CN220332955U - Unmanned aerial vehicle fuselage - Google Patents
Unmanned aerial vehicle fuselage Download PDFInfo
- Publication number
- CN220332955U CN220332955U CN202322123235.7U CN202322123235U CN220332955U CN 220332955 U CN220332955 U CN 220332955U CN 202322123235 U CN202322123235 U CN 202322123235U CN 220332955 U CN220332955 U CN 220332955U
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- Prior art keywords
- fuselage
- main part
- bradyseism
- unmanned aerial
- aerial vehicle
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- 238000013016 damping Methods 0.000 claims abstract description 46
- 230000008878 coupling Effects 0.000 claims abstract description 3
- 238000010168 coupling process Methods 0.000 claims abstract description 3
- 238000005859 coupling reaction Methods 0.000 claims abstract description 3
- 238000009423 ventilation Methods 0.000 claims description 9
- 230000035939 shock Effects 0.000 claims description 6
- 238000010521 absorption reaction Methods 0.000 claims description 5
- 238000005253 cladding Methods 0.000 claims description 5
- 230000002093 peripheral effect Effects 0.000 claims description 5
- 230000001771 impaired effect Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 5
- 239000004917 carbon fiber Substances 0.000 description 5
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 238000005406 washing Methods 0.000 description 1
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- Vibration Dampers (AREA)
Abstract
The utility model belongs to the technical field of unmanned aerial vehicle technique and specifically relates to an unmanned aerial vehicle fuselage is related to, including cover and fuselage main part, be equipped with the coupling mechanism that can connect both in cover and the fuselage main part, be equipped with the mounting panel that is used for installing the component in the fuselage main part, be equipped with the spacing groove on the mounting panel, the stopper sets up in the spacing groove, the projection area of stopper and spacing groove has the partial coincidence all the time, be equipped with the bradyseism mechanism in mounting panel and the fuselage main part, the bradyseism mechanism includes a plurality of bradyseism damping bars, bradyseism damping bar both ends are connected respectively in mounting panel and fuselage main part, all overlap outside each bradyseism damping bar and are equipped with the bradyseism spring, when the unmanned aerial vehicle fuselage receives the impact, the vibrations that the impact produced are transmitted to the fuselage main part is internal, bradyseism damping bar and bradyseism spring work this moment, absorb partial vibrations, thereby reduce vibrations and lead to the impaired possibility of unmanned aerial vehicle component.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle body.
Background
The unmanned aerial vehicle body is made of carbon fiber materials, carbon fiber plates are formed by impregnating and hardening carbon fibers in the same direction with resin, the problems of difficult construction and large engineering quantity of multi-layer carbon fiber cloth can be effectively solved, and the unmanned aerial vehicle body manufactured by the carbon fiber plates has good performances of high tensile strength, corrosion resistance, shock resistance, impact resistance and the like.
The present chinese patent of utility model with bulletin number CN216546660U discloses an unmanned aerial vehicle fuselage and unmanned aerial vehicle, including well body frame, the outside of well body frame is provided with the fuselage main part, be provided with the junction cap between the fuselage main part, the downside of fuselage main part and junction cap is provided with the fuselage base, the one end of junction cap is provided with the horn seat, and the horn seat is integrated into one piece structure with the junction cap, the inboard of horn seat is provided with the installation slot, the downside of horn seat closes the installation screw soon, the other end of junction cap inserts the inboard of well body frame, and passes through screw fixed connection between junction cap and the well body frame.
According to the prior art, the unmanned aerial vehicle body is simple in structure, and when the body is impacted, the vibration generated by the impact easily affects elements in the body, so that unmanned aerial vehicle elements are damaged.
Disclosure of Invention
In order to reduce the possibility that the unmanned aerial vehicle fuselage receives the shock that the impact produced and leads to unmanned aerial vehicle component damage, the application provides an unmanned aerial vehicle fuselage.
The application provides an unmanned aerial vehicle fuselage adopts following technical scheme:
the utility model provides an unmanned aerial vehicle fuselage, including lid and fuselage main part, be equipped with the coupling mechanism that can connect both in lid and the fuselage main part, be equipped with the mounting panel that is used for installing the component in the fuselage main part, be equipped with the stopper on the mounting panel, be equipped with the spacing groove in the fuselage main part, the stopper sets up in the spacing groove, there is the partial coincidence all the time with the projection area of spacing groove the stopper, be equipped with the bradyseism mechanism in mounting panel and the fuselage main part, bradyseism mechanism includes a plurality of bradyseism damping bars, bradyseism damping bar both ends are connected respectively in mounting panel and fuselage main part, all the cover is equipped with the bradyseism spring outside each bradyseism damping bar.
Through adopting above-mentioned technical scheme, when the unmanned aerial vehicle fuselage receives the impact, in the vibrations transmission fuselage main part that the impact produced, bradyseism damping pole and bradyseism spring co-operate this moment, absorb partial vibrations to reduce vibrations and lead to the impaired possibility of unmanned aerial vehicle component.
Optionally, the fuselage main part is equipped with the bradyseism chamber at mounting panel one side far away from the bonnet, and bradyseism damping pole setting is in the bradyseism intracavity, and bradyseism damping pole both ends all are equipped with the universal ball, and the universal ball at bradyseism damping pole both ends rotates respectively and connects in mounting panel and bradyseism intracavity wall, and bradyseism damping pole is close to mounting panel one end and inclines towards the mounting panel center and set up.
Through adopting above-mentioned technical scheme, the setting of bradyseism damping pole is in mounting panel four corners and slope setting for bradyseism mechanism can absorb the vibrations that produce the impact of a plurality of directions, improves bradyseism mechanism's bradyseism effect.
Optionally, the stopper sets up at the mounting panel periphery, and the mounting panel four sides all are equipped with the stopper, and stopper keeps away from mounting panel one end cladding and has the elastic pad.
Through adopting above-mentioned technical scheme, the cladding has the elastic pad on the stopper, can absorb the vibrations that the stopper striking spacing inslot wall produced, reduces the vibrations that the stopper striking spacing inslot wall produced and leads to the possibility of unmanned aerial vehicle component damage.
Optionally, universal balls at two ends of the shock absorption damping rod are respectively connected with the midpoint of the mounting plate and the midpoint of the bottom surface of the shock absorption cavity.
Through adopting above-mentioned technical scheme, be connected with same bradyseism damping pole at mounting panel midpoint and bradyseism chamber bottom surface midpoint for the mounting panel can return to the normal position when stopping the displacement, reduces bradyseism damping pole and bradyseism spring and stretches for a long time and lead to bradyseism damping pole and bradyseism spring's bradyseism effect variation possibility.
Optionally, the corners on the machine cover and the machine body are coated with buffer strips, and the outer peripheral surfaces of the machine cover and the machine body are provided with buffer pads.
By adopting the technical scheme, when the cover and the main body of the machine body strike the ground, the ground can firstly contact the buffer strip and the buffer pad, and the buffer strip and the buffer pad can firstly shake the hand washing part.
Optionally, the connecting mechanism comprises a plurality of receiving posts, the receiving posts are arranged on one side surface of the main body close to the cover, the receiving posts are axially provided with positioning holes at one end far away from the main body along the self, the cover is provided with a plurality of positioning blocks corresponding to the positioning holes, and the positioning blocks can be clamped in the positioning holes.
Through adopting above-mentioned technical scheme, can install the bonnet in the fuselage main part with locating piece joint in the locating hole, the staff of being convenient for operates.
Optionally, the positioning block is provided with a threaded hole, the receiving column is provided with a threaded part at one end of the positioning hole far away from the positioning block, and the threaded hole and the threaded part are simultaneously connected with the same fixing bolt.
Through adopting above-mentioned technical scheme, after with locating piece joint in the locating hole, with fixing bolt Luo screw hole and screw thread portion, can further be fixed in the fuselage main part with the lid, reduce the possibility that the lid drops from the fuselage main part.
Optionally, a plurality of ventilation grooves are formed in the machine cover and the machine body, and a filter screen is arranged on each ventilation groove.
Through adopting above-mentioned technical scheme, the heat that unmanned aerial vehicle component work produced can be distributed to the outside through the ventilation groove, reduces the possibility that heat was hoarded in the fuselage main part, reduces unmanned aerial vehicle component because of the possibility of the damage of the too high temperature in the fuselage main part, and the filter screen can reduce the impurity in the environment and get into the possibility in the fuselage main part.
In summary, the present application includes at least one of the following beneficial effects:
1. when the unmanned aerial vehicle fuselage receives the impact, in the vibrations transmission fuselage main part that the impact produced, bradyseism damping pole and bradyseism spring co-operate this moment, absorb partial vibrations, and blotter and buffering strip can absorb partial vibrations in advance to reduce vibrations and lead to the impaired possibility of unmanned aerial vehicle component.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present application;
FIG. 2 is a schematic view of the interior cross-section of the fuselage body of the present application;
FIG. 3 is a schematic cross-sectional view of the connection mechanism of the present application.
Reference numerals illustrate:
1. a cover; 2. a main body of the main body; 21. a limit groove; 22. a damping cavity; 3. a connecting mechanism; 31. a receiving column; 311. positioning holes; 312. a threaded portion; 32. a positioning block; 321. a threaded hole; 33. a fixing bolt; 4. a mounting plate; 41. a limiting block; 42. an elastic pad; 5. a damping mechanism; 51. a shock-absorbing damping rod; 52. a damping spring; 53. a universal ball; 6. a buffer strip; 7. a cushion pad; 8. a ventilation groove; 9. and (5) a filter screen.
Detailed Description
Embodiments of the present application are described in further detail below with reference to the accompanying drawings.
The embodiment provides an unmanned aerial vehicle body, combining fig. 1 and 2, including cover 1 and body main part 2, cover 1 can connect in body main part 2, be equipped with the mounting panel 4 that is used for installing unmanned aerial vehicle component in the body main part 2, mounting panel 4 outer peripheral fixedly connected with stopper 41, the outside upper cladding of stopper 41 has elastic pad 42, be equipped with spacing groove 21 in the body main part 2, stopper 41 sets up in spacing groove 21, there is partial coincidence all the time in the projection face of stopper 41 and spacing groove 21, body main part 2 is equipped with the bradyseism chamber 22 in the mounting panel 4 side that is far away from cover 1, body main part 2 and mounting panel 4 are equipped with bradyseism mechanism 5 in bradyseism chamber 22, bradyseism mechanism 5 includes a plurality of bradyseism damping bars 51, bradyseism damping bar 51 overcoat is equipped with bradyseism spring 52, bradyseism damping bar 51 both ends are all fixedly connected with universal ball 53, the universal balls 53 at two ends of the damping rod 51 are respectively connected to one side surface of the mounting plate 4, which is close to the damping cavity 22, and one side surface of the damping cavity 22, which is far away from the mounting plate 4, four corners and midpoints of the mounting plate 4 and the damping cavity 22 are respectively provided with the damping rod 51, one ends of the damping rods 51, which are positioned at the four corners of the mounting plate 4 and the damping cavity 22, which are close to the mounting plate 4, are obliquely arranged towards the midpoint of the mounting plate 4, the damping rods 51, which are positioned at the four corners of the mounting plate 4 and the damping cavity 22, can cooperate with the damping springs 52 and the universal balls 53 to absorb vibration generated by the fuselage when the fuselage receives impact in all directions, so that the possibility that elements in the fuselage of the unmanned aerial vehicle are damaged due to the vibration is reduced, the damping rods 51, which are positioned at the midpoints of the mounting plate 4 and the damping cavity 22, can force the mounting plate 4 to return, and the possibility that the mounting plate 4 deviates for a long time is reduced.
The equal cladding of rim angle and fixedly connected with buffer strip 6 of lid 1 and fuselage main part 2, the outer peripheral face fixedly connected with blotter 7 of fuselage main part 2, all be equipped with a plurality of ventilation slots 8 on lid 1 and the fuselage main part 2, correspond ventilation slot 8 equal fixedly connected with filter screen 9 in lid 1 and the fuselage main part 2, buffer strip 6 and buffer pad 7 can be when the fuselage received the impact preliminary absorption part impact the vibrations that produce, further reduce unmanned aerial vehicle's interior component because of the possibility of vibrations damage, unmanned aerial vehicle's component heat can be given off to the outside through ventilation slot 8, reduce the possibility of heat hoarding in fuselage main part 2, reduce unmanned aerial vehicle component because of the possibility of the too high damage of temperature in the fuselage main part 2, filter screen 9 can reduce the dust impurity in the environment get into the possibility in the fuselage main part 2.
Referring to fig. 1 and 3, a connecting mechanism 3 capable of connecting the cover 1 and the main body 2 is arranged on the main body 2, the connecting mechanism 3 comprises a plurality of receiving posts 31, the receiving posts 31 are fixedly connected to one side of the main body 2 close to the cover 1, positioning holes 311 are coaxially formed in the receiving posts 31, a positioning block 32 is fixedly connected to one side of the cover 1 close to the main body 2 and corresponds to the positioning holes 311, the positioning block 32 can be clamped in the positioning holes 311, threaded holes 321 are coaxially formed in the positioning block 32, a threaded portion 312 is arranged at one end, far from the positioning holes 311, of the receiving posts 31, the threaded holes 321 and the threaded portions 312 are connected with the same fixing bolt 33 in a threaded manner, after the positioning block 32 is clamped in the positioning holes 311, the fixing bolt 33 is connected with the threaded holes 321 and the threaded portions 312 in a threaded manner, and the cover 1 can be fixed to the main body 2, so that workers can operate conveniently.
The principle of the application is as follows: when the main body 2 of the machine body is impacted, part of vibration generated by the impact can be firstly absorbed and relieved by the buffer strip 6 and the buffer pad 7, and the vibration transmitted to the inside of the main body 2 of the machine body can be absorbed and relieved by the buffer damping rod 51 and the buffer spring 52, so that the possibility that the elements of the unmanned aerial vehicle are damaged due to the vibration generated by the impact is reduced.
The foregoing description is only of a preferred embodiment of the present application and is not intended to limit the same, but rather, various modifications and variations are possible in light of the above teachings. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.
Claims (8)
1. The utility model provides an unmanned aerial vehicle fuselage, includes lid (1) and fuselage main part (2), is equipped with coupling mechanism (3) that can connect both on lid (1) and fuselage main part (2), its characterized in that: be equipped with mounting panel (4) that are used for mounting element on fuselage main part (2), be equipped with stopper (41) on mounting panel (4), be equipped with spacing groove (21) on fuselage main part (2), stopper (41) set up in spacing groove (21), there is the partial coincidence all the time in the projected area of stopper (41) and spacing groove (21), be equipped with on mounting panel (4) and fuselage main part (2) cushioning mechanism (5), cushioning mechanism (5) include a plurality of cushioning damping bars (51), cushioning damping bar (51) both ends are connected respectively in mounting panel (4) and fuselage main part (2), all overlap outside each cushioning damping bar (51) and are equipped with cushioning spring (52).
2. The unmanned aerial vehicle fuselage of claim 1, wherein: fuselage main part (2) are equipped with bradyseism chamber (22) in mounting panel (4) a side of being away from bonnet (1), and bradyseism damping pole (51) set up in bradyseism chamber (22), and bradyseism damping pole (51) both ends all are equipped with universal ball (53), and universal ball (53) at bradyseism damping pole (51) both ends rotate respectively and connect in mounting panel (4) and buffer chamber (22) inner wall, and bradyseism damping pole (51) are close to mounting panel (4) one end and are set up towards mounting panel (4) center slope.
3. A drone fuselage according to claim 2, wherein: the limiting blocks (41) are arranged on the outer peripheral surface of the mounting plate (4), limiting blocks (41) are arranged on four sides of the mounting plate (4), and an elastic pad (42) is coated at one end, far away from the mounting plate (4), of each limiting block (41).
4. A drone fuselage according to claim 3, wherein: the universal balls (53) at two ends of one shock absorption damping rod (51) are respectively connected with the midpoint of the mounting plate (4) and the midpoint of the bottom surface of the shock absorption cavity (22).
5. The unmanned aerial vehicle fuselage of claim 4, wherein: the corner cladding on lid (1) and fuselage main part (2) has buffer strip (6), and the outer peripheral face of lid (1) and fuselage main part (2) is equipped with blotter (7).
6. The unmanned aerial vehicle fuselage of claim 5, wherein: the connecting mechanism (3) comprises a plurality of receiving columns (31), the receiving columns (31) are arranged on one side face of the main body (2) close to the machine cover (1), the receiving columns (31) are axially provided with positioning holes (311) at one end far away from the main body (2) along the self, the machine cover (1) is provided with a plurality of positioning blocks (32) corresponding to the positioning holes (311), and the positioning blocks (32) can be clamped in the positioning holes (311).
7. The unmanned aerial vehicle fuselage of claim 6, wherein: the positioning block (32) is provided with a threaded hole (321), one end, far away from the positioning block (32), of the receiving column (31) is provided with a threaded portion (312), and the threaded hole (321) and the threaded portion (312) are simultaneously connected with the same fixing bolt (33).
8. The unmanned aerial vehicle fuselage of claim 7, wherein: a plurality of ventilation grooves (8) are formed in the machine cover (1) and the machine body (2), and a filter screen (9) is arranged on each ventilation groove (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322123235.7U CN220332955U (en) | 2023-08-08 | 2023-08-08 | Unmanned aerial vehicle fuselage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322123235.7U CN220332955U (en) | 2023-08-08 | 2023-08-08 | Unmanned aerial vehicle fuselage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220332955U true CN220332955U (en) | 2024-01-12 |
Family
ID=89455992
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322123235.7U Active CN220332955U (en) | 2023-08-08 | 2023-08-08 | Unmanned aerial vehicle fuselage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220332955U (en) |
-
2023
- 2023-08-08 CN CN202322123235.7U patent/CN220332955U/en active Active
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| GR01 | Patent grant | ||
| GR01 | Patent grant |