CN112298546A - Rotor arm quick dismounting mechanism of hybrid wing unmanned aerial vehicle and use method thereof - Google Patents
Rotor arm quick dismounting mechanism of hybrid wing unmanned aerial vehicle and use method thereof Download PDFInfo
- Publication number
- CN112298546A CN112298546A CN202011231609.1A CN202011231609A CN112298546A CN 112298546 A CN112298546 A CN 112298546A CN 202011231609 A CN202011231609 A CN 202011231609A CN 112298546 A CN112298546 A CN 112298546A
- Authority
- CN
- China
- Prior art keywords
- rotor arm
- plates
- mounting groove
- fixedly connected
- arm body
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Clamps And Clips (AREA)
Abstract
The invention discloses a rotor arm quick dismounting mechanism of a hybrid wing unmanned aerial vehicle, which comprises an unmanned aerial vehicle, wherein four mounting seats are arranged at the top of the unmanned aerial vehicle, rotor arm bodies are arranged on two sides of each mounting seat, a second mounting groove is formed in each rotor arm body, two transverse plates which are symmetrically arranged are connected to the inner wall of one side of each second mounting groove in a sliding mode, one side, close to each other, of each transverse plate is fixedly connected with the same first tension spring, and a using method is further disclosed. The invention has the beneficial effects that: the invention has simple structure; through pulling two arm-tie to with its block in the recess, insert the rotor arm body in the third mounting groove, remove the braking of arm-tie again, and realize the installation of rotor arm body and mount pad through first block subassembly, second block subassembly and third block subassembly, only need with two arm-tie of vertical pulling of hand, make two arm-tie keep away from each other and can realize the dismantlement of rotor arm body, easy operation.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles; in particular to a mechanism for quickly disassembling and assembling rotor arms of a hybrid wing unmanned aerial vehicle and a using method thereof.
Background
The unmanned plane is called unmanned plane for short, and is an unmanned plane operated by radio remote control equipment and a self-contained program control device. The machine has no cockpit, but is provided with an automatic pilot, a program control device and other equipment. The personnel on the ground, the naval vessel or the mother aircraft remote control station can track, position, remotely control, telemeter and digitally transmit the personnel through equipment such as a radar. The aircraft can take off like a common airplane under the radio remote control or launch and lift off by a boosting rocket, and can also be thrown into the air by a mother aircraft for flying. During recovery, the aircraft can land automatically in the same way as the common aircraft landing process, and can also be recovered by a parachute or a barrier net for remote control. Can be repeatedly used for many times. The method is widely used for aerial reconnaissance, monitoring, communication, anti-submergence, electronic interference and the like.
What mixed wing unmanned aerial vehicle's on the existing market rotor adopted is the mode of folding rotor more, because connected mode makes rotor and fuselage body not separate like this, still occupied very big space, this packing and the transportation for unmanned aerial vehicle have brought very big difficulty, another shortcoming that unmanned aerial vehicle's rotor fixed connection brought is inconvenient dismantlement and installation, often bring a lot of inconveniences for the user, so we propose a mixed wing unmanned aerial vehicle rotor arm fast dismounting mechanism and application method, in order to solve the above-mentioned problem.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a mechanism for quickly disassembling and assembling rotor arms of a hybrid wing unmanned aerial vehicle and a using method thereof.
The purpose of the invention is realized by the following technical scheme: a rotor arm quick dismounting mechanism of a hybrid wing unmanned aerial vehicle comprises an unmanned aerial vehicle body, wherein four mounting seats are arranged at the top of the unmanned aerial vehicle body, rotor arm bodies are arranged on two sides of each mounting seat, a second mounting groove is formed in each rotor arm body, two transverse plates which are symmetrically arranged are connected to the inner wall of one side of each second mounting groove in a sliding mode, one side, close to each other, of each transverse plate is fixedly connected with the same first tension spring, a first clamping assembly used for clamping the rotor arm bodies and the mounting seats is arranged on the side, far away from each other, of each transverse plate, a third mounting groove and a first mounting groove are formed in each side of each mounting seat, second clamping assemblies used for clamping the rotor arm bodies and the mounting seats are arranged on the inner walls of the top and the bottom of each first mounting groove, a third clamping assembly used for clamping the rotor arm bodies and the mounting seats is arranged on the inner wall of one side of, the top inner wall and the bottom inner wall of first mounting groove all are provided with the control assembly who is used for controlling second block subassembly and third block subassembly.
First block subassembly is including respectively fixed connection two the diaphragm is two pull rods of one side of keeping away from each other, two the one end that the pull rod was kept away from each other all runs through the second mounting groove and rotates and be connected with the arm-tie, the both sides inner wall swivelling joint of second mounting groove has two first pivots that the symmetry set up, the outer wall fixedly connected with L board of first pivot, the one end of L board is rotated with one side of pull rod and is connected, first patchhole has all been seted up to the top and the bottom of rotor arm body.
The second block subassembly includes the fourth extension spring of difference fixed connection at the top inner wall of first mounting groove and bottom inner wall, two the equal first push pedal of fixedly connected with in one side that the fourth extension spring is close to each other, inside first push pedal runs through first mounting groove and extends to the third mounting groove, first push pedal and first plug-in hole looks adaptation.
The third clamping component comprises a third tension spring fixedly connected to the inner wall of one side of the first mounting groove, one end of the third tension spring is fixedly connected with a connecting block, one side of the connecting block is fixedly connected with a connecting rod, the inner wall of one side of the third mounting groove is fixedly connected with a fixed box, one end of the connecting rod penetrates through the first mounting groove and extends to the inside of the fixed box, one end of the connecting rod is fixedly connected with a semicircular plate, the inner walls of the two sides of the fixed box are slidably connected with two symmetrically arranged clamping blocks, the ends, far away from each other, of the two clamping blocks penetrate through the fixed box and extend to the inside of the third mounting groove, one side, close to each other, of the two clamping blocks is fixedly connected with two symmetrically arranged second tension springs, the inner walls of the two sides of the second mounting groove are fixedly, the clamping groove is matched with the clamping block.
The third clamping component further comprises two first connecting plates which are rotatably connected to one side of the connecting block and are symmetrically arranged, two first connecting plates are rotatably connected to one ends, away from each other, of the first connecting plates, second push plates are rotatably connected to the two sides of the second push plates respectively and slidably connected with the inner walls of the two sides of the first mounting groove, and two fifth extension springs are fixedly connected to one ends, away from each other, of the second push plates and fixedly connected with the inner walls of the top and the bottom of the first mounting groove respectively.
The control component comprises two springs which are respectively and fixedly connected with the top inner wall and the bottom inner wall of the first mounting groove, one ends of the two springs which are close to each other are respectively and fixedly connected with a control panel, the top inner wall and the bottom inner wall of the third mounting groove are both provided with second insertion holes which are communicated with the first mounting groove, one sides of the two control plates which are close to each other are respectively penetrated through the two second insertion holes, one side of the first push plate and one side of the second push plate are both fixedly connected with a second fixing column, one side of the control plate is fixedly connected with two third fixing columns which are symmetrically arranged, the inner walls of two sides of the first mounting groove are rotationally connected with four second rotating shafts which are symmetrical in pairs, the outer walls of the second rotating shafts are fixedly connected with second connecting plates, two second through holes symmetrically arranged are formed in the second connecting plate, and the second fixing column and the third fixing column penetrate through the second through holes.
The rotor arm comprises a rotor arm body and is characterized in that two supporting frames are symmetrically arranged at the top and the bottom of the rotor arm body, grooves are formed in the supporting frames, and the grooves are matched with pull plates.
The slide rail is fixedly connected to the inner wall of one side of the second mounting groove, a slide block matched with the slide rail is fixedly connected to one side of the transverse plate, and the slide block is connected with the slide rail in a sliding mode.
A first through hole is formed in one end of the L-shaped plate, a first fixing column is fixedly connected to one side of the pull rod, and the first fixing column penetrates through the first through hole.
The use method of the rotor arm quick dismounting mechanism of the hybrid wing unmanned aerial vehicle comprises the following steps:
s1, mounting a rotor arm body, vertically pulling two pulling plates by hands to enable the two pulling plates to be away from each other, driving two pulling rods to be away from each other by the two pulling plates, driving two transverse plates to be away from each other by the two pulling rods, stretching a first tension spring by the two transverse plates, driving a first fixing column to rotate by the pulling rods, driving an L plate to rotate by the first fixing column, stopping pulling until the pulling plates are higher than the support frames, and rotating the pulling plates to enable two ends of each pulling plate to be respectively clamped with grooves in the tops of the two support frames;
s2, inserting the rotor arm body into a third mounting groove until the fixing box extends into the clamping groove, pulling the two pull plates in the direction away from each other, rotating the pull plates, enabling the two transverse plates to approach each other under the action of the elastic force of the first tension spring, enabling the transverse plates to drive the two pull rods to approach each other, enabling the pull rods to drive the first fixing columns to rotate, and enabling the first fixing columns to drive the L plate to rotate;
s3, the clamping of rotor arm body and mount pad specifically includes the following steps:
s31, enabling one ends, close to a third mounting groove, of two L boards to be far away from each other, inserting the L boards into a second insertion hole and pushing the two control boards to be far away from each other, enabling the control boards to extrude springs and drive two third fixing columns to rotate, enabling the third fixing columns to drive a second connecting plate to rotate, enabling the second connecting plate to drive a second fixing column to rotate, further enabling the second fixing column to drive two first push plates and two second push plates to be close to each other, respectively stretching a fourth tension spring and a fifth tension spring, and enabling the first push plates to be clamped with the first insertion hole;
s32, enabling the two second push plates to approach each other and drive the first connecting plate to rotate, enabling the first connecting plate to drive the connecting block to move transversely in the direction close to the rotor arm body, enabling the connecting block to push the connecting rod to move transversely in the direction close to the rotor arm body and stretch the third tension spring, enabling the connecting rod to push the semicircular plate to move transversely in the direction close to the rotor arm body, enabling the semicircular plate to drive the two clamping blocks to move away from each other, and enabling the two clamping blocks to be clamped with the clamping grooves respectively to achieve installation of the rotor arm body and the installation seat;
s4, when the rotor arm body needs to be disassembled, only two pulling plates need to be vertically pulled by hands to enable the two pulling plates to be away from each other, the two pulling plates drive the two pulling rods to be away from each other, the pulling rods drive the first fixing column to rotate, the first fixing column drives the L plate to rotate, the L plate is separated from the second insertion hole, at the moment, the two control plates are close to each other under the elastic force of the spring, the two first pushing plates and the two second pushing plates are also away from each other under the tensile force of the fourth tension spring and the fifth tension spring, the first pushing plates are released from the clamping state with the first insertion hole, the second pushing plates drive the first connecting plates to rotate, the connecting block moves towards the direction away from the rotor arm body under the tensile force of the third tension spring, the connecting block pulls the connecting rod to move towards the direction away from the rotor arm body, the connecting rod pulls the semi-circular plate to move transversely away from the rotor arm body, the clamping state with the clamping groove is removed, and the rotor arm body can be transversely pulled to be detached.
The invention has the following advantages:
1. in the invention; vertically pulling the two pulling plates by hands to enable the two pulling plates to be away from each other, driving the two pulling rods to be away from each other, driving the two transverse plates to be away from each other by the two pulling rods, stretching the first tension spring by the two transverse plates, driving the first fixing column to rotate by the pulling rods, driving the L plate to rotate by the first fixing column until the pulling plates are higher than the support frames, stopping pulling, and rotating the pulling plates to enable two ends of the pulling plates to be respectively clamped with the grooves in the tops of the two support frames;
2. in the invention; inserting the rotor wing arm body into the third mounting groove until the fixing box extends into the clamping groove, pulling the two pull plates in the direction away from each other, rotating the pull plates, enabling the two transverse plates to approach each other under the action of the elastic force of the first tension spring, enabling the transverse plates to drive the two pull rods to approach each other, enabling the pull rods to drive the first fixing columns to rotate, and enabling the first fixing columns to drive the L plate to rotate;
3. in the invention; the ends, close to the third mounting groove, of the two L plates are far away from each other, the L plates are inserted into the second insertion holes and push the two control plates to be far away from each other, the control plates extrude the springs and drive the two third fixing columns to rotate, the third fixing columns drive the second connecting plate to rotate, the second connecting plate drives the second fixing columns to rotate, the second fixing columns further drive the two first push plates and the two second push plates to be close to each other and respectively stretch the fourth tension spring and the fifth tension spring, and at the moment, the first push plates are clamped with the first insertion holes;
4. in the invention; the two second push plates are close to each other and drive the first connecting plate to rotate, the first connecting plate drives the connecting block to move transversely in the direction close to the rotor arm body, the connecting block pushes the connecting rod to move transversely in the direction close to the rotor arm body and stretches the third tension spring, the connecting rod pushes the semicircular plate to move transversely in the direction close to the rotor arm body, the semicircular plate drives the two clamping blocks to be away from each other, the two clamping blocks are clamped with the clamping grooves respectively, and the rotor arm body and the mounting seat are mounted;
5. in the invention; two pulling plates are vertically pulled by hands to be away from each other, the two pulling plates drive two pull rods to be away from each other, the pull rods drive a first fixed column to rotate, the first fixed column drives an L plate to rotate, the L plate is separated from a second insertion hole, at the moment, two control plates are close to each other under the elastic force of a spring, two first push plates and two second push plates are also far away from each other under the tensile force of a fourth tension spring and a fifth tension spring, the first push plates are released from the clamping state with the first insertion hole, the second push plates drive a first connecting plate to rotate, a connecting block moves towards the direction far away from a rotor arm body under the tensile force of a third tension spring, the connecting block pulls a connecting rod to move towards the direction far away from the rotor arm body, the connecting rod pulls a semi-circular plate to move towards the direction far away from the rotor arm body, the two clamping blocks are close to each other under the tensile force of the, the rotor arm body can be transversely pulled to detach the rotor arm body.
The invention has simple structure; through pulling two arm-tie to with its block in the recess, insert the rotor arm body in the third mounting groove, remove the braking of arm-tie again, and realize the installation of rotor arm body and mount pad through first block subassembly, second block subassembly and third block subassembly, only need with two arm-tie of vertical pulling of hand, make two arm-tie keep away from each other and can realize the dismantlement of rotor arm body, easy operation.
Drawings
FIG. 1 is a schematic top view of the present invention;
figure 2 is a front view of a rotor arm body and mounting base in accordance with the present invention;
figure 3 is a front cross-sectional structural view of a rotor arm body and mount of the present invention;
FIG. 4 is an enlarged view of portion A of FIG. 3;
figure 5 is a front cross-sectional structural view of a rotor arm body according to the present invention;
FIG. 6 is a front sectional view of the mounting base of the present invention;
FIG. 7 is an enlarged view of portion B of FIG. 6;
FIG. 8 is a three-dimensional view of the stand of the present invention.
In the figure; 1. an unmanned aerial vehicle; 2. a rotor arm body; 3. a mounting seat; 4. a first mounting groove; 5. pulling a plate; 6. a pull rod; 7. a support frame; 8. a first fixed column; 9. a transverse plate; 10. a slider; 11. a slide rail; 12. a first tension spring; 13. a second mounting groove; 14. a groove; 15. a first through hole; 16. an L plate; 17. a first rotating shaft; 18. a first push plate; 19. a control panel; 20. a second push plate; 21. a card slot; 22. a clamping block; 23. a fixing plate; 24. a second tension spring; 25. a semicircular plate; 26. a fixed box; 27. a connecting rod; 28. connecting blocks; 29. a first connecting plate; 30. a third tension spring; 31. a first insertion hole; 32. a second insertion hole; 33. a second fixed column; 34. a fourth tension spring; 35. a second through hole; 36. a second rotating shaft; 37. a second connecting plate; 38. a third fixing column; 39. a spring; 40. a third mounting groove; 41. and a fifth tension spring.
Detailed Description
The invention is further described below with reference to the accompanying drawings; the scope of protection of the invention is not limited to the following:
the first embodiment is as follows: as shown in fig. 1-8; a rotor arm quick dismounting mechanism of a hybrid wing unmanned aerial vehicle comprises an unmanned aerial vehicle 1, four mounting seats 3 are arranged at the top of the unmanned aerial vehicle 1, rotor arm bodies 2 are arranged on two sides of each mounting seat 3, a second mounting groove 13 is formed in each rotor arm body 2, two transverse plates 9 which are symmetrically arranged are connected to the inner wall of one side of each second mounting groove 13 in a sliding manner, the same first tension spring 12 is fixedly connected to the side, close to each other, of each transverse plate 9, a first clamping component for clamping the rotor arm bodies 2 and the mounting seats 3 is arranged on the side, away from each other, of each transverse plate 9, third mounting grooves 40 and first mounting grooves 4 are formed in two sides of each mounting seat 3, second clamping components for clamping the rotor arm bodies 2 and the mounting seats 3 are arranged on the inner walls of the tops and the bottoms of the first mounting grooves 4, a third clamping component for clamping the rotor arm bodies 2 and the mounting seats 3 is arranged on the inner wall of one side of each, the top inner wall and the bottom inner wall of the first mounting groove 4 are provided with control components for controlling the second clamping component and the third clamping component
According to the invention, the first clamping component comprises two pull rods 6 fixedly connected to the sides, away from each other, of the two transverse plates 9 respectively, one ends, away from each other, of the two pull rods 6 penetrate through the second installation groove 13 and are rotatably connected with the pull plate 5, the inner walls of the two sides of the second installation groove 13 are rotatably connected with two first rotating shafts 17 which are symmetrically arranged, the outer wall of each first rotating shaft 17 is fixedly connected with an L plate 16, one end of each L plate 16 is rotatably connected with one side of each pull rod 6, and the top and the bottom of the rotor arm body 2 are provided with first insertion holes 31.
In the invention, the second clamping component comprises fourth tension springs 34 respectively fixedly connected to the top inner wall and the bottom inner wall of the first mounting groove 4, one side of each of the two adjacent fourth tension springs 34 is fixedly connected with a first push plate 18, the first push plate 18 penetrates through the first mounting groove 4 and extends into the third mounting groove 40, and the first push plate 18 is matched with the first insertion hole 31.
In the invention, the third clamping component comprises a third tension spring 30 fixedly connected to the inner wall of one side of the first mounting groove 4, one end of the third tension spring 30 is fixedly connected with a connecting block 28, one side of the connecting block 28 is fixedly connected with a connecting rod 27, the inner wall of one side of the third mounting groove 40 is fixedly connected with a fixed box 26, one end of the connecting rod 27 penetrates through the first mounting groove 4 and extends to the inside of the fixed box 26, one end of the connecting rod 27 is fixedly connected with a semicircular plate 25, the inner walls of the two sides of the fixed box 26 are slidably connected with two symmetrically arranged clamping blocks 22, the ends of the two clamping blocks 22 far away from each other penetrate through the fixed box 26 and extend to the inside of the third mounting groove 40, one side of the two clamping blocks 22 close to each other is fixedly connected with two symmetrically arranged second tension springs 24, the inner walls of the two sides of the second mounting, the clamping groove 21 is matched with the clamping block 22.
In the invention, the third clamping component further comprises two symmetrically arranged first connecting plates 29 rotatably connected to one side of the connecting block 28, the ends, far away from each other, of the two first connecting plates 29 are rotatably connected with the second push plate 20, the two sides of the second push plate 20 are respectively connected with the inner walls, far away from each other, of the two first push plates 20 in a sliding manner, the ends, far away from each other, of the two second push plates 20 are respectively and fixedly connected with a fifth tension spring 41, and the ends, far away from each other, of the two fifth tension springs 41 are respectively and fixedly connected with the inner walls, at the top and at the bottom.
In the invention, the control assembly comprises two springs 39 fixedly connected with the top inner wall and the bottom inner wall of a first mounting groove 4 respectively, one ends of the two springs 39 close to each other are fixedly connected with a control plate 19, the top inner wall and the bottom inner wall of a third mounting groove 40 are respectively provided with a second inserting hole 32, the second inserting hole 32 is communicated with the first mounting groove 4, one sides of the two control plates 19 close to each other are respectively penetrated through the two second inserting holes 32, one sides of a first push plate 18 and a second push plate 20 are respectively fixedly connected with a second fixing column 33, one side of the control plate 19 is fixedly connected with two third fixing columns 38 which are symmetrically arranged, the two inner walls at two sides of the first mounting groove 4 are rotatably connected with four second rotating shafts 36 which are symmetric in pairs, the outer wall of the second rotating shaft 36 is fixedly connected with a second connecting plate 37, and the inside of the second, the second fixing column 33 and the third fixing column 38 both penetrate through the second through hole 35.
According to the invention, the top and the bottom of the rotor wing arm body 2 are both fixedly connected with two symmetrically arranged support frames 7, a groove 14 is formed in each support frame 7, and the groove 14 is matched with the pull plate 5.
In the invention, the inner wall of one side of the second mounting groove 13 is fixedly connected with a slide rail 11, one side of the transverse plate 9 is fixedly connected with a slide block 10 matched with the slide rail 11, and the slide block 10 is connected with the slide rail 11 in a sliding manner.
In the invention, one end of the L plate 16 is provided with a first through hole 15, one side of the pull rod 6 is fixedly connected with a first fixing column 8, and the first fixing column 8 penetrates through the first through hole 15.
A use method of a rotor arm quick dismounting mechanism of a hybrid wing unmanned aerial vehicle comprises the following steps:
s1, mounting the rotor arm body 2, vertically pulling two pulling plates 5 by hands to enable the two pulling plates 5 to be away from each other, driving the two pulling plates 6 to be away from each other by the two pulling plates 5, driving the two transverse plates 9 to be away from each other by the two pulling rods 6, stretching a first tension spring 12 by the two transverse plates 9, driving a first fixing column 8 to rotate by the pulling rod 6, driving an L plate 16 to rotate by the first fixing column 8, stopping pulling until the pulling plates 5 are higher than the supporting frames 7, and rotating the pulling plates 5 to enable two ends of the pulling plates 5 to be respectively clamped with grooves 14 in the tops of the two supporting frames 7;
s2, inserting the rotor arm body 2 into the third mounting groove 40 until the fixing box 26 extends into the clamping groove 21, pulling the two pull plates 5 in the direction away from each other, rotating the pull plates 5, enabling the two transverse plates 9 to approach each other under the action of the elastic force of the first tension spring 12, enabling the transverse plates 9 to drive the two pull rods 6 to approach each other, enabling the pull rods 6 to drive the first fixing column 8 to rotate, and enabling the first fixing column 8 to drive the L plate 16 to rotate;
s3, the clamping of the rotor arm body 2 and the mounting base 3 specifically comprises the following steps:
s31, the ends of the two L plates 16 close to the third mounting groove 40 are far away from each other, the L plates 16 are inserted into the second insertion holes 32 and push the two control plates 19 to be far away from each other, the control plates 19 extrude the springs 39 and drive the two third fixing posts 38 to rotate, the third fixing posts 38 drive the second connecting plate 37 to rotate, the second connecting plate 37 drives the second fixing posts 33 to rotate, the second fixing posts 33 drive the two first push plates 18 and the two second push plates 20 to be close to each other and respectively stretch the fourth tension spring 34 and the fifth tension spring 41, and at this time, the first push plates 18 are clamped with the first insertion holes 31;
s32, the two second push plates 20 approach each other and drive the first connecting plate 29 to rotate, the first connecting plate 29 drives the connecting block 28 to move transversely in the direction close to the rotor arm body 2, the connecting block 28 pushes the connecting rod 27 to move transversely in the direction close to the rotor arm body 2 and stretches the third tension spring 30, the connecting rod 27 pushes the semicircular plate 25 to move transversely in the direction close to the rotor arm body 2, the semicircular plate 25 drives the two clamping blocks 22 to move away from each other, the two clamping blocks 22 are respectively clamped with the clamping grooves 21, and the rotor arm body 2 and the mounting base 3 are mounted;
s4, when the rotor arm body 2 needs to be disassembled, only two pulling plates 5 need to be pulled vertically by hands to enable the two pulling plates 5 to be away from each other, the two pulling plates 5 drive the two pulling rods 6 to be away from each other, the pulling rod 6 drives the first fixing column 8 to rotate, the first fixing column 8 drives the L plate 16 to rotate, the L plate 16 is separated from the second inserting hole 32, at the moment, the two control plates 19 are close to each other under the elastic force of the spring 39, the two first pushing plates 18 and the two second pushing plates 20 are also far away from each other under the tensile force of the fourth tension spring 34 and the fifth tension spring 41, the first pushing plates 18 are released from the clamping state with the first inserting hole 31, the second pushing plates 20 drive the first connecting plate 29 to rotate, the connecting block 28 moves in the direction far away from the rotor arm body 2 under the tensile force of the third tension spring 30, the connecting block 28 pulls the connecting rod 27 to move in the direction far away from the rotor arm body 2, the connecting, two fixture blocks 22 are close to each other under the tensile force effect of second extension spring 24, remove the block state with draw-in groove 21, and rotor arm body 2's dismantlement can be realized to horizontal pulling rotor arm body 2 this moment.
The working principle is as follows: the rotor arm body 2 is installed, two pull plates 5 are vertically pulled by hands to enable the two pull plates 5 to be away from each other, the two pull plates 5 drive two pull rods 6 to be away from each other, the two pull rods 6 drive two transverse plates 9 to be away from each other, the two transverse plates 9 stretch a first tension spring 12, the pull rods 6 drive a first fixing column 8 to rotate, the first fixing column 8 drives an L plate 16 to rotate until the pull plates 5 are higher than a support frame 7, the pulling is stopped, the pull plates 5 are rotated to enable two ends of the pull plates 5 to be respectively clamped with grooves 14 at the tops of the two support frames 7, the rotor arm body 2 is inserted into a third installation groove 40 until a fixing box 26 extends into a clamping groove 21, the two pull plates 5 are pulled in the direction away from each other, the pull plates 5 are rotated, the two transverse plates 9 are close to each other under the elastic force of the first tension spring 12, the transverse plates 9 drive the two pull rods 6 to be close, the first fixing post 8 drives the L-shaped plate 16 to rotate, the rotor arm body 2 is clamped with the mounting seat 3, one ends of the two L-shaped plates 16 close to the third mounting groove 40 are far away from each other, the L-shaped plates 16 are inserted into the second insertion holes 32 and push the two control plates 19 away from each other, the control plates 19 press the springs 39 and drive the two third fixing posts 38 to rotate, the third fixing posts 38 drive the second connecting plates 37 to rotate, the second connecting plates 37 drive the second fixing posts 33 to rotate, the second fixing posts 33 drive the two first push plates 18 and the two second push plates 20 to approach each other and respectively stretch the fourth tension spring 34 and the fifth tension spring 41, at the moment, the first push plates 18 are clamped with the first insertion holes 31, the two second push plates 20 approach each other and drive the first connecting plate 29 to rotate, the first connecting plate 29 drives the connecting block 28 to move transversely in a direction close to the rotor arm body 2, the connecting block 28 drives the connecting rod 27 to move transversely in a direction, the connecting rod 27 pushes the semicircular plate 25 to move transversely in the direction close to the rotor arm body 2, the semicircular plate 25 drives the two clamping blocks 22 to move away from each other, the two clamping blocks 22 are respectively clamped with the clamping grooves 21, so that the installation of the rotor arm body 2 and the mounting seat 3 is realized, when the rotor arm body 2 needs to be disassembled, only two pulling plates 5 need to be vertically pulled by hands, so that the two pulling plates 5 are away from each other, the two pulling plates 5 drive the two pulling rods 6 to move away from each other, the pulling rod 6 drives the first fixing column 8 to rotate, the first fixing column 8 drives the L plate 16 to rotate, the L plate 16 is separated from the second inserting hole 32, at the moment, the two control plates 19 are close to each other under the elastic force of the spring 39, the two first push plates 18 and the two second push plates 20 are also away from each other under the tensile force of the fourth tension spring 34 and the fifth tension spring 41, the first push plate 18 releases the clamping, connecting block 28 moves to the direction of keeping away from rotor arm body 2 under the tensile force effect of third extension spring 30, connecting block 28 pulling connecting rod 27 moves to the direction of keeping away from rotor arm body 2, connecting rod 27 pulling semicircle board 25 is to the direction lateral shifting of keeping away from rotor arm body 2, two fixture blocks 22 are close to each other under the tensile force effect of second extension spring 24, remove the block state with draw-in groove 21, the dismantlement of rotor arm body 2 can be realized to lateral pulling rotor arm body 2 this moment.
The foregoing are only preferred embodiments of the present invention; it is to be understood that the invention is not limited to the forms disclosed herein; should not be construed as excluding other embodiments; but is applicable to various other combinations, modifications, and environments; and are within the contemplation described herein; modifications may be made by the above teachings or by techniques or knowledge in the relevant art. And that modifications and variations may be effected by one skilled in the art without departing from the spirit and scope of the invention; it is intended to be within the scope of the appended claims.
Claims (10)
1. A rotor arm quick dismounting mechanism of a hybrid wing unmanned aerial vehicle; including unmanned aerial vehicle (1), its characterized in that: the top of the unmanned aerial vehicle (1) is provided with four mounting seats (3), two sides of each mounting seat (3) are provided with a rotor arm body (2), a second mounting groove (13) is formed in each rotor arm body (2), the inner wall of one side of each second mounting groove (13) is connected with two transverse plates (9) which are symmetrically arranged in a sliding manner, one side, close to each other, of each transverse plate (9) is fixedly connected with the same first tension spring (12), one side, far away from each other, of each transverse plate (9) is provided with a first clamping assembly used for clamping the rotor arm bodies (2) and the mounting seats (3), two sides of each mounting seat (3) are provided with a third mounting groove (40) and a first mounting groove (4), the inner wall of the top and the inner wall of the bottom of each first mounting groove (4) are provided with second clamping assemblies used for clamping the rotor arm bodies (2) and the mounting seats (3), the utility model discloses a rotor wing mounting structure, including first mounting groove (4), one side inner wall of first mounting groove (4) is provided with the third block subassembly that is used for making rotor wing arm body (2) and mount pad (3) block, the top inner wall and the bottom inner wall of first mounting groove (4) all are provided with the control assembly who is used for controlling second block subassembly and third block subassembly.
2. The hybrid wing drone rotor arm quick-disconnect mechanism of claim 1; the method is characterized in that: first block subassembly is including respectively fixed connection two pull rod (6) of one side of keeping away from each other of diaphragm (9), two the one end of keeping away from each other of pull rod (6) all runs through second mounting groove (13) and swivelling joint has arm-tie (5), the both sides inner wall swivelling joint of second mounting groove (13) has two first pivots (17) that the symmetry set up, the outer wall fixedly connected with L board (16) of first pivot (17), the one end of L board (16) is rotated with one side of pull rod (6) and is connected, first patchhole (31) have all been seted up to the top and the bottom of rotor arm body (2).
3. The hybrid wing drone rotor arm quick-disconnect mechanism of claim 1; the method is characterized in that: the second block subassembly is including fourth extension spring (34), two of difference fixed connection at the top inner wall of first mounting groove (4) and bottom inner wall the equal first push pedal (18) of fixedly connected with in one side that fourth extension spring (34) are close to each other, inside first push pedal (18) run through first mounting groove (4) and extend to third mounting groove (40), first push pedal (18) and first patchhole (31) looks adaptation.
4. The hybrid wing drone rotor arm quick-disconnect mechanism of claim 1; the method is characterized in that: the third clamping component comprises a third tension spring (30) fixedly connected to the inner wall of one side of the first mounting groove (4), one end of the third tension spring (30) is fixedly connected with a connecting block (28), one side of the connecting block (28) is fixedly connected with a connecting rod (27), one inner wall of one side of the third mounting groove (40) is fixedly connected with a fixed box (26), one end of the connecting rod (27) penetrates through the first mounting groove (4) and extends into the fixed box (26), one end of the connecting rod (27) is fixedly connected with a semicircular plate (25), two inner walls of two sides of the fixed box (26) are slidably connected with two symmetrically arranged clamping blocks (22), one end, far away from each other, of each clamping block (22) penetrates through the fixed box (26) and extends into the third mounting groove (40), and one side, close to each other, of each clamping block (22) is fixedly connected with two symmetrically arranged second tension springs (24), the utility model discloses a mounting structure, including second mounting groove (13), the same fixed plate (23) of both sides inner wall fixedly connected with of second mounting groove (13), draw-in groove (21) have been seted up to fixed plate (23) one end that is close to mount pad (3), draw-in groove (21) and fixture block (22) looks adaptation.
5. The hybrid wing drone rotor arm quick-disconnect mechanism of claim 1; the method is characterized in that: the third joint subassembly is still including rotating two first connecting plate (29) of connection setting in the symmetry of connecting block (28) one side, two one end that first connecting plate (29) kept away from each other all rotates and is connected with second push pedal (20), the both sides of second push pedal (20) respectively with the both sides inner wall sliding connection of first mounting groove (4), two the equal fixedly connected with fifth extension spring (41) of one end that second push pedal (20) kept away from each other, two the one end that fifth extension spring (41) kept away from each other respectively with the top inner wall and the bottom inner wall fixed connection of first mounting groove (4).
6. The hybrid wing drone rotor arm quick-disconnect mechanism of claim 5; the method is characterized in that: the control assembly comprises two springs (39) fixedly connected to the top inner wall and the bottom inner wall of a first mounting groove (4) respectively, one ends, close to each other, of the two springs (39) are fixedly connected with a control panel (19), the top inner wall and the bottom inner wall of a third mounting groove (40) are respectively provided with a second insertion hole (32), the second insertion holes (32) are communicated with the first mounting groove (4), one sides, close to each other, of the two control panels (19) respectively penetrate through the two second insertion holes (32), one sides of a first push plate (18) and a second push plate (20) are respectively and fixedly connected with a second fixing column (33), one side of the control panel (19) is fixedly connected with two third fixing columns (38) which are symmetrically arranged, and two second rotating shafts (36) which are symmetrically arranged are rotatably connected to the inner walls on the two sides of the first mounting groove (4, the outer wall fixedly connected with second connecting plate (37) of second pivot (36), two second through-holes (35) that the symmetry set up are seted up to the inside of second connecting plate (37), second fixed column (33) all run through second through-hole (35) with third fixed column (38).
7. The hybrid wing drone rotor arm quick-disconnect mechanism of claim 1; the method is characterized in that: the rotor arm is characterized in that two support frames (7) symmetrically arranged are fixedly connected to the top and the bottom of the rotor arm body (2), a groove (14) is formed in each support frame (7), and the groove (14) is matched with the pull plate (5).
8. The hybrid wing drone rotor arm quick-disconnect mechanism of claim 1; the method is characterized in that: one side inner wall fixedly connected with slide rail (11) of second mounting groove (13), one side fixedly connected with of diaphragm (9) and slide rail (11) looks adaptation slider (10), slider (10) and slide rail (11) sliding connection.
9. The hybrid wing drone rotor arm quick-disconnect mechanism of claim 2; the method is characterized in that: first through-hole (15) have been seted up to the one end of L board (16), one side fixedly connected with first fixed column (8) of pull rod (6), first fixed column (8) run through first through-hole (15).
10. Use of the mechanism for quick disassembly and assembly of a rotor arm of a hybrid wing drone according to any one of claims 1 to 9, characterised in that: it comprises the following steps:
s1, mounting a rotor wing arm body (2), vertically pulling two pull plates (5) by hands to enable the two pull plates (5) to be away from each other, driving two pull rods (6) to be away from each other by the two pull plates (5), driving two transverse plates (9) to be away from each other by the two pull rods (6), stretching a first tension spring (12) by the two transverse plates (9), driving a first fixed column (8) to rotate by the pull rods (6), driving an L plate (16) to rotate by the first fixed column (8), stopping pulling until the pull plates (5) are higher than support frames (7), rotating the pull plates (5), and enabling two ends of each pull plate (5) to be clamped with grooves (14) in the tops of the two support frames (7) respectively;
s2, inserting the rotor arm body (2) into the third mounting groove (40) until the fixing box (26) extends into the clamping groove (21), pulling the two pull plates (5) in the direction away from each other, rotating the pull plates (5), enabling the two transverse plates (9) to approach each other under the action of the elastic force of the first tension spring (12), enabling the transverse plates (9) to drive the two pull rods (6) to approach each other, enabling the pull rods (6) to drive the first fixing column (8) to rotate, and enabling the first fixing column (8) to drive the L plate (16) to rotate;
s3, the clamping of the rotor arm body (2) and the mounting seat (3), and the method specifically comprises the following steps:
s31, one ends, close to a third mounting groove (40), of two L boards (16) are far away from each other, the L boards (16) are inserted into a second insertion hole (32) and push two control boards (19) to be far away from each other, the control boards (19) extrude springs (39) and drive two third fixing columns (38) to rotate, the third fixing columns (38) drive a second connecting board (37) to rotate, the second connecting board (37) drive a second fixing column (33) to rotate, then the second fixing column (33) drive two first push plates (18) and two second push plates (20) to be close to each other and respectively stretch a fourth tension spring (34) and a fifth tension spring (41), and at the moment, the first push plates (18) are clamped with the first insertion hole (31);
s32, the two second push plates (20) are close to each other and drive the first connecting plate (29) to rotate, the first connecting plate (29) drives the connecting block (28) to transversely move towards the direction close to the rotor arm body (2), the connecting block (28) pushes the connecting rod (27) to transversely move towards the direction close to the rotor arm body (2) and stretches the third tension spring (30), the connecting rod (27) pushes the semicircular plate (25) to transversely move towards the direction close to the rotor arm body (2), the semicircular plate (25) drives the two clamping blocks (22) to be away from each other, the two clamping blocks (22) are clamped with the clamping grooves (21) respectively, and the installation of the rotor arm body (2) and the installation seat (3) is realized;
s4, when the rotor arm body (2) needs to be disassembled, only two pulling plates (5) need to be pulled vertically by hands to enable the two pulling plates (5) to be far away from each other, the two pulling plates (5) drive two pull rods (6) to be far away from each other, the pull rods (6) drive first fixing columns (8) to rotate, the first fixing columns (8) drive L plates (16) to rotate, the L plates (16) are separated from second insertion holes (32), at the moment, the two control plates (19) are close to each other under the elastic force action of springs (39), the two first pushing plates (18) and the two second pushing plates (20) are also far away from each other under the tensile force action of a fourth tension spring (34) and a fifth tension spring (41), the first pushing plates (18) are released from the clamping state with the first insertion holes (31), the second pushing plates (20) drive first connecting plates (29) to rotate, and the connecting blocks (28) move in the direction far away from the rotor arm body (2) under the tensile force action of a third tension spring (30), connecting block (28) pulling connecting rod (27) remove to the direction of keeping away from rotor arm body (2), and connecting rod (27) pulling semicircle board (25) are to the direction lateral shifting of keeping away from rotor arm body (2), and two fixture blocks (22) are close to each other under the pulling force effect of second extension spring (24), remove the block state with draw-in groove (21), and the dismantlement of rotor arm body (2) can be realized to horizontal pulling rotor arm body (2) this moment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011231609.1A CN112298546B (en) | 2020-11-06 | 2020-11-06 | Rotor arm quick dismounting mechanism of hybrid wing unmanned aerial vehicle and use method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011231609.1A CN112298546B (en) | 2020-11-06 | 2020-11-06 | Rotor arm quick dismounting mechanism of hybrid wing unmanned aerial vehicle and use method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112298546A true CN112298546A (en) | 2021-02-02 |
| CN112298546B CN112298546B (en) | 2022-02-15 |
Family
ID=74325218
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011231609.1A Active CN112298546B (en) | 2020-11-06 | 2020-11-06 | Rotor arm quick dismounting mechanism of hybrid wing unmanned aerial vehicle and use method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112298546B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115970361A (en) * | 2022-04-06 | 2023-04-18 | 江苏瀚林滤材有限公司 | Belt filter cloth prevents pothook and lets out vacuum apparatus |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170015403A1 (en) * | 2015-07-15 | 2017-01-19 | Zerotech (Shenzhen) Intelligence Robot Co., Ltd | Unmanned aerial vehicle arm adjustment device and unmanned aerial vehicle |
| CN109204800A (en) * | 2018-10-19 | 2019-01-15 | 中卫航空科技发展有限公司 | A kind of foldable quadrotor individual soldier unmanned plane |
| CN109353507A (en) * | 2018-10-17 | 2019-02-19 | 中卫航空科技发展有限公司 | A kind of portable multi-function individual combat unmanned plane |
| CN109795680A (en) * | 2019-03-13 | 2019-05-24 | 南京晓庄学院 | A kind of rotor wing unmanned aerial vehicle that can specify horn breaking point and its control method |
| CN210761308U (en) * | 2019-09-03 | 2020-06-16 | 镇江市勘察测绘研究院 | Multi-rotor unmanned aerial vehicle |
| CN211391682U (en) * | 2019-12-31 | 2020-09-01 | 广州朱雀智能科技有限公司 | Unmanned aerial vehicle wing connection structure |
-
2020
- 2020-11-06 CN CN202011231609.1A patent/CN112298546B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20170015403A1 (en) * | 2015-07-15 | 2017-01-19 | Zerotech (Shenzhen) Intelligence Robot Co., Ltd | Unmanned aerial vehicle arm adjustment device and unmanned aerial vehicle |
| CN109353507A (en) * | 2018-10-17 | 2019-02-19 | 中卫航空科技发展有限公司 | A kind of portable multi-function individual combat unmanned plane |
| CN109204800A (en) * | 2018-10-19 | 2019-01-15 | 中卫航空科技发展有限公司 | A kind of foldable quadrotor individual soldier unmanned plane |
| CN109795680A (en) * | 2019-03-13 | 2019-05-24 | 南京晓庄学院 | A kind of rotor wing unmanned aerial vehicle that can specify horn breaking point and its control method |
| CN210761308U (en) * | 2019-09-03 | 2020-06-16 | 镇江市勘察测绘研究院 | Multi-rotor unmanned aerial vehicle |
| CN211391682U (en) * | 2019-12-31 | 2020-09-01 | 广州朱雀智能科技有限公司 | Unmanned aerial vehicle wing connection structure |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115970361A (en) * | 2022-04-06 | 2023-04-18 | 江苏瀚林滤材有限公司 | Belt filter cloth prevents pothook and lets out vacuum apparatus |
Also Published As
| Publication number | Publication date |
|---|---|
| CN112298546B (en) | 2022-02-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112298546B (en) | Rotor arm quick dismounting mechanism of hybrid wing unmanned aerial vehicle and use method thereof | |
| CN112722312B (en) | Emergency rescue vehicle and emergency rescue method for airplane substitute wheel | |
| CN216659710U (en) | A fixed equipment that is used for emergent unmanned aerial vehicle in removing command car | |
| CN102779438A (en) | Flight simulated mechanical execution system simulating full-motion of airplane | |
| CN110615114A (en) | Method and device for assisting landing and landing of airplane | |
| KR101789167B1 (en) | Automatic take-0ff equipment for airplane | |
| CN113992899A (en) | Unmanned aerial vehicle passes back image composite graph equipment in real time | |
| CN110203412A (en) | A kind of prior-warning device of individual combat unmanned plane | |
| CN112278240B (en) | Small-sized fixed wing unmanned aerial vehicle empennage quick dismounting mechanism and using method thereof | |
| CN113386965B (en) | Unmanned aerial vehicle grabs thing device | |
| CN202666406U (en) | Six-arm model airplane spiral rack | |
| CN215475797U (en) | Unmanned aerial vehicle that takes photo by plane of many cameras | |
| CN214524445U (en) | Air cylinder buffer device of unmanned airport | |
| CN221341088U (en) | Unmanned aerial vehicle with camera | |
| CN209321225U (en) | A kind of modularization being dismounted for multiple times teaching unmanned plane | |
| CN220996802U (en) | Three-blade folding paddle clamp of unmanned aerial vehicle | |
| CN216401794U (en) | Unmanned aerial vehicle with unmanned aerial vehicle camera positioner | |
| CN113335543B (en) | On-line monitoring power station equipment based on unmanned aerial vehicle in flight | |
| CN111422370A (en) | Unmanned aerial vehicle ejection rack single machine, parallel track ejection rack and launching method thereof | |
| CN220577530U (en) | Quick detach formula undercarriage and unmanned aerial vehicle for unmanned aerial vehicle | |
| CN218858723U (en) | Survey and drawing camera mounting structure for unmanned aerial vehicle | |
| CN214930703U (en) | Fixed wing unmanned aerial vehicle for forest patrol convenient to extend and combine | |
| CN116692075A (en) | Unmanned aerial vehicle equipment for collaborative inspection | |
| CN218949526U (en) | Unmanned aerial vehicle is patrolled and examined to electric power | |
| CN210852886U (en) | Folding piece of folding usefulness of unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |