CN112402124B

CN112402124B - Quick assembly disassembly and locking device of aircraft airborne stretcher

Info

Publication number: CN112402124B
Application number: CN202011290086.8A
Authority: CN
Inventors: 张丽; 刘锐; 李红波; 熊彬; 刘亮亮
Original assignee: South China Aircraft Industry Co Ltd of China Aviation Industry General Aircraft Co Ltd
Current assignee: South China Aircraft Industry Co Ltd of China Aviation Industry General Aircraft Co Ltd
Priority date: 2020-11-17
Filing date: 2020-11-17
Publication date: 2023-04-14
Anticipated expiration: 2040-11-17
Also published as: CN112402124A

Abstract

The invention belongs to the field of the design of an aircraft rescue task system, and relates to a quick dismounting and locking device of an aircraft-mounted stretcher. Quick assembly disassembly and locking device includes: a sliding device, a locking device and a limiting device. Wherein, the sliding device comprises a horizontal sliding device and a vertical sliding device; the locking device comprises a stretcher fixing device; the limiting device comprises an upper limiting device, a lower limiting device, a left limiting device, a right limiting device, a front limiting device and a rear limiting device. The invention can accelerate the disassembly and assembly speed of the airplane airborne stretcher and enhance the space utilization rate of the airplane; particularly when the device is used for rescue type airplanes, the efficiency of rescuing and carrying wounded persons can be effectively improved.

Description

Quick assembly disassembly and locking device of aircraft machine carries stretcher

Technical Field

The invention belongs to the field of airplane rescue systems, and particularly relates to a quick dismounting and locking device for an airborne stretcher of an airplane.

Background

When the aircraft carries out rescue work, rescue personnel are required to quickly carry the stretcher with the wounded to the stretcher supporting arm, and after the aircraft finishes rescue task and returns, the manned stretcher needs to be quickly detached from the supporting arm, so that the wounded can be quickly treated and then delivered.

The existing rescue type airplane is limited by airplane space, number of passengers, cost and the like and cannot be provided with a hoisting device in the whole cabin, and the stretcher is carried to the supporting arm after reaching the interior of the airplane in a main mode: 2 rescue workers stand at the front end and the rear end of the stretcher station and hold the stretcher tightly, 1-2 rescue workers are positioned on the side face of the stretcher station to support the stretcher, and 3-4 rescue workers jointly place the stretcher in clamping grooves on a supporting arm of the stretcher and are locked and fixed through a clamping hoop; after the airplane returns, 3-4 rescue workers adopt the same station position as that of the stretcher during installation to release the locking clamp, lift the stretcher and quickly send the wounded backward. The form greatly encroaches on the internal space of the cabin, and reduces the number of the airborne stretchers, thereby reducing the rescue capacity of the airplane; in addition, the stretcher is complex in disassembly and assembly, more manpower is required to be invested to a single rescue task, and the airplane rescue efficiency is reduced.

Disclosure of Invention

The purpose of the invention is as follows: the invention provides a quick dismounting, mounting and locking device of an airborne stretcher of an airplane, which can solve the problems of quick dismounting, mounting and locking of the airborne stretcher of the airplane, reduce the manpower resource requirement for dismounting and mounting the stretcher, improve the rescue efficiency, realize the maximum design of the number of the airborne stretchers to a certain extent and improve the number of rescuers of the airplane.

The technical scheme of the invention is as follows: in order to achieve the above object, a device for quick release and locking of a stretcher 2 on board an aircraft is provided for quick release and locking of the stretcher 2 on a stretcher support arm 15, characterized in that it comprises the following components:

the sliding device is used for realizing the disassembly and assembly of the stretcher 2 and performing disassembly and assembly in a sliding mode through the optimized design of manual carrying and installation;

the limiting device is used for installing and positioning the stretcher 2; when the stretcher 2 is installed, the stretcher 2 is pushed in along the direction of the stretcher supporting arm 15, and when the stretcher 2 is propped against the front limit stop 26 and cannot be pushed in, the stretcher 2 is shown to reach a proper assembly position, and the subsequent assembly work such as locking and fixing of the stretcher 2 and the like can be performed;

the locking device is used for locking and fixing the stretcher 2 after being arranged at a limit position;

4 left and right limiting devices corresponding to the stretcher supporting arms 15 are symmetrically arranged on the front side, the back side and the left side of the long side 28 of the stretcher rod, and each left and right limiting device comprises lug plates 27 symmetrically arranged on the left side and the right side and is used for realizing the matching with the stretcher supporting arms 15; the sliding device is positioned at the lower part of the stretcher 2 and is respectively connected with the left limiting device and the right limiting device through bolts 18;

the limiting device comprises a front limiting stop 26 which is arranged on the upper end surface of one end, connected with the stand column 1, of the stretcher supporting arm 15 and is fixedly connected with the stretcher supporting arm 15;

the locking device comprises a quick-release pin 16, and the quick-release pin 16 is used for quickly locking the airplane onboard stretcher 2 and the supporting arm 15 thereof; the left and right limiting devices are symmetrically provided with pin holes on the lug plates 27, the stretcher supporting arms 15 are also provided with through holes corresponding to limiting positions, and after the stretcher 2 is arranged at the limiting positions, the locking is realized by inserting the quick-release pins 16 into the pin holes.

In a possible embodiment, said sliding means comprise horizontal sliding means and/or vertical sliding means, in contact with the upper surface and the left and right sides, respectively, of the stretcher support arm 15.

In a possible embodiment, the limiting device further comprises a pressure-bearing bushing 12, a through hole is formed in the center of the pressure-bearing bushing 12, pressure-bearing bushing sliding limiting grooves 14 are vertically formed in the two sides of the installation limiting position of the stretcher 2 of the stretcher supporting arm 15, when the stretcher 2 is pushed to the limiting position, the pressure-bearing bushing 12 is pushed into the pressure-bearing bushing sliding limiting grooves 14 from the lower part until the through hole in the center of the pressure-bearing bushing 12 is concentric with the through hole in the corresponding limiting position on the stretcher supporting arm 15, and further locking is performed. By arranging the pressure-bearing bush 12, on one hand, the stretcher can be prevented from shaking front and back, and meanwhile, the stretcher can bear front and back overload; on the other hand, the sliding device can be protected. After the pressure bearing bush 12 is installed, the vertical sliding device is separated from the left side and the right side of the supporting arm 15, and the vertical sliding device is prevented from being extruded and damaged when the airplane is overloaded forwards or backwards.

In one possible embodiment, the positive limit stop 26 has an inner contour that is curved to match the contour of the long side 28 of the stretcher bar, so as to achieve accurate positioning and withstand upward and lateral forces.

In one possible embodiment, the upper portion of the pressure-bearing bushing sliding limiting groove 14 is semicircular and matched with the outer circumference of the pressure-bearing bushing 12, and the height of the pressure-bearing bushing sliding limiting groove is matched with the installation position of the quick release pin 16. The loading and unloading speed is increased, the installation position does not need to be checked by manual visual inspection, and the rescue efficiency is improved.

In a possible embodiment, the bearing bush 12 is connected to the stretcher support arm 15 by a bearing bush mooring chain 13. So as to avoid the loss of the pressure bearing bush 12 and have simple and convenient operation.

In one possible embodiment, the sliding means employ a rolling connection.

In one possible embodiment, the sliding device may be a roller made of a rubber material with flame retardancy, low friction coefficient and wear resistance.

The invention has the beneficial effects that: the quick dismounting and locking device of the invention enables stretcher carriers to realize the quick dismounting of multi-layer stretchers in the aircraft passageway space without occupying the space at the head part and the tail part of the stretcher station, thus greatly saving the internal space of the cabin, increasing the number of the carrier stretchers and improving the number of the sick and wounded in the aircraft transportation. The limiting device is used for quickly installing and positioning the stretcher. When the stretcher is installed, the stretcher is quickly pushed in along the direction of the supporting arm under the condition of not using an assembling tool and visual inspection, when the stretcher is propped against the limiting device and cannot be pushed in, the stretcher is shown to reach a proper assembling position, the mounting hole position on the stretcher is coaxial with the mounting hole of the supporting arm, subsequent assembling work such as inserting a pressure-bearing bushing and a quick-release pin can be developed, the demand on manpower resources is reduced, and the airplane rescue capacity and the rescue efficiency are improved.

Drawings

FIG. 1 is a schematic view of the structure of the apparatus of the present invention

FIG. 2 is an enlarged view of a portion of FIG. 1 in the direction of A

FIG. 3 is a partial enlarged view of FIG. 1 taken along line B

FIG. 4 is a partial view taken along line C of FIG. 2

Fig. 5 is a quick-release embodiment of the airborne multi-layered stretcher.

Wherein:

1-upright post; 2, stretcher; 3-a base; 4-quick disassembling and locking device left end; 5-quick dismounting and locking device right end; 6-a stretcher limiting component; 7-horizontal sliding device; 8-horizontal slide axis of rotation; 9-U-shaped custom bolt fastener assembly; 10-U-shaped specialty bolts; 11-vertical slide axis of rotation; 12-a pressure bearing liner; 13-a pressure bearing bush mooring chain; 14-a pressure-bearing lining sliding limiting groove; 15-a stretcher support arm; 16-quick release pins; 17-support arm end face; 18-countersunk bolts; 19-bearing bush end face; 20-vertical sliding means; 21-riveting; 22-a fastener assembly; 23-U-shaped special bolt end heads; 24-quick release pin bosses; 25-quick release pin end; 26-a front limit stop; 27-a tab; 28-long side of stretcher bar.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. The described embodiments are only some embodiments of the invention, 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.

Please refer to fig. 1. In the embodiment of fig. 1, the rapid dismounting and locking device comprises 2 layers of stretchers 2, a vertical column 1, a base 3, a right end 5 of the rapid dismounting and locking device and a left end 4 of the rapid dismounting and locking device, wherein the rapid dismounting and locking device of the airborne stretcher of the airplane is arranged at the total 4 position of any layer of the airborne stretcher and is respectively positioned in the area encircled by a circle in the figure.

Please refer to fig. 2. In fig. 2, the stretcher comprises a stretcher 2, a countersunk bolt 18, a u-shaped special bolt 10, a u-shaped special bolt fastener assembly 9, a stretcher limiting assembly 6, a horizontal sliding device 7, a horizontal sliding device rotation axis 8, a pressure-bearing bush 12, a pressure-bearing bush mooring chain 13, a pressure-bearing bush sliding limiting groove 14, a stretcher supporting arm 15, a quick-release pin 16, a vertical sliding device 20, a rivet 21, a u-shaped special bolt end 23, a quick-release pin convex part 24, a quick-release pin end 25, a vertical sliding device rotation axis 11, a supporting arm end surface 17, a countersunk bolt 18, a pressure-bearing bush end surface 19, a supporting arm end surface 17 and a pressure-bearing bush end surface 19, wherein the gap between the supporting arm end surface 17 and the pressure-bearing bush end surface 19 is a. The stretcher limiting component 6 is fastened on the stretcher through a rivet 21; the countersunk head bolt 18 passes through the internal through hole structure of the horizontal sliding device 7, the stretcher positioning assembly 6, and the horizontal sliding device 7 is fixed on the stretcher positioning assembly 6 by the fastener assembly 22. The U-shaped special bolt end 23 of the U-shaped special bolt 10 is in a thread structure, the rest parts are in a polished rod structure, the inside of the vertical sliding device 20 is in a through hole structure, and after the polished rod part of the U-shaped special bolt 10 penetrates through the through hole of the vertical sliding device 20, the vertical sliding device 20 is fixed on the stretcher supporting arm 15 by the U-shaped special bolt fastener assembly 9. The bearing bush 12 is inserted into the bearing bush sliding limiting groove 14, and the stretcher limiting component 6 and the stretcher supporting arm 15 are fixed through the quick-release pin 16.

Please refer to fig. 1 and 2. The quick release and locking device right end 5 has a total of 2

horizontal slides

7 and 4 vertical slides 20 (the two rear vertical slides are not shown in fig. 2 due to the overlapping relationship). In fig. 2, the horizontal sliding means 7 are in contact with the upper surface of the stretcher support arm 15; there is a gap a between the vertical slide 20 and the left and right sides of the stretcher support arm 15. When the stretcher 2 is carried onto the stretcher support arm 15 and slides, the horizontal sliding device 7 rotates around the horizontal sliding device rotation axis 8, since the vertical sliding device 20 and the stretcher support arm 15 will not rotate due to the gap a, and during the process of pushing the stretcher to its fixed point, once the vertical sliding device 20 contacts with the stretcher support arm 15, the vertical sliding device 20 will rotate around the vertical sliding device rotation axis 11, so as to realize the function of fast and easy sliding of the stretcher 16 on the stretcher support arm 15.

Please refer to fig. 2. In fig. 2, a total of 1

quick release pin

16, 2

pressure bearing bushings

12, and 2 bushing mooring chains 13 are shown. When the stretcher limiting component 6 is installed, the end 25 of the quick-release pin is pressed, the convex part 24 of the quick-release pin is contracted into the quick-release pin 16 under the action of the spring in the quick-release pin, the quick-release pin 16 penetrates from the left side to the right side of the stretcher supporting arm 15, after the installation is in place, the end 25 of the quick-release pin is loosened, and the convex part 24 of the quick-release pin can be automatically popped out and clamped; when the stretcher is disassembled, the plug pin can be drawn out by pressing the end 25 of the quick-release pin, so that the aim of quickly disassembling and assembling the airplane-mounted stretcher is fulfilled. The pressure bearing bushings 4 are arranged on the left side and the right side of the supporting arm 15, and can transmit and bear overload force transmitted to the supporting arm by the stretcher during airplane flight, ground and emergency landing. The pressure-bearing bush mooring chain 13 fastens the pressure-bearing bush 4 to the support arm 15, and prevents the pressure-bearing bush 12 from falling off or losing in the dismounting process.

Please refer to fig. 1, fig. 2, fig. 3. In fig. 3, the quick release and locking device comprises a right end 5 and a left end 4, and the difference between the two is that the left end 4 of the quick release and locking device is provided with one more front limit stop 26. The front limit stop 26 is used for mounting and positioning the stretcher 2. When the stretcher 2 is mounted, the stretcher 2 is pushed along the upper surface of the supporting arm 15, when the stretcher 2 cannot be pushed in against the front limit stop 26, which indicates that the stretcher 2 has reached the proper assembly position, the quick release pin 16 can be directly inserted into the bearing bush 12 without the need to manually or by means of tools to calibrate the relative position between the stretcher 2 and the stretcher supporting arm 15.

Please refer to fig. 2 and fig. 4. In fig. 4, the stretcher support arm 15, the bearing bush 12, the bearing bush slide restraint groove 14 and the mooring chain 13 are included. The pressure-bearing bush 12 can slide upwards to the bottom along the bush sliding limiting groove 14 during installation to be coaxial with the quick release pin 16, and can slide downwards along the bush sliding limiting groove 14 during release.

Please refer to fig. 1, fig. 2, fig. 3, fig. 4, fig. 5. In fig. 5, when the stretcher 2 is mounted, 2 stretcher handlers are located at the side of the supporting arm 15, push the stretcher 2 to the front limit stopper 26 in the pushing direction in fig. 5, and then lock the stretcher with the quick release pins 16, thereby completing the mounting of the stretcher. When the stretcher 2 is disassembled, the quick-release pins 16 are removed, and the stretcher 2 is removed along the pulling-out direction in fig. 5, so that the disassembling work of the stretcher is completed. By adopting the quick dismounting and locking device, stretcher carriers can fully utilize the passage space of the stretcher carried from the outside to the inside of the cabin to realize the quick dismounting of the multi-layer stretcher without occupying the space at the head part (outwards in figure 5) and the tail part (inwards in figure 5) of the stretcher station.

The above-described embodiments are merely illustrative of the preferred embodiments of the present invention, which are described in detail and detail, but should not be construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the patent of the invention should be subject to the appended claims.

Claims

1. A quick assembly disassembly and locking device of an aircraft onboard stretcher for carrying out the quick assembly disassembly and locking of a stretcher (2) on a stretcher support arm (15), characterized in that it comprises the following components: the sliding device is used for realizing the disassembly and assembly of the stretcher (2) and performing disassembly and assembly in a sliding mode through manpower carrying, installation and optimization design; the limiting device is used for installing and positioning the stretcher (2); when the stretcher (2) is installed, the stretcher (2) is pushed in along the direction of the supporting arm (15), the direction of the short side of the stretcher (2) is consistent with the direction of the supporting arm (15), when the stretcher (2) abuts against the limiting device and cannot be pushed in, the stretcher (2) is shown to reach a proper assembly position, and subsequent assembly work such as locking and fixing of the stretcher (2) can be performed; the locking device is used for locking and fixing the stretcher (2) after the stretcher is installed to the limiting position; 4 left and right limiting devices corresponding to the stretcher supporting arms (15) are symmetrically arranged on the long sides (28) of the stretcher rods in the front-back and left-right directions, and each left and right limiting device comprises lug plates (27) symmetrically arranged in the left-right direction and used for realizing the matching with the stretcher supporting arms (15); the sliding device is positioned at the lower part of the stretcher (2) and is respectively connected with the left limiting device and the right limiting device through bolts (18); the limiting device comprises a front limiting stop block (26), the front limiting stop block (26) is arranged on the upper end surface of one end, connected with the stand column (1), of the stretcher supporting arm (15) and is fixedly connected with the stretcher supporting arm (15); the locking device comprises a quick-release pin (16), and the quick-release pin (16) is used for quickly locking the airplane airborne stretcher (2) and the supporting arm (15) thereof; the pin holes are symmetrically formed in the lug plates (27) of the left and right limiting devices, the through holes are formed in the corresponding limiting positions of the stretcher supporting arms (15), and after the stretcher (2) is arranged at the limiting positions, the locking is realized by inserting the quick-release pins (16) into the pin holes.

2. A device for quick release and locking of a stretcher on board an aircraft according to claim 1, characterized in that said sliding means comprise horizontal and/or vertical sliding means, in contact with the upper surface and the right and left sides, respectively, of the supporting arms (15) of the stretcher.

3. The device as claimed in claim 1, wherein the limiting device further comprises a bearing bush (12), a through hole is provided in the center of the bearing bush (12), bearing bush sliding limiting grooves (14) are vertically provided on both sides of the mounting limiting position of the stretcher (2) of the stretcher supporting arm (15), when the stretcher (2) is pushed to the limiting position, the bearing bush (12) is pushed into the bearing bush sliding limiting groove (14) from the lower part until the through hole in the center of the bearing bush (12) is concentric with the through hole in the corresponding limiting position on the stretcher supporting arm (15), and further locking is performed.

4. The device for the rapid disassembly and assembly and locking of an on-board stretcher for aircraft according to claim 1, characterized in that the inner shape of the front limit stop (26) is a cambered surface, matching the shape of the long side (28) of the stretcher bar, so as to achieve accurate positioning and be able to bear upward and lateral forces.

5. The device for quickly disassembling and locking an on-board stretcher of an aircraft according to claim 3, characterized in that the upper portion of the pressure-bearing bush sliding limiting groove (14) is semicircular and matched with the outer circumference of the pressure-bearing bush (12), and the height thereof is matched with the installation position of the quick-release pin.

6. A device for quick release and locking of a stretcher on board an aircraft according to claim 3, characterized in that said pressure-bearing bush (12) is connected to said stretcher support arm (15) by a bush mooring chain (13).

7. The device for quickly disassembling and locking an on-board stretcher for aircraft according to claim 1, wherein said sliding means is a rolling connection.

8. The device of claim 7, wherein the sliding means is a roller made of a rubber material that is flame retardant, has a low coefficient of friction, and is wear resistant.