CN216546793U - Integrative fuselage bracket of collection dress unloading - Google Patents
Integrative fuselage bracket of collection dress unloading Download PDFInfo
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- CN216546793U CN216546793U CN202120663878.9U CN202120663878U CN216546793U CN 216546793 U CN216546793 U CN 216546793U CN 202120663878 U CN202120663878 U CN 202120663878U CN 216546793 U CN216546793 U CN 216546793U
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Abstract
The utility model provides a loading, unloading and transporting integrated machine body bracket which comprises a chassis frame, wherein one end of the chassis frame is closed, the other end of the chassis frame is provided with an opening, two ends above the chassis frame are respectively provided with a supporting frame, and a spring damping part and/or a hydraulic damping part are connected between the chassis frame and the supporting frames; the movable machine body support block is arranged above the support frame, a lead screw lifter used for lifting the movable machine body support block is arranged on the support frame, and the top of a lead screw of the lead screw lifter is connected with the movable machine body support block. The utility model can adjust the height and the pitch angle of the fuselage, can finish the loading and unloading of the fuselage without the assistance of hoisting equipment, has excellent damping effect and reduces the risk of fuselage damage.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicle transportation, in particular to a fuselage bracket integrating loading, unloading and transportation.
Background
Traditional fuselage bracket can only realize the support and the transportation of fuselage, is difficult to realize the height and the every single move regulation of fuselage, and the loading and unloading process must lift by crane the installation that equipment is supplementary could accomplish the fuselage, and its work efficiency is low, need the auxiliary of external equipment, waste time and energy and jolt because the transportation in the transportation, the shock attenuation effect is poor, has the risk that causes the damage to the unmanned aerial vehicle fuselage.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a loading, unloading and transporting integrated body bracket, which can adjust the height and the pitch angle of a body, can finish the loading and unloading of the body without the assistance of hoisting equipment, has excellent damping effect and reduces the risk of damage to the body.
The utility model is realized by the following technical scheme:
a fuselage bracket integrating loading, unloading and transporting comprises a chassis frame with one closed end and an opening at the other end, wherein supporting frames are arranged at two ends above the chassis frame, and a spring damping part and/or a hydraulic damping part are connected between the chassis frame and the supporting frames; the movable machine body support block is arranged above the support frame, a lead screw lifter used for lifting the movable machine body support block is arranged on the support frame, and the top of a lead screw of the lead screw lifter is connected with the movable machine body support block.
Optionally, the spring shock-absorbing component includes a fixed base, a connecting seat and a spring, the fixed base is connected with the chassis frame, the connecting seat is connected with the support frame, one end of the spring is connected with the fixed base, the other end of the spring is connected with the connecting seat, two sides of the top of the fixed base are provided with guide blocks, a sliding groove is vertically arranged on each guide block, and two sides of the bottom of the connecting seat are provided with sliding blocks matched with the sliding groove.
Optionally, a strip-shaped limiting hole is vertically formed in the upper edge of the guide block, and a limiting shaft matched with the limiting hole is inserted into the sliding block.
Optionally, the hydraulic damping part comprises a hydraulic damper and a connecting block, the two ends of the hydraulic damper are connected with the connecting block, the connecting block at the upper end is connected with the supporting frame, and the connecting block at the lower end is connected with the chassis frame.
Optionally, a fixed fuselage supporting block is arranged at the top of the supporting frame of the chassis frame closed section.
Optionally, the top of the movable fuselage support block and the top of the fixed fuselage support block are both provided with a gasket.
Optionally, the support frame includes a left support and a right support, and the left support and the right support are respectively provided with one screw rod lifter.
Optionally, the movable body supporting block with the opening at one end of the chassis frame comprises a left supporting block and a right supporting block, the left supporting block is connected with the top of a lead screw of the lead screw lifter on the left support, and the right supporting block is connected with the top of a lead screw of the lead screw lifter on the right support.
Optionally, the bottoms of the two ends of the chassis frame are respectively provided with a fixing seat for connecting the bottom plate of the container.
Optionally, a plurality of lifting bolts are symmetrically arranged on two sides of the chassis frame, and a binding band for binding the body is bolted to the lifting bolts.
The utility model has at least the following advantages and beneficial effects: according to the utility model, one end of the chassis frame is provided with an opening, so that the falling frame can be avoided to push the body bracket to the lower part of the body, then the movable body supporting block is lifted through the arranged lead screw lifting machine shell, the body is supported at the top of the movable body supporting block, the height of the body is adjusted through the lead screw lifting machine shell, and the heights of the movable body supporting blocks at two ends can be independently adjusted, so that the pitching angle adjustment of the body is realized, and the body loading and unloading are completed without the help of a lifting device; in addition, the arranged spring damping part and/or the hydraulic damping part can achieve good damping, and the risk of damage to the machine body is reduced.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and those skilled in the art can also obtain other related drawings based on the drawings without inventive efforts.
FIG. 1 is a schematic structural view of a pallet for loading and unloading a unitary fuselage according to the present invention;
FIG. 2 is an enlarged view of FIG. 1 at A;
FIG. 3 is an enlarged view of FIG. 1 at B;
FIG. 4 is a schematic structural view of a lead screw elevator;
FIG. 5 is a schematic view showing a structure of a spring damper;
FIG. 6 is a schematic structural view of a hydraulic damping shock absorbing member;
FIG. 7 is a schematic view of the fuselage in a transport position;
FIG. 8 is a schematic structural view of a disassembled state of the body;
FIG. 9 is a schematic view of a process bolt;
icon: 100-body bracket, 1-chassis frame, 2-support frame, 201-left support frame, 202-right support frame, 3-spring damping part, 301-fixed base, 302-connecting seat, 303-spring, 304-guide block, 305-slide block, 306-limit hole, 307-limit shaft, 4-hydraulic damping part, 401-hydraulic damper, 402-connecting block, 5-movable body support block, 501-left support block, 502-right support block, 6-lead screw lifter, 601-hand wheel, 7-fixed body support block, 8-fixed seat, 9-eyebolt, 10-process bolt, and 1001-perforating hole.
Detailed Description
As shown in fig. 1-6, a loading, unloading and transporting integrated fuselage carrier 100 comprises a chassis frame 1 with one end closed and the other end provided with an opening, wherein universal wheels are arranged at the bottom of the chassis, and the universal wheels with course lock structures are adopted to ensure that the fuselage carrier 100 can move stably.
Chassis frame 1's both ends bottom all is equipped with the fixing base 8 that is used for connecting the container bottom plate, after pushing away the container of transportation usefulness with fuselage bracket 100 during the transportation fuselage, is connected fixing base 8 and container bottom plate through the bolt, prevents to rock in the transportation.
The chassis frame 1 is provided with a plurality of suspension bolts 9 on two sides symmetrically, the suspension bolts 9 are tied with binding bands for binding the fuselage, so that the fuselage can be bound tightly through the binding bands (not shown), in practical application, a process bolt 10 (shown in fig. 9) with a through hole 1001 can be inserted into a position on the fuselage connected with the wing, and the binding bands penetrate through the through hole 1001 of the process bolt 10, so that the fuselage can be bound more firmly.
The two ends above the chassis frame 1 are both provided with the support frames 2, the chassis frame 1 and the support frames 2 are integrally in the rectangular tube structure, the rectangular tube structure has the advantages of being high in strength and strong in rigidity, and the problem that the strength and the rigidity of the machine body bracket 100 are insufficient in the machine body transportation process can be effectively solved.
The top of support frame 2 is equipped with movable fuselage tray 5, supports the fuselage through the movable fuselage tray 5 at both ends, is equipped with on the support frame 2 to be used for rising the lead screw lift 6 with movable fuselage tray 5, and the lead screw top of lead screw lift 6 is connected with movable fuselage tray 5, and the connected mode can be bolted connection or welding.
It is worth mentioning that the screw rod lifter 6 has the advantages of compact structure, small volume, light weight, wide power source, low noise, convenient installation, flexible use, high mechanical transmission efficiency, low operating force, long service life and the like, the screw rod lifter 6 is composed of a worm gear reducer and a screw rod, the worm is driven by the worm to realize speed reduction, the worm gear is equivalent to a nut of the lifting screw rod and is matched with the screw rod, the worm is an input shaft, the screw rod is an output shaft, and the screw rod is driven to lift through the rotation of the worm. In this embodiment, one end of the worm is connected with a hand wheel 601, and the rapid lifting of the screw rod can be realized by rotating the hand wheel 601.
In this embodiment, the supporting frame 2 includes a left bracket 201 and a right bracket 202, the left bracket 201 and the right bracket 202 are respectively provided with a screw rod lifter 6, and the structural stability can be ensured by the left bracket 201 and the right bracket 202; the movable fuselage support block 5 with the opening end of the chassis frame 1 comprises a left support block 501 and a right support block 502, the left support block 501 is connected with the top of a screw rod lifter 6 on the left support 201, and the right support block 502 is connected with the top of a screw rod of the screw rod lifter 6 on the right support 202, namely the movable fuselage support block 5 is divided into a left part and a right part, so that the undercarriage can be conveniently avoided, and the position of the undercarriage can be reserved.
In this embodiment, 2 tops of support frame of chassis frame 1 closed section are equipped with fixed fuselage tray 7 for the fuselage supports more stably when the transportation, the top of activity fuselage tray 5 and fixed fuselage tray 7 all refers to fuselage bottom appearance and designs, and the top of activity fuselage tray 5 and fixed fuselage tray 7 all is equipped with the liner, and the material of liner can be the felt, or other flexible pads such as rubber pad, guarantee that the fuselage is the flexonics with activity fuselage tray 5 and fixed fuselage tray 7, play certain cushioning effect.
A spring shock absorption component 3 and/or a hydraulic damping shock absorption component 4 are connected between the chassis frame 1 and the support frame 2, preferably, the spring shock absorption component 3 comprises a fixed base 301, a connecting seat 302 and a spring 303, the fixed base 301 is connected with the chassis frame 1, the connecting seat 302 is connected with the support frame 2, the connecting mode can be bolt connection or welding, one end of the spring 303 is connected with the fixed base 301, the other end of the spring 303 is connected with the connecting seat 302, the connecting mode can be welding, guide blocks 304 are arranged on two sides of the top of the fixed base 301, sliding grooves are vertically arranged on the guide blocks 304, sliding blocks 305 matched with the sliding grooves are arranged on two sides of the bottom of the connecting seat 302, bar-shaped limiting holes 306 are vertically arranged on the guide blocks 304, and limiting shafts 307 matched with the limiting holes 306 are inserted on the sliding blocks 305, by the cooperation of the stopper hole 306 and the stopper shaft 307, the failure of the spring 303 can be prevented.
The hydraulic damping part 4 comprises a hydraulic damper 401 and a connecting block 402, the two ends of the hydraulic damper 401 are connected with the connecting block 402, the connecting mode can be selected through bolt connection, the connecting block 402 at the upper end is connected with the supporting frame 2, the connecting block 402 at the lower end is connected with the chassis frame 1, and the connecting mode can be welding.
In this embodiment, spring shock attenuation part 3 and hydraulic damping shock attenuation part 4 all have the setting, play dual shock attenuation through spring shock attenuation part 3 and hydraulic damping shock attenuation part 4, and the shock attenuation effect is excellent, and the hydraulic resistor can also absorb impact energy moreover, very big reduction the risk of fuselage damage.
The using process of the utility model is as follows:
the dismounting and transporting process of the machine body comprises the following steps: when the unmanned aerial vehicle stops at the bottom surface, the body bracket 100 is pushed to the lower part of the body, the undercarriage is accommodated at the opening of the chassis frame 1, the hand wheel 601 is rotated to drive the movable body supporting block 5 to rise, so that the body is supported, and parts such as wings, horizontal tails, vertical tails and the like are taken down, namely the disassembly of the body is completed; then the hand wheel 601 is rotated to make the movable body supporting block 5 descend to the lowest (as shown in fig. 7, at this moment, the movable body supporting block 5 and the fixed body supporting block 7 are at the same height), the body and the body bracket 100 are integrally pushed into the container, the fixed seat 8 and the container are connected through the bolt to fix the body bracket 100, and the body is tightly bound through the binding band, so that the body can be transported.
The installation process of the machine body comprises the following steps: the fuselage is lifted up through the fuselage bracket 100, the hand wheel 601 is rotated to lift the fuselage to a proper height (as shown in fig. 8), the pitching angle of the fuselage is adjusted through independently adjusting the heights of the two movable fuselage support blocks 5, the fuselage is in butt joint with the wing fork lugs, after the butt joint is installed, the unmanned aerial vehicle is put down to the bottom surface, and the fuselage bracket 100 can be moved away.
The above is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and various modifications and changes will occur to those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides an integrative fuselage bracket of collection dress unloads fortune which characterized in that: the damping device comprises a chassis frame (1) with one closed end and an opening at the other end, wherein supporting frames (2) are arranged at two ends above the chassis frame (1), and a spring damping part (3) and/or a hydraulic damping part (4) are connected between the chassis frame (1) and the supporting frames (2); the movable machine body supporting block (5) is arranged above the supporting frame (2), a screw rod lifter (6) used for lifting the movable machine body supporting block (5) is arranged on the supporting frame (2), and the top of a screw rod of the screw rod lifter (6) is connected with the movable machine body supporting block (5).
2. A pallet loading and unloading integrated body as claimed in claim 1, wherein: spring shock attenuation part (3) include unable adjustment base (301), connecting seat (302) and spring (303), unable adjustment base (301) with chassis frame (1) is connected, connecting seat (302) with support frame (2) are connected, the one end of spring (303) with unable adjustment base (301) are connected, the other end of spring (303) with connecting seat (302) are connected, the top both sides of unable adjustment base (301) are equipped with guide block (304), vertical spout that is equipped with is followed in guide block (304), the bottom both sides of connecting seat (302) be equipped with spout complex slider (305).
3. A pallet loading and unloading integrated body as claimed in claim 2, wherein: a strip-shaped limiting hole (306) is vertically formed in the upper edge of the guide block (304), and a limiting shaft (307) matched with the limiting hole (306) is inserted into the sliding block (305).
4. A pallet loading and unloading integrated body as claimed in claim 1, wherein: the hydraulic damping part (4) comprises a hydraulic damper (401) and a connecting block (402), the two ends of the hydraulic damper (401) are connected with the connecting block (402), the connecting block (402) at the upper end is connected with the supporting frame (2), and the connecting block (402) at the lower end is connected with the chassis frame (1).
5. A containerized and disassemblable integral fuselage carrier of any of claims 1-4, wherein: the top of the supporting frame (2) at one closed end of the chassis frame (1) is provided with a fixed machine body supporting block (7).
6. A pallet loading and unloading integrated body as claimed in claim 5, wherein: and the tops of the movable machine body supporting block (5) and the fixed machine body supporting block (7) are respectively provided with a gasket.
7. A containerized and disassemblable integral fuselage carrier of any of claims 1-4, wherein: the supporting frame (2) comprises a left support (201) and a right support (202), and the left support (201) and the right support (202) are respectively provided with one lead screw lifter (6).
8. A pallet loading and unloading integrated body as claimed in claim 7, wherein: the movable machine body supporting block (5) with the opening one end of the chassis frame (1) comprises a left supporting block (501) and a right supporting block (502), the left supporting block (501) is connected with the top of a lead screw lifter (6) on a left support (201), and the right supporting block (502) is connected with the top of a lead screw of the lead screw lifter (6) on a right support (202).
9. A containerized and disassemblable integral fuselage carrier of any of claims 1-4, wherein: and the bottoms of the two ends of the chassis frame (1) are respectively provided with a fixing seat (8) used for connecting the bottom plate of the container.
10. A containerized and disassemblable integral fuselage carrier of any of claims 1-4, wherein: a plurality of lifting bolts (9) are symmetrically arranged on two sides of the chassis frame (1), and binding bands for binding the machine body are tied on the lifting bolts (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120663878.9U CN216546793U (en) | 2021-03-31 | 2021-03-31 | Integrative fuselage bracket of collection dress unloading |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120663878.9U CN216546793U (en) | 2021-03-31 | 2021-03-31 | Integrative fuselage bracket of collection dress unloading |
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| Publication Number | Publication Date |
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| CN216546793U true CN216546793U (en) | 2022-05-17 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202120663878.9U Active CN216546793U (en) | 2021-03-31 | 2021-03-31 | Integrative fuselage bracket of collection dress unloading |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114770079A (en) * | 2022-06-17 | 2022-07-22 | 四川腾盾科技有限公司 | Non-hoisting type disassembling and assembling method for medium and large unmanned aerial vehicle |
-
2021
- 2021-03-31 CN CN202120663878.9U patent/CN216546793U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114770079A (en) * | 2022-06-17 | 2022-07-22 | 四川腾盾科技有限公司 | Non-hoisting type disassembling and assembling method for medium and large unmanned aerial vehicle |
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