CN219904737U - Fuselage bracket for unmanned aerial vehicle - Google Patents
Fuselage bracket for unmanned aerial vehicle Download PDFInfo
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- CN219904737U CN219904737U CN202321610715.XU CN202321610715U CN219904737U CN 219904737 U CN219904737 U CN 219904737U CN 202321610715 U CN202321610715 U CN 202321610715U CN 219904737 U CN219904737 U CN 219904737U
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- 230000007246 mechanism Effects 0.000 claims abstract description 32
- 230000001360 synchronised effect Effects 0.000 claims abstract description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 239000006096 absorbing agent Substances 0.000 claims description 2
- 230000035939 shock Effects 0.000 claims description 2
- 238000000034 method Methods 0.000 abstract description 4
- 230000008569 process Effects 0.000 abstract description 4
- 238000013016 damping Methods 0.000 description 2
- 230000003028 elevating effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000004806 packaging method and process Methods 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000011084 recovery Methods 0.000 description 1
- 230000032258 transport Effects 0.000 description 1
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Abstract
The utility model discloses a fuselage bracket for an unmanned aerial vehicle, which comprises a base, and a middle bracket, a lifting bracket, a connecting piece and a guide roller which are arranged on the base, wherein the middle bracket is positioned in the middle of the base and comprises a lifting mechanism and a middle supporting block arranged at the top of the lifting mechanism; the lifting bracket comprises two groups of scissor lifts which are respectively arranged at two sides of the middle bracket and a body supporting block which is arranged at the top of the scissor lifts, and a horizontal driving mechanism for controlling the synchronous lifting of the two groups of scissor lifts is arranged between the two groups of scissor lifts; the connecting piece is located the base side, including pull rod and connecting seat, the one end and the base of pull rod are connected, and the other end of pull rod is fixed mutually with the wing connection lug of fuselage through the connecting seat. The lifting bracket supports the front part, the middle part and the rear part of the machine body respectively through the middle bracket and the lifting brackets on the two sides of the middle bracket, and meanwhile, the lifting structure is adopted, so that the machine body is convenient to use in the processes of disassembly, assembly and transportation, and the lifting bracket has the characteristics of stable structure, simplicity in operation and the like.
Description
Technical Field
The utility model belongs to the technical field of unmanned aerial vehicle transportation, and particularly relates to a fuselage bracket for an unmanned aerial vehicle.
Background
Unmanned aerial vehicle comprises fuselage, wing, V tail isotructure, need accomplish all flows of dismantling, packing, transportation and installation in the transportation, consequently, when transporting unmanned aerial vehicle, often need 10 to 15 people to cooperate, take a day time just can accomplish dismantling and packing of an aircraft, in addition, all adopt the manual work to send into the container after fuselage, wing isotructure dismantle, need more than 10 people to cooperate, waste time and energy.
In the prior art, the utility model patent with the publication number of CN217707184U discloses container type unmanned aerial vehicle packaging and transporting equipment, the equipment adopts a body bracket to realize the fixation and transportation of an unmanned aerial vehicle body, the body bracket is provided with a supporting block main structure for supporting the unmanned aerial vehicle body, the tensioning and loosening after the body is fixed can be realized through the cooperation of a diagonal draw bar, a fixed frame and a main body frame, the bottom of the main body frame is provided with casters, the transportation of the body is facilitated, the end part of the main body frame is provided with a hand draw bar, and the traction or the hand pushing of the body bracket can be realized. When the unmanned aerial vehicle body height adjusting device is used, the body bracket is only used when the body is fixed and transported, and the height of the body cannot be adjusted by matching with the unmanned aerial vehicle, so that the height of the unmanned aerial vehicle body can be adjusted by additionally using the bracket.
The utility model patent with publication number CN108502206A discloses a multi-purpose double-layer unmanned aerial vehicle body transportation bracket, which comprises a lower frame component, an upper frame component, 2 lifting components, 2 manual hydraulic pump sets, damping springs and universal casters, wherein the lower frame component is horizontally arranged at the bottom of the transportation bracket, and the universal casters are fixedly arranged on the lower surface of the lower frame component; the upper frame component is horizontally and fixedly arranged on the inner side of the lower frame component and is fixed through a damping spring; the 2 manual hydraulic pump sets are fixedly arranged on the upper surface of the lower frame assembly; the 2 lifting assemblies are fixedly arranged on the upper surface of the lower frame assembly and vertically move up and down through the upper frame assembly. During the use, accessible lifting unit and euphroe realize the fixed and the recovery of unmanned aerial vehicle fuselage, but also height around adjustable lifting unit realizes the fixed of unmanned aerial vehicle every single move gesture, but because unmanned aerial vehicle fuselage is long and weight is big, only adopts two sets of lifting unit to support unmanned aerial vehicle, and is high to the stability requirement of the manual hydraulic pump of device structure and control lifting unit lift.
Disclosure of Invention
The utility model aims to provide a fuselage bracket for an unmanned aerial vehicle, which supports the front part, the middle part and the rear part of the fuselage respectively through a middle bracket and lifting brackets on two sides of the middle bracket, and simultaneously adopts a lifting structure, so that the fuselage is convenient to use in the processes of disassembly and transportation, and has the characteristics of stable structure, simplicity in operation and the like.
The utility model is realized by the following technical scheme: the utility model provides an unmanned aerial vehicle is with fuselage bracket, includes the base, and locate middle part bracket, lift bracket, connecting piece and the guide roller on the base, middle part bracket is located the base middle part, includes elevating system and locates the middle part riding block at elevating system top; the lifting bracket comprises two groups of scissor lifts which are respectively arranged at two sides of the middle bracket and a body supporting block which is arranged at the top of the scissor lifts, and a horizontal driving mechanism for controlling the synchronous lifting of the two groups of scissor lifts is arranged between the two groups of scissor lifts; the connecting piece is located the base side, including pull rod and connecting seat, the one end and the base of pull rod are connected, and the other end of pull rod is fixed mutually with the wing connection lug of fuselage through the connecting seat.
At least one end part of the base is provided with a steering mechanism, and the steering mechanism is provided with a traction rod.
The base comprises an upper base and a lower base which are arranged up and down, a buffer device is arranged between the upper base and the lower base, the lifting mechanism, the scissor-fork type lifter and the pull rod are all arranged on the upper base, and the guide roller is arranged on the lower base.
The buffer device is a steel wire rope shock absorber for connecting the upper base and the lower base.
The lifting mechanism is a worm gear screw rod lifter.
The horizontal driving mechanism is of a double-cylinder structure which is synchronously arranged.
Compared with the prior art, the utility model has the following advantages:
(1) The airframe bracket has the functions of supporting and lifting, and can rapidly realize airframe lifting and retraction of the landing gear without auxiliary equipment, thereby rapidly completing rapid disassembly and assembly of the unmanned aerial vehicle.
(2) The utility model can realize the support of the front, middle and back parts of the machine body through the middle bracket and the lifting bracket, and has stable support structure.
(3) According to the utility model, the worm wheel screw rod lifter and the double-oil-cylinder structure are respectively adopted to match with the lifting operation of the machine body, so that the machine body bracket has a rapid lifting function, and the problems of low efficiency and high labor intensity caused by manually realizing lifting by adopting a ratchet wrench and the like are avoided.
(4) The fuselage bracket provided by the utility model is also provided with the connecting piece for fixing the fuselage, so that the stability of fuselage transportation can be improved in the unmanned plane transportation process.
Drawings
Fig. 1 is a schematic structural view of a fuselage cradle.
Fig. 2 is a schematic structural view of a wire rope damper.
Fig. 3 is a schematic structural view of a body bracket provided with a drawbar.
Fig. 4 is a schematic structural view of the steering mechanism.
Fig. 5 is a schematic structural view of the middle bracket.
Fig. 6 is a schematic structural view of a scissor lift.
Fig. 7 is a schematic structural view of the connector.
The device comprises a 1-base, a 1-upper base, a 1-2-lower base, a 2-middle bracket, a 2-1-lifting mechanism, a 2-middle bracket, a 3-lifting bracket, a 3-1-scissor-type lifter, a 3-2-body bracket, a 3-horizontal driving mechanism, a 4-connecting piece, a 4-1-pull rod, a 4-2-connecting seat, a 5-guide roller, a 6-steering mechanism, a 7-traction rod and an 8-buffer device.
Detailed Description
The present utility model will be described in further detail with reference to examples, but embodiments of the present utility model are not limited thereto.
Examples:
the embodiment is a fuselage carrier for an unmanned aerial vehicle.
As shown in fig. 1, the lifting device comprises a base 1, a middle bracket 2 arranged on the base 1, a lifting bracket 3, a connecting piece 4 and a guide roller 5, wherein the middle bracket 2 and the lifting bracket 3 have the functions of supporting and lifting at the same time, and can respectively support the front part, the middle part and the rear part of a machine body, and the connecting piece 4 is used for fixing the machine body and the base 1 so as to strengthen the stability of the machine body in the transportation process.
Specifically, in this embodiment, the base 1 includes an upper base 1-1 and a lower base 1-2 that are connected up and down, the upper base 1-1 and the lower base 1-2 may both adopt a steel frame structure, and a buffer device 8 is provided between the upper base 1-1 and the lower base 1-2, such as a wire rope damper shown in fig. 2, and during installation, the buffer device may be uniformly arranged between the upper base 1-1 and the lower base 1-2, so as to reduce impact caused by vibration in all directions on the machine body during transportation. The guide roller 5 is arranged on the lower base 1-2, so that the machine body can conveniently move along the body bracket. The middle bracket 2, the lifting bracket 3 and the connecting piece 4 are all arranged on the upper base 1-1, wherein the middle bracket 2 is positioned in the middle of the base 1 and comprises a lifting mechanism 2-1 and a middle supporting block 2-2 arranged at the top of the lifting mechanism 2-1; the lifting bracket 3 comprises two groups of scissor lifts 3-1 which are respectively arranged at two sides of the middle bracket 2 and a body supporting block 3-2 which is arranged at the top of the scissor lifts 3-1, and the lifting of the two groups of scissor lifts 3-1 can be synchronously controlled by adopting a double-cylinder structure which is synchronously arranged through arranging a horizontal driving mechanism 3-3 between the two groups of scissor lifts 3-1; the connecting piece 4 is located on the side edge of the base 1 and comprises a pull rod 4-1 and a connecting seat 4-2, one end of the pull rod 4-1 is connected with the base 1, and the other end of the pull rod 4-1 is fixed with a wing connecting lug of the airframe through the connecting seat 4-2.
In this embodiment, in order to facilitate the traction of the airframe bracket, as shown in fig. 3 and 4, steering mechanisms 6 are respectively disposed at the front end of the lower base 1-2 and the rear end of the lower base 1-2, and traction rods 7 are disposed on the steering mechanisms 6, so that the airframe bracket can be flexibly steered, and the steering mechanisms 6 can adopt any known structure as long as the angle can be adjusted by matching with the traction direction of the traction rods 7. When the unmanned aerial vehicle is specifically used, the structures of the traction rods 7 arranged at the front end of the lower base 1-2 and the rear end of the lower base 1-2 can be the same or different, and the traction rods can be matched with a traction mechanism (such as a winch or other traction equipment) to move the airframe bracket, so that the airframe bracket is pulled into a container to realize the packaging and transportation of the unmanned aerial vehicle, or the airframe bracket is pulled out of the container and then the unmanned aerial vehicle is installed.
The middle bracket 2 is used for supporting the middle part of the machine body, as shown in fig. 3, two middle brackets 2 are arranged at the middle position of the upper base 1-1, each middle bracket 2 is provided with two lifting mechanisms 2-1 and one middle supporting block 2-2, as shown in the structure of fig. 5, the lifting mechanisms 2-1 are all worm wheel screw lifters, the two worm wheel screw lifters are synchronous through a rotating shaft machine, and then lifting of the middle supporting blocks 2-2 connected with the worm wheel screw lifters is realized. The lifting bracket 3 is used for supporting the front and rear of the machine body, and can be constructed as shown in fig. 3, two groups of scissor lifts 3-1 are arranged at suitable positions on two sides of the middle bracket 2, fig. 6 is a specific embodiment of the scissor lifts 3-1, and by combining the structures shown in fig. 4 and fig. 6, one end of the bottom of the scissor lifts 3-1 is hinged to the upper base 1-1, the other end of the bottom of the scissor lifts 3-1 can horizontally move on the upper base 1-1, the machine body supporting block 3-2 is positioned at the top of the scissor lifts 3-1, and one end of the top of the scissor lifts 3-1 horizontally moves along a top platform thereof when the scissor lifts. When the two groups of scissor lifts 3-1 are synchronously driven by the horizontally telescopic double-oil-cylinder structure, the two groups of scissor lifts 3-1 can synchronously lift on the upper base 1-1, so that the lifting and supporting of the front part and the rear part of the machine body can be realized.
In this embodiment, the middle bracket 2 and the lifting bracket 3 can be matched for use, that is, when in use, the machine body supporting blocks 3-2 on the two groups of scissor lifts 3-1 are synchronously driven by the oil cylinders to rise to the highest position, so that the lifting of the machine body can be realized, the machine wheels are lifted off the ground, the landing gear of the airplane can be retracted, and then the machine body supporting blocks 3-2 on the two groups of scissor lifts 3-1 are synchronously driven by the double oil cylinder structure to fall to the lowest position, so that the support of the machine body can be realized. When the body support block 3-2 is supported, the middle support block 2-2 is lifted to a proper position by using the worm wheel screw rod lifter, so that the body support block 3-2 can be assisted to support the body. Meanwhile, the body supporting blocks 3-2 and the middle supporting block 2-2 can be manufactured in a coordinated manner with the appearance of the body, and a buffer pad is arranged on one side contacted with the body, so that scratch and damage to an airplane can be avoided.
When the fuselage is supported by the fuselage bracket, because the connecting pieces 4 are disposed at two sides of the upper base 1-1, so that the connecting pieces 4 are disposed at two sides of the fuselage, fig. 7 is a specific embodiment of the connecting pieces 4, and as shown in fig. 7, the connecting pieces 4 include a connecting base 4-2 and a pull rod 4-1, the connecting base 4-2 is fixed on the wing connecting lugs of the fuselage, one end of the pull rod 4-1 is connected with the connecting base 4-2, and the other end of the pull rod 4-1 is connected with the upper base 1-1. The pull rod 4-1 can be connected and fixed by adopting a positive and negative screw thread mechanism to connect the upper base 1-1 and the machine body, and the length of the pull rod 4-1 can be adjusted in a telescopic way.
Fuselage bracket mainly used unmanned aerial vehicle dismantles, uses when transporting and installing, for example:
when the unmanned aerial vehicle is dismounted, the body bracket is sent to the lower part of the body, the starting oil cylinder controls the two groups of scissor lifts 3-1 on the upper base 1-1 to synchronously lift to the highest position and lift the body, the landing gear of the airplane is retracted after the airplane wheel is lifted off, the oil cylinder is controlled to synchronously lower the two groups of scissor lifts 3-1 to the lowest position, and as the height of the middle bracket 2 is lower than the lowest position which can be reached by the scissor lifts 3-1, the worm wheel screw machine lifting of the middle bracket 2 is started, so that the height of the middle supporting block 2-2 stops when the height of the middle supporting block is consistent with the height of the body supporting block 3-2 on the scissor lifts 3-1, and the support of the body is realized. Then, a pull rod 4-1 with a positive and negative thread mechanism is respectively connected with an upper base 1-1 of the body bracket and a wing connecting lug of the body, so that the body is fixed.
When unmanned aerial vehicle transports, send the fuselage bracket to the container through guide roller 5, connect the capstan winch in the box with the drawbar 7 (front end) of fuselage bracket, start the capstan winch and pull into the box with the fuselage bracket in, guide roller 5 can be followed the guide slot in the box and removed to the assigned position back and stop.
When the unmanned aerial vehicle is installed, the traction rod 7 (rear end) connected with the body bracket is used for external traction, the body bracket is pulled to move out of the box body, the connecting piece 4 on the body bracket is removed, after the middle bracket 2 on the body bracket is controlled to reset, the oil cylinder is restarted to synchronously lift the two groups of scissor lifts 3-1 to the highest position, the landing gear of the aircraft is opened, then the oil cylinder is controlled to synchronously lower the two groups of scissor lifts 3-1 to the lowest position, and the body is supported by the landing gear of the aircraft.
The foregoing description is only a preferred embodiment of the present utility model, and is not intended to limit the present utility model in any way, and any simple modification, equivalent variation, etc. of the above embodiment according to the technical matter of the present utility model fall within the scope of the present utility model.
Claims (6)
1. The utility model provides an unmanned aerial vehicle is with fuselage bracket which characterized in that: the lifting device comprises a base (1), and a middle bracket (2), a lifting bracket (3), a connecting piece (4) and a guide roller (5) which are arranged on the base (1), wherein the middle bracket (2) is positioned in the middle of the base (1) and comprises a lifting mechanism (2-1) and a middle supporting block (2-2) arranged at the top of the lifting mechanism (2-1); the lifting bracket (3) comprises two groups of scissor lifts (3-1) which are respectively arranged at two sides of the middle bracket (2) and a machine body supporting block (3-2) which is arranged at the top of the scissor lifts (3-1), and a horizontal driving mechanism (3-3) for controlling the synchronous lifting of the two groups of scissor lifts (3-1) is arranged between the two groups of scissor lifts; the connecting piece (4) is located at the side edge of the base (1) and comprises a pull rod (4-1) and a connecting seat (4-2), one end of the pull rod (4-1) is connected with the base (1), and the other end of the pull rod (4-1) is fixed with a wing connecting lug of the machine body through the connecting seat (4-2).
2. The unmanned aerial vehicle fuselage cradle of claim 1, wherein: at least one end part of the base (1) is provided with a steering mechanism (6), and the steering mechanism (6) is provided with a traction rod (7).
3. The unmanned aerial vehicle fuselage cradle of claim 1, wherein: the base (1) comprises an upper base (1-1) and a lower base (1-2) which are arranged up and down, a buffer device (8) is arranged between the upper base (1-1) and the lower base (1-2), the lifting mechanism 2-1, the scissor type lifter (3-1) and the pull rod (4-1) are all arranged on the upper base (1-1), and the guide roller (5) is arranged on the lower base (1-2).
4. A fuselage cradle for an unmanned aerial vehicle according to claim 3, wherein: the buffer device (8) is a steel wire rope shock absorber for connecting the upper base (1-1) and the lower base (1-2).
5. The unmanned aerial vehicle fuselage cradle of claim 1, wherein: the lifting mechanism (2-1) is a worm gear screw rod lifter.
6. The unmanned aerial vehicle fuselage cradle of claim 1, wherein: the horizontal driving mechanism (3-3) is of a double-cylinder structure which is synchronously arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321610715.XU CN219904737U (en) | 2023-06-25 | 2023-06-25 | Fuselage bracket for unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321610715.XU CN219904737U (en) | 2023-06-25 | 2023-06-25 | Fuselage bracket for unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219904737U true CN219904737U (en) | 2023-10-27 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321610715.XU Active CN219904737U (en) | 2023-06-25 | 2023-06-25 | Fuselage bracket for unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219904737U (en) |
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2023
- 2023-06-25 CN CN202321610715.XU patent/CN219904737U/en active Active
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