CN217100480U - Solar unmanned aerial vehicle transportation assembly - Google Patents
Solar unmanned aerial vehicle transportation assembly Download PDFInfo
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- CN217100480U CN217100480U CN202123375580.7U CN202123375580U CN217100480U CN 217100480 U CN217100480 U CN 217100480U CN 202123375580 U CN202123375580 U CN 202123375580U CN 217100480 U CN217100480 U CN 217100480U
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Abstract
The utility model discloses a solar energy unmanned aerial vehicle transportation subassembly, include: the solar unmanned aerial vehicle transportation assembly comprises a frame, a shape following base and fixing mechanisms, wherein the shape following base is arranged on the frame, the shape following base is provided with a supporting sponge matched with the lower wing surface of a wing, the fixing mechanisms are arranged at two ends of the frame, the wing internally comprises a main beam, two ends of the main beam penetrate through the wing and are exposed at two sides of the wing, the two fixing mechanisms are respectively used for fixing the exposed ends of the main beam, and the solar unmanned aerial vehicle transportation assembly can protect the wing from colliding and deforming in the transportation process and is convenient to transport.
Description
Technical Field
The utility model belongs to the technical field of solar energy unmanned aerial vehicle transports, more specifically relates to a solar energy unmanned aerial vehicle transportation subassembly.
Background
Along with unmanned aerial vehicle's technique constantly develops, the unmanned aerial vehicle of various special demands comes in succession, and partial unmanned aerial vehicle is for assembling the structure, and the volume is huge, need disassemble in the transportation and separately transport. The wings need to be fixedly transported due to the manufacturing process and materials, and collision and deformation are avoided.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a solar energy unmanned aerial vehicle transportation subassembly to the not enough of existence among the prior art, this solar energy unmanned aerial vehicle transportation subassembly can protect the wing to avoid colliding with in the transportation with the physique warp, conveniently transports.
In order to achieve the above object, the utility model provides a solar energy unmanned aerial vehicle transportation subassembly, include:
a frame;
the conformal base is arranged on the frame, and a supporting sponge matched with the lower wing surface of the wing is arranged on the conformal base;
the two fixing mechanisms are respectively arranged at two ends of the frame;
the wing contains the girder, the both ends of girder pass the wing and expose at wing both sides, two the fixed establishment is used for fixing respectively the end that exposes of girder.
Optionally, the securing mechanism comprises:
one end of the fixed seat penetrates through the conformal base and is arranged on the frame, and the other end of the fixed seat is provided with a first groove matched with one side of the wing;
the fixed block, be provided with on the fixed block with wing opposite side matched with second recess, the fixed block with the fixing base can be dismantled and be connected.
Optionally, the lifting caster comprises a lifting caster, the lifting caster is arranged on the outer side of the frame, the lifting caster comprises:
one end of the first sleeve is connected with the frame, and one end of the second sleeve is inserted at the other end of the first sleeve in a sliding manner;
the fixed end of the driving mechanism is arranged in the first sleeve, the driving end of the driving mechanism is arranged in the second sleeve, and the driving mechanism can drive the second sleeve to extend and retract in the first sleeve;
and the universal wheel is arranged at the other end of the second sleeve.
Optionally, the driving mechanism is a worm and gear mechanism, a rotating shaft is arranged on a circle center of a worm gear of the worm and gear mechanism, and one end of the rotating shaft penetrates through the first sleeve and is exposed to form an operating end.
Optionally, still include a plurality of lifting hooks and bumper shock absorber, it is a plurality of the lifting hook can dismantle the setting on the periphery of wing, the bumper shock absorber sets up on the fixing base.
Optionally, a groove is formed in the frame, the conformal base and the wing are arranged in the groove, and the upper end of the wing does not exceed the groove.
Optionally, the stacking device further comprises a stacking frame, the structure of the stacking frame is the same as that of the frame, and the stacking frame is stacked above the frame.
Optionally, the first groove and the second groove form a receiving groove matched with the main beam.
Optionally, the conformal base comprises a plurality of flexible foam blocks, and the flexible foam blocks are spliced to form the conformal base.
Optionally, the frame is a rectangle, the both sides of frame still are provided with and consolidate guide structure, it includes to consolidate guide structure:
two side's pipes, two side's pipe sets up respectively the both sides of frame, side's pipe sets up the outside of lifting foot wheel, side's pipe through a plurality of connecting pipes with the long limit of frame is connected, the length of side's pipe is less than the length on long limit of frame, the both ends of side's pipe respectively are provided with an pipe chute, the both ends of pipe chute respectively with the one end of side's pipe with the one end on long limit of frame is connected.
The utility model provides a solar energy unmanned aerial vehicle transportation subassembly, its beneficial effect lies in:
1. this solar energy unmanned aerial vehicle transportation subassembly can protect the wing to avoid colliding with in the transportation and the physique warp, conveniently transports.
2. This solar energy unmanned aerial vehicle transportation component improves conveying efficiency through the cooperation of frame and stack frame.
3. This solar energy unmanned aerial vehicle transportation subassembly passes through the lifting foot wheel and reduces the transportation degree of difficulty, conveniently transports the loading and unloading.
Other features and advantages of the present invention will be described in detail in the detailed description which follows.
Drawings
The above and other objects, features and advantages of the present invention will become more apparent by describing in more detail exemplary embodiments thereof with reference to the attached drawings, in which like reference numerals generally represent like parts throughout the exemplary embodiments of the present invention.
Fig. 1 shows a schematic structural diagram of a solar unmanned aerial vehicle transportation assembly according to an embodiment of the present invention.
Fig. 2 shows a top view of a solar unmanned aerial vehicle transport assembly according to an embodiment of the present invention.
Fig. 3 shows a schematic structural diagram of a fixing mechanism of a solar unmanned aerial vehicle transportation assembly according to an embodiment of the present invention.
Fig. 4 shows a schematic structural diagram of a lifting caster of a solar unmanned aerial vehicle transportation assembly according to an embodiment of the present invention.
Fig. 5 shows the side view of fig. 4 of a solar drone transport assembly according to an embodiment of the present invention.
Description of reference numerals:
1. a frame; 2. superposing the frames; 3. a fixed seat; 4. a fixed block; 5. lifting caster wheels.
Detailed Description
Preferred embodiments of the present invention will be described in more detail below. While the following describes preferred embodiments of the present invention, it should be understood that the present invention may be embodied in various forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art.
Fig. 1 shows a schematic structural view of a solar unmanned aerial vehicle transportation assembly according to an embodiment of the present invention; fig. 2 shows a top view of a solar drone transport assembly according to one embodiment of the present invention; fig. 3 shows a schematic structural view of a fixing mechanism of a solar unmanned aerial vehicle transportation assembly according to an embodiment of the present invention; fig. 4 shows a schematic structural view of a lifting caster of a solar unmanned aerial vehicle transport assembly according to an embodiment of the present invention; fig. 5 shows the side view of fig. 4 of a solar drone transport assembly according to an embodiment of the present invention.
As shown in fig. 1-5, a solar unmanned aerial vehicle transportation assembly, comprising:
a frame 1;
the conformal base is arranged on the frame 1, and a supporting sponge matched with the lower wing surface of the wing is arranged on the conformal base;
the fixing mechanisms are arranged at two ends of the frame 1;
the wing contains a main beam, two ends of the main beam penetrate through the wing and are exposed at two sides of the wing, and the two fixing mechanisms are respectively used for fixing the exposed ends of the main beam.
Specifically, the protective wings are placed through the frame 1, the shape following base is attached to the lower wing surfaces of the wings, the wings are stressed uniformly, damage is reduced, the wings can be fixed at two ends through the fixing mechanism, and stability of the wings is improved.
Further, frame 1 is 6061 aluminium square tube welded overall structure, use three 200mm 100mm x 8 m's aluminium square tube as the girder, it constitutes to be 100mm x 5mm aluminium square tube welding all around, install the universal wheel on the frame 1, make things convenient for the removal of whole subassembly to use, 1 both sides of frame widen the reinforcement processing, respectively increase a square pipe in both sides, and connect through the mode that draws the support to one side, it is used for consolidating frame 1 to consolidate the outside, and use with guide pulley cooperation direction in the container when being used for transportation assembly business turn over container.
In this embodiment, the fixing mechanism includes:
one end of the fixed seat 3 penetrates through the conformal base to be arranged on the frame 1, and the other end of the fixed seat 3 is provided with a first groove matched with one side of the wing;
Specifically, be provided with the fixed slot on the frame 1, fixing base 3 can be dismantled and connect in the fixed slot, supports the wing through fixing base 3, and through the 3 fastening restriction wings of fixed block 4 cooperation fixing base, avoid the wing to rock at the removal in-process.
Further, fixed block 4 and fixing base 3 are 6061 aluminum alloy manufacturing, are provided with the hoisting ring on the fixed block 4.
Furthermore, the fixing block further comprises a bolt, a first screw hole and a second screw hole are respectively formed in the two ends of the fixing block 4 and the two ends of the fixing base 3, and the bolt penetrates through the first screw hole and the second screw hole.
In this embodiment, still include lifting caster 5, lifting caster 5 sets up the outside at frame 1, and lifting caster 5 includes:
one end of the first sleeve is connected with the frame 1, and one end of the second sleeve is inserted at the other end of the first sleeve in a sliding manner;
the fixed end of the driving mechanism is arranged in the first sleeve, the driving end of the driving mechanism is arranged in the second sleeve, and the driving mechanism can drive the second sleeve to stretch and retract in the first sleeve;
the universal wheel is arranged at the other end of the second sleeve.
Specifically, the lifting caster wheels 5 facilitate the movement of the frame 1, the height of the frame 1 can be increased during transportation, and the frame 1 can be conveniently transported to a transporting platform and a transporting vehicle.
Further, in use, the lifting caster 5 is extended to raise one end of the frame 1 from the ground to the height of the vehicle compartment, then one end of the frame 1 is inserted into the vehicle compartment and the lifting caster 5 is retracted, and then the frame 1 is completely inserted into the vehicle compartment.
In this embodiment, the driving mechanism is a worm and gear mechanism, a rotating shaft is disposed at a center of a worm gear of the worm and gear mechanism, and one end of the rotating shaft penetrates through the first sleeve and is exposed to form an operating end.
Specifically, the worm gear mechanism is driven by the rotating shaft to provide power.
In this embodiment, still include a plurality of lifting hooks and bumper shock absorber, a plurality of lifting hooks can dismantle the setting on the periphery of wing, and the bumper shock absorber setting is on fixing base 3.
Specifically, the wings are convenient to transport through the lifting hooks, and vibration in the transportation process is reduced through the shock absorbers.
In this embodiment, the frame 1 is provided with a groove, the conformal base and the wing are arranged in the groove, and the upper end of the wing does not exceed the groove.
Specifically, the wings are protected through the grooves, and hard collision is avoided.
In the embodiment, the stacking frame 2 is further included, the structure of the stacking frame 2 is the same as that of the frame 1, and the stacking frame 2 is stacked above the frame 1.
Specifically, a plurality of wings are transported at a time by being placed on the frame 1 by stacking the frames 2.
Further, the periphery of the superposition frame 2 and the frame 1 is provided with a guide table, and the guide table is matched with a guide wheel in the transfer trolley.
In this embodiment, the first and second grooves constitute receiving grooves that mate with the main beams.
Specifically, the cross-section of girder is oval, avoids circular girder at the holding tank internal rotation distortion, improves the degree of restriction.
In this embodiment, the conformal base includes a plurality of flexible foam blocks, and the plurality of flexible foam blocks are spliced into the conformal base.
Specifically, the flexible foam block material is sponge foam, and the whole shape is the dysmorphism structure, and the foam upper surface is handled along with the shape according to wing fuselage shape, guarantees that the atress of wing fuselage on the foam is relatively even, plays the guard action, and the foam is connected through the viscose with frame 1 is direct to place the foam in the recess of fixed position.
In this embodiment, the frame is the rectangle, and the both sides of frame still are provided with consolidates guide structure, consolidates guide structure and includes:
two square pipes, two square pipes set up respectively in the both sides of frame, and square pipe sets up in the outside of caster, and square pipe is connected through the long limit of a plurality of connecting pipes with the frame, and the length on the long limit of square pipe is less than the length on the long limit of frame, and the both ends of square pipe respectively are provided with an pipe chute, and the both ends of pipe chute are connected with the one end on square pipe and the one end on the long limit of frame respectively.
When this embodiment a solar energy unmanned aerial vehicle transportation component uses, use the transportation wing as an example, fix fixed establishment on the wing earlier to fix the lifting hook around the wing, remove the wing to frame 1 through the hoist on, later remove all the other wings in proper order to stack frame 2 on, place the stack frame 2 of assembled on frame 1, later transport in unison.
While various embodiments of the present invention have been described above, the above description is intended to be illustrative, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations will be apparent to those of ordinary skill in the art without departing from the scope and spirit of the described embodiments.
Claims (10)
1. The utility model provides a solar energy unmanned aerial vehicle transportation subassembly which characterized in that includes:
a frame;
the conformal base is arranged on the frame, and a supporting sponge matched with the lower wing surface of the wing is arranged on the conformal base;
the two fixing mechanisms are respectively arranged at two ends of the frame;
the wing contains the girder, the both ends of girder pass the wing and expose at wing both sides, two the fixed establishment is used for fixing respectively the end that exposes of girder.
2. The solar drone transport assembly of claim 1, wherein the securing mechanism includes:
one end of the fixed seat penetrates through the conformal base and is arranged on the frame, and the other end of the fixed seat is provided with a first groove matched with one side of the wing;
the fixed block, be provided with on the fixed block with wing opposite side matched with second recess, the fixed block with the fixing base can be dismantled and be connected.
3. The solar unmanned aerial vehicle transport assembly of claim 1, further comprising lift casters disposed on an exterior side of the frame, the lift casters comprising:
one end of the first sleeve is connected with the frame, and one end of the second sleeve is inserted at the other end of the first sleeve in a sliding manner;
the fixed end of the driving mechanism is arranged in the first sleeve, the driving end of the driving mechanism is arranged in the second sleeve, and the driving mechanism can drive the second sleeve to extend and retract in the first sleeve;
and the universal wheel is arranged at the other end of the second sleeve.
4. The solar unmanned aerial vehicle transportation assembly of claim 3, wherein the driving mechanism is a worm and gear mechanism, a rotating shaft is arranged at the center of a worm gear of the worm and gear mechanism, and one end of the rotating shaft penetrates through the first sleeve and is exposed out to form an operating end.
5. The solar unmanned aerial vehicle transportation assembly of claim 2, further comprising a plurality of lifting hooks and shock absorbers, wherein the lifting hooks are detachably arranged on the periphery of the wing, and the shock absorbers are arranged on the fixed base.
6. The solar unmanned aerial vehicle transportation assembly of claim 1, wherein a groove is formed in the frame, the conformal base and the wing are arranged in the groove, and an upper end of the wing does not exceed the groove.
7. The solar unmanned aerial vehicle transportation assembly of claim 6, further comprising a stacking frame having a structure identical to that of the frame, the stacking frame stacked above the frame.
8. The solar unmanned aerial vehicle transportation assembly of claim 2, wherein the first groove and the second groove form a receiving groove that mates with the main beam.
9. The solar unmanned aerial vehicle transport assembly of claim 1, wherein the conformable base comprises a plurality of flexible foam blocks, the flexible foam blocks being spliced into the conformable base.
10. The solar unmanned aerial vehicle transportation assembly of claim 3, wherein the frame is rectangular, and reinforcing guide structures are further disposed on two sides of the frame, and comprise:
two side's pipes, two side's pipe sets up respectively the both sides of frame, side's pipe sets up the outside of lifting foot wheel, side's pipe through a plurality of connecting pipes with the long limit of frame is connected, the length of side's pipe is less than the length on long limit of frame, the both ends of side's pipe respectively are provided with an pipe chute, the both ends of pipe chute respectively with the one end of side's pipe with the one end on long limit of frame is connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123375580.7U CN217100480U (en) | 2021-12-29 | 2021-12-29 | Solar unmanned aerial vehicle transportation assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123375580.7U CN217100480U (en) | 2021-12-29 | 2021-12-29 | Solar unmanned aerial vehicle transportation assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217100480U true CN217100480U (en) | 2022-08-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123375580.7U Active CN217100480U (en) | 2021-12-29 | 2021-12-29 | Solar unmanned aerial vehicle transportation assembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217100480U (en) |
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2021
- 2021-12-29 CN CN202123375580.7U patent/CN217100480U/en active Active
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