is provided with a mounting hole. The mounting seat is connected to the carrier device through bolts. The connecting lock hook is rotatably connected to the mounting seat. A torsion spring is provided outside the lock hook rotating shaft. The connecting lock hook is rotatably connected to the mounting seat.

[0012] Compared with the prior art, the beneficial effects of the utility model are:

[0013] It is connected to the aircraft through two measures of an aircraft floor clip and a door frame stop block. When one measure of connecting to the aircraft fails, it does not affect the connection safety. The connection method to the aircraft is quick installation and quick disassembly connection, without the need for additional tools and without operating on the aircraft. Moreover, it does not limit the type of carrier device. It is fixedly connected to the carrier device through a variety of mounting seat interfaces, adapting to a variety of carrier devices. The bracket is designed with double safety locks, improving the reliability and safety of the connection. Description of the Drawings

[0014] Figure 1 is a schematic diagram of the overall structure of the present utility model;

[0015] Figure 2 is a schematic diagram of the horizontal base, stop block locking mechanism and carrier mounting structure of the present utility model;

[0016] Figure 3 is a schematic diagram of the longitudinal support frame and floor clip lock pin structure of the present utility model;

[0017] Figure 4 is a schematic diagram of the connection structure between the aircraft door frame and the carrier mounting structure of the present utility model;

[0018] Figure 5 is a schematic diagram of the V-groove structure of the present utility model;

[0019] Figure 6 is a schematic diagram of the mounting seat structure of the present utility model;

[0020] Figure 7 is a schematic diagram of the connection lock hook and lock hook rotating shaft structure of the present utility model.

[0021] In the figure: 101, aircraft door frame; 102, door frame stop block; 103, floor clip; 104, aircraft floor; 105, carrier device; 201, horizontal base; 202, longitudinal support frame; 203, horizontal connecting shaft; 301, floor clip lock pin; 301B, lock tongue; 301C, dial; 302, compression spring; 303, guide; 401, limit card slot; 401B, V-groove; 402, limit pin; 402B, unlocking dial; 403, limit lock; 403B, lock inclined plane; 404, unlocking handle; 501, mounting seat; 501B, mounting hole; 501C, mounting device; 502, connection lock hook; 503, lock hook rotating shaft; 504, torsion spring. Detailed implementation manners

[0022] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0023] Please refer to Figure 1-7, the present utility model provides a technical solution for a carrier bracket structure connected to an aircraft floor clip and a door frame structure: including an aircraft door frame 101, a door frame stop block 102, an aircraft floor 104, a floor clip 103 and a bracket main body. The bracket main body is clamped inside the door frame stop block 102. The bracket main body includes a transverse base 201, left and right longitudinal support frames 202 and a transverse connecting shaft 203. A carrier installation structure is provided outside the bracket main body. One end of the carrier installation structure is installed with a carrier device 105. The longitudinal support frame 202 is arranged above the transverse base 201. The transverse connecting shaft 203 is arranged inside the longitudinal support frame 202. Both sides of the transverse base 201 are clamped inside the floor clip 103. Stop block locking mechanisms are provided on both sides of the bracket main body. The left and right sides of the bracket main body are clamped inside the door frame stop block 102 through the stop block locking mechanisms.

[0024] Specifically, floor clip lock pins 301 are provided on both the left and right sides of the transverse base 201. The floor clip lock pins 301 are retractable lock pins. The floor clip lock pins 301 include a lock tongue 301B and a dial 301C. One end of the dial 301C is provided with a guide member 303. The guide member 303 is slidably connected inside the transverse base 201. A compression spring 302 is provided outside the guide member 303. One end of the floor clip lock pin 301 is slidably connected inside the aircraft floor clip 103 through the compression spring 302. The other end of the floor clip lock pin 301 is slidably connected inside the transverse base 201 through the compression spring 302.

[0025] Specifically, the stop block locking mechanism includes a limit card slot 401, a limit pin 402, a limit lock 403 and an unlocking handle 404. The limit card slots 401 are installed at both ends of the transverse connecting shaft 203. A V-shaped groove 401B is provided inside the limit card slot 401. The V-shaped groove 401B is clamped outside the door frame stop block 102. The unlocking handle 404 is provided at the top of the limit card slot 401. The unlocking handle 404 is movably connected inside the limit card slot 401 below. One end of the limit pin 402 is provided with an unlocking dial 402B. The limit lock 403 is located at one end of the limit pin 402. One end of the limit lock 403 is provided with a lock inclined surface 403B.

[0026] Specifically, the carrier installation structure includes a mounting seat 501, a connecting lock hook 502 and a lock hook rotating shaft 503. One end of the mounting seat 501 is provided with a mounting hole 501B. The mounting seat 501 is connected to the carrier device 105 through bolts. The connecting lock hook 502 is rotatably connected to the mounting seat 501. A torsion spring 504 is provided outside the lock hook rotating shaft 503 to connect the lock hook 502 and the mounting seat for rotational connection.

[0027] In this implementation scheme, the transverse base 201 and the transverse connecting shaft 203 are connected by bolts to form an integral structure. The bottom surfaces of the transverse base 201 and the longitudinal support frames 202 are in contact with the aircraft floor 104. The aircraft floor 104 restricts the overall downward degree of freedom.

[0028] The floor clip locking pin 301 tends to move outward under the spring force of the compression spring 302. The floor clip locking pin 301 moves outward along the guide 303 until it fits against the inner wall of the transverse base 201. At this time, the locking tongue 301B extends into the floor clip 103. The floor clip 103 is fixed to the aircraft floor 104 by bolts on the aircraft. Under the restriction of the floor clips 103 on both sides of the aircraft door, the degrees of freedom of upward, inward, outward, leftward, and rightward movement of the overall structure formed by the clip locking pin 301, the transverse base 201, the transverse connecting shaft 203, and the transverse connecting shaft 203 are restricted. At this time, the connection and locking through the floor clip 103 are achieved.

[0029] The doorframe stop block 102 is installed on the aircraft doorframes 101 on both sides of the aircraft by bolts. The limit card slot 401 is fixedly connected to the transverse connecting shaft 203 by bolts. When the V-shaped grooves 401B installed on both sides of the transverse connecting shaft 203 are inserted into the doorframe stop block 102 at the same time, the degrees of freedom of inward, outward, leftward, and rightward movement of the overall structure formed by the limit card slot 401, the transverse bases 201 and 203, and the transverse connecting shaft 203 are restricted. The limit pin 402 tends to move outward under the action of the compression spring inside the transverse connecting shaft 203. The limit pin 402 moves outward along the inner wall of the transverse connecting shaft 203 until it is limited. At this time, the upper surface of the limit pin 402 extends below the doorframe stop block 102, and the degree of freedom of upward movement of the overall structure formed by the limit pin 402, the transverse base 201, the transverse connecting shaft 203, and the transverse connecting shaft 203 is formed through the lower side of the doorframe stop block 102. At this time, the connection and locking through the doorframe stop blocks 102 on both sides of the aircraft doorframe 101 are achieved.

[0030] The above-mentioned connection methods through the floor clip 103 and the doorframe stop block 102 are independent of each other. The operation of one connection does not affect the other connection; the structural compositions of the two connections are independent of each other. If one connection structure fails, it does not affect the other connection structure. Only when both the doorframe stop block 102 and the floor clip 103 fail at the same time, or the two connection structures involved in the present invention fail at the same time, can a functional failure occur.

[0031] The limit lock 403 is fixedly connected to the unlocking handle 404 by threads. The limit lock 403 passes through the inside of the limit card slot 401. A compression spring 302 is installed along the limit lock 403 inside the limit card slot 401. The limit lock 403 tends to move downward under the action of the compression spring 302 until it is limited by the inner wall of the limit card slot 401. At this time, the lock inclined surface 403B extends out of the outer surface of the limit card slot 401.

[0032] When connecting the bracket involved in the present invention to the aircraft, first push the unlocking levers 402B at both ends of the transverse connecting shaft 203 inward, overcoming the acting force of the compression spring inside the transverse connecting shaft 203. During the pushing process, the limit pins 402 contact the locking inclined surfaces 403B. Continue to push the unlocking levers 402B inward. Under the action of the limit pins 402, the limit locks 403 move upward against the spring force. Push the unlocking levers 402B until the unlocking levers 402B completely enter between the limit locks 403 and the transverse connecting shaft 203. The limit locks 403 descend under the action of the spring force and return to their original positions. At this time, the unlocking levers 402B are limited by the limit locks 403, and the two limit pins 402 remain in the non-protruding state.

[0033] Lift the overall structure and suspend it above the cabin floor. Align the V-shaped grooves 401B on both sides with the doorframe stop blocks 102, and place the overall structure downward along the doorframe stop blocks 102. At the same time, push the levers 301C inward until the floor clip locking pins 301 are limited by the transverse base 201 and cannot be pushed further. Place the overall structure on the aircraft floor 104, slightly adjust the position of the overall structure, release the levers 301C, and the floor clip locking pins 301 pop out under the action of the compression springs 302, and the locking tongues 301B extend into the floor clips 103. Then pull the unlocking handles 404 on both sides upward to release the limitation on the unlocking levers 402B. The limit pins 402 pop out under the action of the spring force, and the limit pins 402 extend to the lower side of the doorframe stop blocks 102 to complete the connection with the aircraft.

[0034] When disconnecting the bracket involved in the present invention from the aircraft, push the unlocking levers 402B at both ends of the transverse connecting shaft 203 inward, overcoming the acting force of the compression spring 302 inside the transverse connecting shaft 203. During the pushing process, the limit pins 402 contact the locking inclined surfaces 403B. Continue to push the unlocking levers 402B inward. Under the action of the limit pins 402, the limit locks 403 move upward against the spring force. Push the unlocking levers 402B until the unlocking levers 402B completely enter between the limit locks 403 and the transverse connecting shaft 203. The limit locks 403 descend under the action of the spring force and return to their original positions. At this time, the unlocking levers 402B are limited by the limit locks 403, and the limitation on the upward degree of freedom by the stop blocks is released.

[0035] At the same time, push the levers 301C on both sides inward until the floor clip locking pins 301 are limited by the transverse base 201 and cannot be pushed, at which time the degrees of freedom of the floor clip in the inward, outward, leftward, rightward, and upward directions are released.

[0036] Keep the levers 301C in their current positions, and lift the overall structure formed by the transverse base 201, the transverse connecting shaft 203, and the transverse connecting shaft 203 upward until the V-shaped grooves 401B disengage from the doorframe stop blocks 102. At this time, all degrees of freedom are released, and the connection with the aircraft is disconnected.

[0037] The mounting seat 501 is fixedly connected to the carrier 105 by bolts, so that the quick installation and quick removal of the mounting seat 501 can be achieved, and the quick installation and quick removal of the carrier 105 can be completed.

[0038] A lock hook shaft 503 is provided on the mounting seat 501 , and a torsion spring 504 is installed around the lock hook shaft 503 between the connecting lock hook 502 and the mounting seat 501 . The connecting lock hook 502 has an upward tendency when in use, that is, a locking tendency.

[0039] When the mounting base 501 needs to be connected to the transverse connecting shaft 203, the connecting lock hook 502 is pulled upward to overcome the spring force. Figure 6 The mounting seat 501 is rotated clockwise to a certain angle, and the positions of the mounting seats 501 on both sides are adjusted at the same time, and the connecting lock hook 502 is released. The connecting lock hook 502 rotates counterclockwise under the action so that it hooks the horizontal connecting shaft 203 to form a lock.

[0040] When the connection between the mounting seat 501 and the transverse connecting shaft 203 needs to be released, press Figure 6 The connecting lock hooks 502 on both sides are rotated clockwise to a certain angle so that the connecting lock hooks 502 are separated from the limit of the horizontal connecting shaft 203, and the mounting seat 501 is lifted to release the connection.

[0041] The mounting seat 501 is provided with a plurality of mounting holes 501B at different positions. According to the requirements of different carriers for the mounting position, the mounting holes 501B at different positions can be selected for connection. Meanwhile, the mounting device 501C can be adaptively adjusted according to the connecting surface of the carrier 105. It can be a flat surface connection, a curved surface connection, or other adapter connection.

[0042] The aircraft is connected to the aircraft by two measures, namely, the aircraft floor clamp 103 and the door frame stop block 102. When one of the measures for connecting to the aircraft fails, the connection safety is not affected. The connection method with the aircraft is a quick installation and quick release connection. No additional tools are required and no operation on the aircraft is required. In addition, the type of the carrier 105 is not limited. The carrier 105 is fixedly connected to the carrier 105 through a variety of mounting seats 501 interfaces. It is suitable for a variety of carriers 105. The bracket is designed with double safety locking to improve the reliability and safety of the connection.

[0043] It should be noted that in this text, relational terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the term "comprising", "including" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article or device comprising a series of elements not only includes those elements, but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article or device. Without further limitation, an element defined by the statement "comprising an..." does not exclude the presence of additional identical elements in the process, method, article or device comprising said element.

[0044] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions and variations can be made to these embodiments without departing from the principles and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A carrier support structure connected to an aircraft floor clamp and a door frame structure, comprising an aircraft door frame (101), a door frame stopper (102), an aircraft floor (104), a floor clamp (103) and a support body, characterized in that: A bracket body is clamped on the inner side of the door frame stop block (102), and the bracket body comprises a transverse base (201), left and right longitudinal support frames (202) and a transverse connecting shaft (203). A carrying installation structure is provided on the outer side of the bracket body, and a carrying device (105) is installed on one end of the carrying installation structure. A longitudinal support frame (202) is provided above the transverse base (201), and a transverse connecting shaft (203) is provided inside the longitudinal support frame (202). Both sides of the transverse base (201) are clamped inside the floor clamp (103). Stop block locking mechanisms are provided on both sides of the bracket body, and the left and right sides of the bracket body are clamped inside the door frame stop block (102) through the stop block locking mechanisms.

2. A carrier structure connected to an aircraft floor clip and a door frame structure according to claim 1, characterized in that: The left and right sides of the transverse base (201) are provided with floor clamp lock pins (301), the floor clamp lock pin (301) is a retractable lock pin, the floor clamp lock pin (301) comprises a lock tongue (301B) and a paddle (301C), one end of the paddle (301C) is provided with a guide member (303), the guide member (303) is slidably connected inside the transverse base (201), a compression spring (302) is provided outside the guide member (303), one end of the floor clamp lock pin (301) is slidably connected inside the aircraft floor clamp (103) through the compression spring (302), and the other end of the floor clamp lock pin (301) is slidably connected inside the transverse base (201) through the compression spring (302).

3. A carrier structure connected to an aircraft floor clip and a door frame structure according to claim 1, characterized in that: The stop block locking mechanism comprises a limit slot (401), a limit pin (402), a limit lock (403) and an unlocking handle (404); the limit slot (401) is installed at both ends of the transverse connecting shaft (203); a V-shaped slot (401B) is provided inside the limit slot (401); the V-shaped slot (401B) is clamped on the outside of the door frame stop block (102); an unlocking handle (404) is provided at the top of the limit slot (401); the unlocking handle (404) is movably connected to the limit slot (401) below; an unlocking paddle (402B) is provided at one end of the limit pin (402); the limit lock (403) is located at one end opposite to the limit pin (402); and a locking inclined surface (403B) is provided at one end of the limit lock (403).

4. A carrier structure connected to an aircraft floor clip and a door frame structure according to claim 1, characterized in that: The carrying and mounting structure comprises a mounting seat (501), a connecting lock hook (502) and a lock hook rotating shaft (503); a mounting hole (501B) is provided at one end of the mounting seat (501); the mounting seat (501) is connected to a carrying device (105) by means of bolts; the connecting lock hook (502) is rotatably connected to the mounting seat (501); a torsion spring (504) is provided on the outer side of the lock hook rotating shaft (503); and the connecting lock hook (502) is rotatably connected to the mounting seat.

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