CN212605759U - A fixture for unmanned aerial vehicle aircraft wing - Google Patents
A fixture for unmanned aerial vehicle aircraft wing Download PDFInfo
- Publication number
- CN212605759U CN212605759U CN202021255627.9U CN202021255627U CN212605759U CN 212605759 U CN212605759 U CN 212605759U CN 202021255627 U CN202021255627 U CN 202021255627U CN 212605759 U CN212605759 U CN 212605759U
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- fixedly connected
- aerial vehicle
- unmanned aerial
- upper clamping
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Abstract
The utility model discloses a fixture for unmanned aerial vehicle aircraft wing, including punch holder, gag lever post, first drive shaft and lower plate, the below of punch holder is provided with the lower plate, the top intermediate position department of punch holder is provided with first drive shaft, and the bottom of first drive shaft extends to the inside of lower plate, the equal fixedly connected with gag lever post in both sides on lower plate top, and the top of gag lever post all extends to the top of punch holder. The utility model discloses an when unmanned aerial vehicle aircraft descends, because the action of gravity of self, the stabilizer blade can receive the impact force with ground contact back, and apply this impact force for the buffer beam, after the buffer beam received the impact force, can compress buffer spring, buffer spring can produce elasticity after compressed in spacing shell, thereby offset this impact force, buffer function when this structure has realized unmanned aerial vehicle aircraft descends, the situation that is favorable to avoiding unmanned aerial vehicle aircraft to damage takes place.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle aircraft technical field specifically is a fixture for unmanned aerial vehicle aircraft wing.
Background
Unmanned aerial vehicle aircraft is a very common equipment in modern society, mainly used technical field that takes photo by plane, and unmanned aerial vehicle aircraft mainly comprises fuselage, wing and camera device, and the wing needs to be connected with the fuselage is firm, and this just needs the fuselage to the wing centre gripping firmly, otherwise unmanned aerial vehicle aircraft is the danger that probably takes place the crash, and traditional unmanned aerial vehicle aircraft wing fixture has many weak points.
First, traditional unmanned aerial vehicle aircraft wing fixture, the centre gripping effect is not good, can take place the situation that the wing drops.
Second, the unbalanced condition of wing centre gripping can appear in traditional unmanned aerial vehicle aircraft wing fixture to influence the unmanned aerial vehicle aircraft and carry out aerial work.
Third, traditional unmanned aerial vehicle aircraft wing fixture when unmanned aerial vehicle aircraft descends, can not cushion the unmanned aerial vehicle aircraft, easily causes the unmanned aerial vehicle aircraft to damage.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a fixture for unmanned aerial vehicle aircraft wing to the wing that proposes in solving above-mentioned background art probably drops, the unbalanced and not good problem of buffering effect of wing centre gripping.
In order to achieve the above object, the utility model provides a following technical scheme: a clamping mechanism for an unmanned aerial vehicle aircraft wing comprises an upper clamping plate, a limiting rod, a first driving shaft and a lower clamping plate, wherein the lower clamping plate is arranged below the upper clamping plate, the first driving shaft is arranged at the middle position of the top end of the upper clamping plate, the bottom end of the first driving shaft extends into the lower clamping plate, the limiting rod is uniformly and fixedly connected to two sides of the top end of the lower clamping plate, the top end of the limiting rod extends to the upper part of the upper clamping plate, through holes are uniformly formed in the top end of the upper clamping plate, an upper clamping groove is uniformly formed in the bottom end of the upper clamping plate, a sleeve rod is uniformly and fixedly connected to the inner part of the bottom end of the upper clamping plate, a second compression spring is sleeved on two sides of the outer wall of the sleeve rod, a hinge rod is hinged to one side of the bottom end of the second compression spring through an articulated piece, an extrusion plate is hinged to one end, the top end of the balancing stand penetrates through the inside of the through hole and extends to the upper part of the upper clamping plate, the top end of the balancing stand is fixedly connected with a protective shell, the top end of the balancing stand inside the protective shell is fixedly connected with a level gauge, the top end of the lower clamping plate is uniformly provided with a lower clamping groove, the bottom end of the inner part of the lower clamping groove is uniformly and fixedly connected with a first compression spring, the top end of the first compression spring is fixedly connected with a fine adjustment plate, the two sides of the fine adjustment plate are respectively provided with a first sliding block, the two sides of the inner part of the lower clamping groove are respectively provided with a second sliding groove, the inner part of each second sliding groove is provided with a second sliding block, one side of each second sliding block is fixedly connected to one side of the first sliding block, the two sides of the bottom end of the fine adjustment plate are respectively provided with a second driving shaft, and the bottom end of each second driving shaft extends to the lower, the utility model discloses a spacing shell of lower plate, including lower splint, the equal fixedly connected with spacing shell in both sides of lower splint bottom, the equal fixedly connected with buffer spring in top of the inside of spacing shell, the equal fixedly connected with buffer beam in bottom of the inside buffer spring of spacing shell, and the bottom of buffer beam all extends to the below of spacing shell, the bottom of buffer beam all articulates through the articulated elements has the stabilizer blade, press from both sides the inside in groove and last clamp groove down and all install the wing, and the screw is all installed to one side on.
Preferably, the number of the limiting rods is four, and the length of the limiting rods is larger than the upward moving distance of the upper clamping plate.
Preferably, the protective housing is transparent, the spirit level is O type in shape, and the outer wall of spirit level both sides all is provided with the scale mark.
Preferably, the outer wall of first drive shaft is provided with the external screw thread structure, the inner wall of punch holder all is provided with the internal thread structure of mutually supporting with the external screw thread structure of first drive shaft.
Preferably, the number of second drive shaft sets up to eight, and the outer wall of second drive shaft all is provided with the external screw thread structure, the inner wall of lower plate all is provided with the internal thread structure who mutually supports with the external screw thread structure of second drive shaft.
Preferably, the number of the upper clamping groove and the lower clamping groove is four, the central line of the upper clamping groove and the central line of the lower clamping groove are on the same straight line, the upper clamping groove and the lower clamping groove are enclosed to form a rectangle, and the fastening grooves are formed in the two sides of the contact positions of the wing and the upper clamping groove and the lower clamping groove.
Compared with the prior art, the beneficial effects of the utility model are that:
(1) the first driving shaft is rotated by arranging the first driving shaft, the limiting rod, the upper clamping plate, the lower clamping plate, the upper clamping groove, the lower clamping groove, the extrusion plate, the hinge rod, the second compression spring and the loop bar, under the limit of the limiting rod, the first driving shaft drives the upper clamping plate downwards, the two side walls of the upper clamping groove and the lower clamping groove are inserted into the fastening grooves on the two sides of the wing, the wing is clamped between the upper clamping plate and the lower clamping plate, and when the upper clamping plate moves downwards, the extrusion plate can bear the thrust from the wings, the extrusion plate can extrude the hinge rod under the action of the thrust, under the matching of the hinge piece, the hinge rod can compress the second compression spring to two sides along the loop rod, when the second compression spring is compressed to a certain degree, the first driving shaft stops rotating, at the moment, the wing is firmly clamped, the structure realizes the stable clamping function of the wing, and is favorable for preventing the falling of the wing.
(2) By arranging the gradienters, the second driving shaft, the first sliding chute, the first sliding block, the second sliding chute, the second sliding block, the first compression spring and the fine adjustment plate, after the clamping of the wing is finished, the four gradienters are observed to find out the gradienter with liquid level difference, judging the deviation relation of the wing in the horizontal direction through the liquid level difference, then rotating the corresponding second driving shaft, under the coordination of the first sliding groove, the first sliding block, the second sliding groove, the second sliding block and the first compression spring, one side of the fine adjustment plate can move upwards, observing the liquid level change of the corresponding level instrument while rotating the second driving shaft, stopping rotating the second driving shaft when the liquid levels on the two sides of the level instrument are in zero scale, at the moment, the horizontal correction to the wing has been accomplished promptly, and this structure has realized detecting whether the wing is installed balanced function, is favorable to guaranteeing the safe of unmanned aerial vehicle aircraft aerial operation and goes on.
(3) Through being provided with the stabilizer blade, the buffer beam, buffer spring and spacing shell, when the unmanned aerial vehicle aircraft descends, because the action of gravity of self, can receive the impact force from ground, after stabilizer blade and ground contact, receive the impact force, and apply this impact force for the buffer beam, the buffer beam receives the impact force after, can compress buffer spring, buffer spring can produce elasticity after being compressed in spacing shell, thereby offset this impact force, buffer function when this structure has realized the unmanned aerial vehicle aircraft descends, be favorable to avoiding the situation that the unmanned aerial vehicle aircraft damaged to take place.
Drawings
Fig. 1 is a schematic view of the front view cross-sectional structure of the present invention.
Fig. 2 is a schematic top view of the present invention.
Fig. 3 is an enlarged schematic structural diagram of a in fig. 1 according to the present invention.
Fig. 4 is a schematic front view of the structure of the present invention.
Fig. 5 is a schematic top view of the cross-sectional structure of the upper plate of the present invention.
Fig. 6 is an enlarged schematic structural diagram of the position B in fig. 1 according to the present invention.
In the figure: 1. an upper splint; 2. a limiting rod; 3. a protective shell; 4. a through hole; 5. a first drive shaft; 6. a level gauge; 7. a balancing stand; 8. a fine adjustment plate; 9. a first compression spring; 10. a second drive shaft; 11. a lower splint; 12. a support leg; 13. a buffer rod; 14. a buffer spring; 15. a limiting shell; 16. an airfoil; 17. a propeller; 18. a first chute; 19. a loop bar; 20. a second compression spring; 21. a hinged lever; 22. a pressing plate; 23. an upper clamping groove; 24. a lower clamping groove; 25. a first slider; 26. a second chute; 27. and a second slider.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-6, the present invention provides a technical solution: a clamping mechanism for an unmanned aerial vehicle aircraft wing comprises an upper clamping plate 1, a limiting rod 2, a first driving shaft 5 and a lower clamping plate 11, wherein the lower clamping plate 11 is arranged below the upper clamping plate 1, and the first driving shaft 5 is arranged in the middle of the top end of the upper clamping plate 1;
the outer wall of first drive shaft 5 is provided with the external screw thread structure, and the inner wall of punch holder 1 all is provided with the internal thread structure who mutually supports with the external screw thread structure of first drive shaft 5.
Specifically, as shown in fig. 1, 2, 4 and 5, when the mechanism is used, first, since the outer wall of the first driving shaft 5 is provided with the external thread structure and the inner walls of the upper clamp plate 1 are each provided with the internal thread structure that is fitted with the external thread structure of the first driving shaft 5, rotating the first driving shaft 5 causes the upper clamp plate 1 to be driven.
The bottom of first drive shaft 5 extends to the inside of lower plate 11, and the both sides on lower plate 11 top all evenly fixedly connected with gag lever post 2.
The number of the limiting rods 2 is four, and the length of the limiting rods 2 is larger than the upward moving distance of the upper clamping plate 1.
Specifically, as shown in fig. 1, 2 and 4, when the mechanism is used, first, the first driving shaft 5 is driven, and the limiting rod 2 limits the motion track of the upper clamp plate 1 so that the upper clamp plate can only perform lifting motion in the vertical direction.
The top of gag lever post 2 all extends to the top of punch holder 1, through-hole 4 has evenly been seted up on the top of punch holder 1, double-layered groove 23 has evenly been seted up to the bottom of punch holder 1, the even fixedly connected with loop bar 19 in inside of 1 bottom of punch holder, the both sides of loop bar 19 outer wall all overlap and are equipped with second compression spring 20, one side of second compression spring 20 bottom all articulates through the articulated elements has hinge bar 21, the one end of hinge bar 21 all articulates through the articulated elements has stripper plate 22, the equal fixedly connected with gimbal 7 in one side of stripper plate 22, the top of gimbal 7 all runs through the top that extends to punch holder 1 in the inside of through-hole 4, the equal fixedly connected with protective housing 3 in top of gimbal 7, the equal fixedly connected with spirit level 6 in top of the inside gimbal 7 of protective housing 3.
The protective housing 3 is transparent, the spirit level 6 is O-shaped, and the outer walls of two sides of the spirit level 6 are provided with scale marks.
Specifically, as shown in fig. 1, 2 and 4, when the mechanism is used, firstly, whether a liquid level difference occurs between the liquid levels on both sides of the level gauge 6 inside the transparent protective casing 3 is observed, and then, fine adjustment is performed on the unbalanced wing 16.
The top end of the lower splint 11 is evenly provided with lower splint grooves 24.
The number of the upper clamping grooves 23 and the lower clamping grooves 24 is four, the central line of the upper clamping grooves 23 and the central line of the lower clamping grooves 24 are on the same straight line, the upper clamping grooves 23 and the lower clamping grooves 24 are enclosed to form a rectangle, and the fastening grooves are formed in the two sides of the contact positions of the wings 16 and the upper clamping grooves 23 and the lower clamping grooves 24.
Specifically, as shown in fig. 4 and 5, when the mechanism is used, first, when the upper clamping plate 1 moves downward to the upper clamping groove 23 and the lower clamping groove 24 are contacted, the rotation of the first driving shaft 5 is stopped, at this time, the upper clamping groove 23 and the lower clamping groove 24 just enclose a rectangle to wrap one end of the wing 16, and both side walls of the upper clamping groove 23 and the lower clamping groove 24 just insert into the inside of the catching grooves at both sides of one end of the wing 16.
The number of second drive shaft 10 sets up to eight, and the outer wall of second drive shaft 10 all is provided with the external screw thread structure, and the inner wall of lower plate 11 all is provided with the internal thread structure who mutually supports with the external screw thread structure of second drive shaft 10.
Specifically, as shown in fig. 1 and 4, when using the mechanism, first, since the outer wall of the second driving shaft 10 is provided with the external thread structure and the inner wall of the lower clamp plate 11 is provided with the internal thread structure which is mutually matched with the external thread structure of the second driving shaft 10, rotating the second driving shaft 10 causes one end of the trimming plate 8 to be driven.
The bottom of second drive shaft 10 all extends to the below of lower plate 11, the equal fixedly connected with spacing shell 15 in both sides of lower plate 11 bottom, the equal fixedly connected with buffer spring 14 in top of spacing shell 15 inside, the equal fixedly connected with buffer beam 13 in bottom of the inside buffer spring 14 of spacing shell 15, the bottom of buffer beam 13 all extends to the below of spacing shell 15, the bottom of buffer beam 13 all articulates through the articulated elements has stabilizer blade 12, wing 16 is all installed to the inside of lower clamp groove 24 and last clamp groove 23, screw 17 is all installed to one side on wing 16 top.
The working principle is as follows: when the device is used, firstly, the wings 16 are respectively inserted into the corresponding lower clamping grooves 24, then, the first driving shaft 5 is rotated, under the limitation of the limiting rod 2, the first driving shaft 5 can drive the upper clamping plate 1 downwards, the two side walls of the upper clamping groove 23 and the lower clamping groove 24 can be inserted into the catching grooves on the two sides of the wings 16, the extrusion plate 22 can receive thrust from the wings 16 when the upper clamping plate 1 moves downwards, the extrusion plate 22 can push one ends of the two hinged rods 21 hinged together upwards under the action of the thrust, under the cooperation of the hinged pieces, the other ends of the two hinged rods 21 can compress the second compression spring 20 towards two sides along the loop rod 19, and when the second compression spring 20 is compressed to a certain degree, the rotation of the first driving shaft 5 is stopped.
Then, four levels 6 are observed, because the levels 6 are fixedly connected with the extrusion plate 22 through the balance frame 7, and both the levels are kept horizontal, when the wing 16 is installed in an unbalanced manner, the extrusion plate 22 is also unbalanced, at this time, the levels 6 also become non-horizontal, so that a liquid level difference occurs, the level 6 with the liquid level difference is found out, the deviation relation of the wing 16 corresponding to the level 6 in the horizontal direction is judged through the liquid level difference, then, the corresponding second driving shaft 10 is rotated, one side of the fine adjustment plate 8 moves upwards under the matching of the first sliding groove 18, the first sliding block 25, the second sliding groove 26, the second sliding block 27 and the first compression spring 9, the liquid level change corresponding to the level 6 is observed while the second driving shaft 10 is rotated, and when the liquid levels on both sides of the level 6 are at zero scale, the second driving shaft 10 stops rotating.
Finally, when unmanned aerial vehicle aircraft descends, because the action of gravity of self, can receive the impact force that comes from ground reaction, after stabilizer blade 12 and ground contact, receive this impact force to conduct the buffer beam 13 that links to each other with this impact force, buffer beam 13 receives the impact force after, can compress buffer spring 14, and spacing shell 15 can be inside buffer spring 14 restriction, and buffer spring 14 can produce elasticity after being compressed in spacing shell 15, thereby offset this impact force.
It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (6)
1. The utility model provides a fixture for unmanned aerial vehicle aircraft wing, includes punch holder (1), gag lever post (2), first drive shaft (5) and lower plate (11), its characterized in that: a lower clamping plate (11) is arranged below the upper clamping plate (1), a first driving shaft (5) is arranged at the middle position of the top end of the upper clamping plate (1), the bottom end of the first driving shaft (5) extends into the lower clamping plate (11), limiting rods (2) are uniformly and fixedly connected to the two sides of the top end of the lower clamping plate (11), the top ends of the limiting rods (2) extend above the upper clamping plate (1), through holes (4) are uniformly formed in the top end of the upper clamping plate (1), upper clamping grooves (23) are uniformly formed in the bottom end of the upper clamping plate (1), sleeve rods (19) are uniformly and fixedly connected to the inner portion of the bottom end of the upper clamping plate (1), second compression springs (20) are sleeved on the two sides of the outer wall of the sleeve rods (19), hinge rods (21) are hinged to one side of the bottom ends of the second compression springs (20), and extrusion plates (22) are hinged to one ends of the hinge rods (21) through hinge pieces, one side of the extrusion plate (22) is fixedly connected with a balance frame (7), the top end of the balance frame (7) penetrates through the through hole (4) and extends to the upper part of the upper clamping plate (1), the top end of the balance frame (7) is fixedly connected with a protective shell (3), the top end of the balance frame (7) in the protective shell (3) is fixedly connected with a spirit level (6), the top end of the lower clamping plate (11) is uniformly provided with a lower clamping groove (24), the bottom end of the inner part of the lower clamping groove (24) is uniformly and fixedly connected with a first compression spring (9), the top end of the first compression spring (9) is fixedly connected with a fine adjustment plate (8), the two sides of the fine adjustment plate (8) are respectively provided with a first sliding groove (18), the inner part of the first sliding groove (18) is respectively provided with a first sliding block (25), the two sides of the inner part of the lower clamping groove (24) are respectively provided with a second sliding groove (, and a second sliding block (27) is arranged in each second sliding groove (26), one side of each second sliding block (27) is fixedly connected to one side of each first sliding block (25), the two sides of the bottom end of each fine adjustment plate (8) are respectively provided with a second driving shaft (10), the bottom end of each second driving shaft (10) extends to the lower part of the corresponding lower clamping plate (11), the two sides of the bottom end of the corresponding lower clamping plate (11) are respectively and uniformly and fixedly connected with a limiting shell (15), the top end of the inner part of each limiting shell (15) is respectively and fixedly connected with a buffer spring (14), the bottom ends of the buffer springs (14) in the limiting shells (15) are respectively and fixedly connected with buffer rods (13), the bottom ends of the buffer rods (13) extend to the lower part of the corresponding limiting shell (15), the bottom ends of the buffer rods (13) are respectively hinged with supporting legs (12), and wings (16) are respectively arranged in the lower clamping grooves (24) and the upper clamping grooves (23), and one side of the top end of each wing (16) is provided with a propeller (17).
2. A clamping mechanism for a wing of an unmanned aerial vehicle as claimed in claim 1, wherein: the number of the limiting rods (2) is four, and the length of the limiting rods (2) is larger than the upward moving distance of the upper clamping plate (1).
3. A clamping mechanism for a wing of an unmanned aerial vehicle as claimed in claim 1, wherein: the protective housing (3) is transparent, the spirit level (6) is O-shaped, and the outer walls of the two sides of the spirit level (6) are provided with scale marks.
4. A clamping mechanism for a wing of an unmanned aerial vehicle as claimed in claim 1, wherein: the outer wall of first drive shaft (5) is provided with the external screw thread structure, the inner wall of punch holder all is provided with the internal thread structure of mutually supporting with the external screw thread structure of first drive shaft (5).
5. A clamping mechanism for a wing of an unmanned aerial vehicle as claimed in claim 1, wherein: the number of second drive shaft (10) sets up to eight, and the outer wall of second drive shaft (10) all is provided with the external screw thread structure, the inner wall of lower plate (11) all is provided with the internal thread structure who mutually supports with the external screw thread structure of second drive shaft (10).
6. A clamping mechanism for a wing of an unmanned aerial vehicle as claimed in claim 1, wherein: the number of the upper clamping groove (23) and the lower clamping groove (24) is four, the central line of the upper clamping groove (23) and the central line of the lower clamping groove (24) are on the same straight line, the upper clamping groove (23) and the lower clamping groove (24) are enclosed to form a rectangle, and fastening grooves are formed in the two sides of the joint of the wing (16) and the upper clamping groove (23) and the lower clamping groove (24).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021255627.9U CN212605759U (en) | 2020-07-01 | 2020-07-01 | A fixture for unmanned aerial vehicle aircraft wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021255627.9U CN212605759U (en) | 2020-07-01 | 2020-07-01 | A fixture for unmanned aerial vehicle aircraft wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212605759U true CN212605759U (en) | 2021-02-26 |
Family
ID=74757320
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021255627.9U Active CN212605759U (en) | 2020-07-01 | 2020-07-01 | A fixture for unmanned aerial vehicle aircraft wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212605759U (en) |
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2020
- 2020-07-01 CN CN202021255627.9U patent/CN212605759U/en active Active
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Effective date of registration: 20230717 Address after: No. 861, Wuyuer Street, Bei'an City, Heihe City, Heilongjiang Province, 164000 Patentee after: Heilongjiang Shalun Agricultural Service Co.,Ltd. Address before: 226500 1003B, building 6, 999 Wanshou South Road, Chengnan street, Rugao City, Nantong City, Jiangsu Province Patentee before: Yunyi Zhichuang Aviation Technology (Nantong) Co.,Ltd. |