CN218662395U - Aircraft capable of rotating by 360 degrees - Google Patents
Aircraft capable of rotating by 360 degrees Download PDFInfo
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- CN218662395U CN218662395U CN202223319929.XU CN202223319929U CN218662395U CN 218662395 U CN218662395 U CN 218662395U CN 202223319929 U CN202223319929 U CN 202223319929U CN 218662395 U CN218662395 U CN 218662395U
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- camera
- aircraft
- aircraft body
- plate
- fixedly connected
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model belongs to the technical field of aircrafts, in particular to an aircraft capable of rotating 360 degrees, which comprises an aircraft body; the top end surface of the aircraft body is uniformly and fixedly connected with connecting arms, one ends of the connecting arms, far away from the aircraft body, are fixedly provided with rotors, and the top end surface of the aircraft body is provided with a camera; through laying the camera on the aircraft body, and let the aircraft body be located between a set of fixed plate, then the slide that upwards slides, make the gag lever post roll-off in the draw-in groove, then clockwise rotation pivot, make the connecting wire winding in the pivot, the connecting wire can stimulate the disc this moment, thereby make the disc drive the slide bar and remove, the slide bar can promote the clamp splice to carry out the centre gripping to the camera this moment, thereby fix the camera on the aircraft body, then promote the slide, make gag lever post and circular slot joint, the connecting wire can be in the state of straightening this moment and avoid the slide bar to appear removing.
Description
Technical Field
The utility model relates to an aircraft technical field specifically is a can 360 rotatory aircraft.
Background
The aircraft is an apparatus flying in the air, and the types of the aircraft are various, wherein one aircraft can be provided with a camera, and the effect of high-altitude shooting is achieved by flying in the air through the aircraft.
The existing aircraft can realize 360-degree rotary flight through the rotor wing, and the camera is installed on the aircraft through the screw, so that when the camera is detached from and installed on the aircraft, the camera can be detached from and installed on the aircraft only by means of the screwdriver, and when people forget to carry the screwdriver, the camera cannot be firmly fixed on the aircraft, so that the aircraft capable of rotating 360 degrees is provided aiming at the problems.
SUMMERY OF THE UTILITY MODEL
In order to compensate prior art's not enough, solve because the camera is through the screw mounting on the aircraft, consequently when dismantling and installing the camera from the aircraft, need just can dismantle the camera from the aircraft with the help of the screwdriver and install, forget when the people and carry the screwdriver on, can lead to the unable problem of fixing on the aircraft that is firm with the camera, the utility model provides a can 360 rotatory aircraft.
The utility model provides a technical scheme that its technical problem adopted is: the utility model relates to an aircraft capable of rotating 360 degrees, which comprises an aircraft body; the top end face of the aircraft body is uniformly and fixedly connected with a connecting arm, one end of the connecting arm, far away from the aircraft body, is fixedly provided with a rotor wing, the top end face of the aircraft body is provided with a camera, the top end face of the aircraft body is fixedly connected with a group of fixed plates, the fixed plates are internally and slidably connected with slide bars, one ends, close to the camera, of the slide bars are fixedly connected with U-shaped clamping blocks, the surfaces of the fixed plates are fixedly connected with discs, the side walls of the discs are fixedly connected with connecting wires, one ends, far away from the discs, of the connecting wires are fixedly provided with rotating shafts, the bottom ends of the rotating shafts are rotatably connected with the inside of the fixed plates, the surfaces of the rotating shafts are slidably connected with sliding plates, the bottom ends of the sliding plates are fixedly connected with limiting rods, the top ends of the fixed plates are provided with a plurality of groups of clamping grooves, and the limiting rods are clamped with the inner walls of the clamping grooves, through laying the camera on the aircraft body, and let the aircraft body be located between a set of fixed plate, then upwards slide the slide, make the gag lever post roll-off from the draw-in groove in, then the clockwise rotation pivot, make the connecting wire winding in the pivot, the connecting wire can stimulate the disc this moment, thereby make the disc drive the slide bar and remove, the slide bar can promote the clamp splice to carry out the centre gripping to the camera this moment, thereby fix the camera on the aircraft body, then promote the slide, make gag lever post and circular slot joint, the connecting wire can be in the state of straightening at this moment and avoid the slide bar to appear removing, when needs take away the camera from the aircraft body away, the pulling slide, make the gag lever post roll-off from the draw-in groove in, later reverse pivot, make the connecting wire loosen from the pivot, then directly take away the camera from the aircraft body.
Preferably, the fixed surface of pivot is connected with the connecting plate, the top fixedly connected with elasticity rope of connecting plate, the one end and the slide fixed connection of connecting plate are kept away from to the elasticity rope, and through the power of pulling the slide with the help of elasticity rope, the condition that the gag lever post drops in from the draw-in groove can be avoided appearing, and when the aircraft body carries out the rotation of more wide-angle, the slide can incline downwards to lead to the slide to slide because of the reason of gravity, make the gag lever post drop from in the draw-in groove.
Preferably, one side fixed mounting that the disc is close to the fixed plate has the spring, the one end and the fixed plate fixed connection of disc are kept away from to the spring, loosen the back from the pivot as the connecting wire, and the spring can promote the disc to make the disc drive the slide bar and remove, make the clamp splice no longer contact with the camera, played the effect of reseing to the clamp splice.
Preferably, both sides corresponding to the inner wall of the clamping block are provided with grooves, the inner wall of each groove is fixedly connected with a rectangular plate, a round rod is connected in the rectangular plate in a sliding mode, one end, far away from the grooves, of the round rod is fixedly connected with a first magnetic block, the inner wall of each groove is fixedly connected with a second magnetic block, the first magnetic block and the second magnetic block repel each other, when the camera is clamped by the clamping block, the force of the first magnetic block and the force of the second magnetic block repel each other can be used for enabling the first magnetic block to drive the round rod to slide in the rectangular plate, so that the first magnetic block clamps the camera, and further the aircraft body is fixed on the aircraft body.
Preferably, the one end fixedly connected with block rubber of round bar is kept away from to first magnetic path, the block rubber is the arc, when first magnetic path carries out the centre gripping to the camera, the block rubber can contact with the camera to make the block rubber increase with the frictional force of camera, and then reach the effect of further fixing the camera on the aircraft body.
Preferably, the top end face of the aircraft body is fixedly provided with a supporting plate, a sliding groove is formed in the surface of the supporting plate in a penetrating mode, a pressing plate is connected with an inner wall painting of the sliding groove, one side, far away from the camera, of the supporting plate is fixedly connected with a supporting block, a threaded rod is connected with the inner thread of the supporting block, the bottom end of the threaded rod is rotatably connected with the inner portion of the pressing plate, when the camera is fixed on the aircraft body through a clamping block, the threaded rod is rotated, the threaded rod drives the pressing plate to move downwards, the pressing plate can press the camera at the moment, the camera is further fixed on the aircraft body, when the camera needs to be taken away from the aircraft body, the threaded rod is rotated, the pressing plate does not press the camera any more, and then subsequent dismantling work is carried out on the camera.
The utility model discloses an useful part lies in:
1. through laying the camera on the aircraft body, and let the aircraft body be located between a set of fixed plate, then the slide that upwards slides, make the gag lever post roll-off in the draw-in groove, then clockwise rotation pivot, make the connecting wire winding in the pivot, the connecting wire can stimulate the disc this moment, thereby make the disc drive the slide bar and remove, the slide bar can promote the clamp splice to carry out the centre gripping to the camera this moment, thereby fix the camera on the aircraft body, then promote the slide, make gag lever post and circular slot joint, the connecting wire can be in the state of straightening this moment and avoid the slide bar to appear removing.
2. After the camera is clamped by the clamping block, the first magnetic block drives the round rod to slide in the rectangular plate by means of the repulsive force of the first magnetic block and the second magnetic block, so that the camera is clamped by the first magnetic block, and the aircraft body is further fixed on the aircraft body.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without inventive exercise.
FIG. 1 is a perspective view of an aircraft body;
FIG. 2 is a front view of the aircraft body;
FIG. 3 is a cross-sectional view of the fixation plate;
FIG. 4 is an enlarged view of FIG. 3 at A;
FIG. 5 is a cross-sectional view of the clamp block;
fig. 6 is an enlarged view of fig. 2 at B.
In the figure: 1. an aircraft body; 2. a connecting arm; 3. a rotor; 4. a camera; 5. a fixing plate; 6. a slide bar; 7. a clamping block; 8. a card slot; 9. a limiting rod; 10. a rotating shaft; 11. a slide plate; 12. an elastic cord; 13. a connecting plate; 14. a connecting wire; 15. a spring; 16. a disc; 18. a rubber block; 19. a first magnetic block; 20. a second magnetic block; 21. a rectangular plate; 22. a round bar; 23. a groove; 24. a support plate; 25. a chute; 26. pressing a plate; 27. a support block; 28. a threaded rod.
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 efforts belong to the protection scope of the present invention.
Referring to fig. 1-6, an aircraft capable of rotating 360 ° comprises an aircraft body 1; the top end face of the aircraft body 1 is uniformly and fixedly connected with a connecting arm 2, one end, far away from the aircraft body 1, of the connecting arm 2 is fixedly provided with a rotor 3, the top end face of the aircraft body 1 is provided with a camera 4, the top end face of the aircraft body 1 is fixedly connected with a set of fixing plate 5, a slide rod 6 is connected in the fixing plate 5 in a sliding manner, one end, close to the camera 4, of the slide rod 6 is fixedly connected with a U-shaped clamping block 7, the surface of the fixing plate 5 is fixedly connected with a disc 16, the side wall of the disc 16 is fixedly connected with a connecting wire 14, one end, far away from the disc 16, of the connecting wire 14 is fixedly provided with a rotating shaft 10, the bottom end of the rotating shaft 10 is rotatably connected with the inside of the fixing plate 5, the surface of the rotating shaft 10 is slidably connected with a sliding plate 11, the bottom end of the sliding plate 11 is fixedly connected with a limiting rod 9, the top end of the fixing plate 5 is provided with a plurality of clamping grooves 8, and the limiting rod 9 is clamped with the inner wall of the clamping grooves 8; in operation, through laying camera 4 on aircraft body 1, and let aircraft body 1 be located between a set of fixed plate 5, then upwards slide 11, make gag lever post 9 follow roll-off in draw-in groove 8, then clockwise rotation pivot 10, make connecting wire 14 twine on pivot 10, connecting wire 14 can stimulate disc 16 this moment, thereby make disc 16 drive slide bar 6 move, slide bar 6 can promote clamp splice 7 and carry out the centre gripping to camera 4 this moment, thereby fix camera 4 on aircraft body 1, then promote slide 11, make gag lever post 9 and circular slot joint, connecting wire 14 can be in the state of stretching straight this moment and avoid slide bar 6 to appear moving, when needing to take away camera 4 from aircraft body 1, stimulate slide 11, make gag lever post 9 follow roll-off in draw-in groove 8, later reverse pivot 10, make connecting wire 14 loosen from pivot 10, then directly take away camera 4 from aircraft body 1.
A connecting plate 13 is fixedly connected to the surface of the rotating shaft 10, an elastic rope 12 is fixedly connected to the top end of the connecting plate 13, and one end, far away from the connecting plate 13, of the elastic rope 12 is fixedly connected with the sliding plate 11; during operation, through the power of holding slide 11 with the help of elasticity rope 12, can avoid appearing the condition that gag lever post 9 drops from the draw-in groove 8 in, when aircraft body 1 carries out more wide-angle rotation, slide 11 probably slopes downwards to lead to slide 11 because of the reason of gravity, make gag lever post 9 drop from the draw-in groove 8 in.
A spring 15 is fixedly installed on one side, close to the fixed plate 5, of the disc 16, and one end, far away from the disc 16, of the spring 15 is fixedly connected with the fixed plate 5; in operation, when the connecting wire 14 is loosened from the rotating shaft 10, the spring 15 pushes the disc 16, so that the disc 16 drives the sliding rod 6 to move, and the clamping block 7 is not contacted with the camera 4 any more, thereby playing a role in resetting the clamping block 7.
Grooves 23 are formed in two corresponding sides of the inner wall of the clamping block 7, a rectangular plate 21 is fixedly connected to the inner wall of each groove 23, a round rod 22 is connected to the rectangular plate 21 in a sliding mode, a first magnetic block 19 is fixedly connected to one end, far away from the groove 23, of each round rod 22, and a second magnetic block 20, with the first magnetic blocks 19 repelling each other, is fixedly connected to the inner wall of each groove 23; during operation, after the camera 4 is clamped by the clamping block 7, the first magnetic block 19 drives the round rod 22 to slide in the rectangular plate 21 by means of the repulsive force of the first magnetic block 19 and the second magnetic block 20, so that the first magnetic block 19 clamps the camera 4, and the aircraft body 1 is further fixed on the aircraft body 1.
One end of the first magnetic block 19, which is far away from the round rod 22, is fixedly connected with a rubber block 18, and the rubber block 18 is arc-shaped; in operation, when the first magnetic block 19 clamps the camera 4, the rubber block 18 contacts with the camera 4, so that the rubber block 18 increases the friction force with the camera 4, and further the camera 4 is further fixed on the aircraft body 1.
A supporting plate 24 is fixedly installed on the top end face of the aircraft body 1, a sliding groove 25 is formed in the surface of the supporting plate 24 in a penetrating mode, a pressing plate 26 is connected to an inner mural of the sliding groove 25, a supporting block 27 is fixedly connected to one side, away from the camera 4, of the supporting plate 24, a threaded rod 28 is connected to the supporting block 27 in a threaded mode, and the bottom end of the threaded rod 28 is rotatably connected with the inside of the pressing plate 26; during operation, when camera 4 is fixed on aircraft body 1 by clamp splice 7, rotate threaded rod 28 for threaded rod 28 drives clamp plate 26 and moves down, and clamp plate 26 can push down camera 4 this moment, thereby makes camera 4 further fixed on aircraft body 1, when needs take away camera 4 from aircraft body 1, reverse threaded rod 28 for clamp plate 26 no longer pushes down camera 4, later is carrying out subsequent work of demolising to camera 4.
According to the working principle, when the camera 4 is fixed on the aircraft body 1 by the clamping block 7, the threaded rod 28 is rotated, the threaded rod 28 drives the pressing plate 26 to move downwards, at the moment, the pressing plate 26 presses the camera 4, so that the camera 4 is further fixed on the aircraft body 1, when the camera 4 needs to be taken away from the aircraft body 1, the threaded rod 28 is reversed, the pressing plate 26 does not press the camera 4 any more, and then the camera 4 is subjected to subsequent dismantling work; when the first magnetic block 19 clamps the camera 4, the rubber block 18 can contact with the camera 4, so that the friction force between the rubber block 18 and the camera 4 is increased, and the camera 4 is further fixed on the aircraft body 1; after the camera 4 is clamped by the clamping block 7, the first magnetic block 19 can drive the round rod 22 to slide in the rectangular plate 21 by means of the repulsive force of the first magnetic block 19 and the second magnetic block 20, so that the camera 4 is clamped by the first magnetic block 19, and the aircraft body 1 is further fixed on the aircraft body 1; when the connecting wire 14 is loosened from the rotating shaft 10, the spring 15 pushes the disc 16, so that the disc 16 drives the sliding rod 6 to move, the clamping block 7 is not contacted with the camera 4 any more, and the effect of resetting the clamping block 7 is achieved; the situation that the limiting rod 9 falls off from the clamping groove 8 can be avoided by the force of pulling the sliding plate 11 by the elastic rope 12, and when the aircraft body 1 rotates at a large angle, the sliding plate 11 may incline downwards, so that the sliding plate 11 slides due to gravity, and the limiting rod 9 falls off from the clamping groove 8; through laying camera 4 on aircraft body 1, and let aircraft body 1 be located between a set of fixed plate 5, then upwards slide 11, make gag lever post 9 follow roll-off in draw-in groove 8, then clockwise rotation pivot 10, make connecting wire 14 winding on pivot 10, connecting wire 14 can stimulate disc 16 this moment, thereby make disc 16 drive slide bar 6 move, slide bar 6 can promote clamp splice 7 and carry out the centre gripping to camera 4 this moment, thereby fix camera 4 on aircraft body 1, then promote slide 11, make gag lever post 9 and circular slot joint, connecting wire 14 can be in the state of stretching straight this moment and avoid slide bar 6 to appear moving, when needs take away camera 4 from aircraft body 1, stimulate slide 11, make gag lever post 9 follow roll-off in draw-in groove 8, later reverse pivot 10, make connecting wire 14 loosen from pivot 10, then directly take away camera 4 from aircraft body 1.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention.
Claims (6)
1. An aircraft rotatable through 360 °, characterized in that: comprising an aircraft body (1); the utility model discloses an aircraft, including aircraft body (1), camera (4), fixed plate (16), the even fixedly connected with linking arm (2) of top face of aircraft body (1), the one end fixed mounting that aircraft body (1) was kept away from in linking arm (2) has rotor (3), camera (4) have been placed to the top face of aircraft body (1), a set of fixed plate (5) of top face fixedly connected with of aircraft body (1), sliding connection has slide bar (6) in fixed plate (5), slide bar (6) are close to one end fixedly connected with "U" font clamp splice (7) of camera (4), the fixed surface of fixed plate (5) is connected with disc (16), the lateral wall fixedly connected with connecting wire (14) of disc (16), the one end fixed mounting that disc (16) were kept away from in connecting wire (14) has pivot (10), the bottom and fixed plate (5) internal rotation of pivot (10) are connected, the sliding surface of pivot (10) is connected with slide (11), the bottom fixedly connected with gag lever post (9) of slide (11), multiunit draw-in groove (8) have been seted up on the top of fixed plate (5), the inner wall joint of gag lever post (9) and draw-in groove (8).
2. An aircraft rotatable through 360 ° according to claim 1, wherein: the surface fixed connection of pivot (10) has connecting plate (13), the top fixed connection of connecting plate (13) has elasticity rope (12), the one end and slide (11) fixed connection of connecting plate (13) are kept away from in elasticity rope (12).
3. An aircraft rotatable through 360 ° according to claim 2, wherein: one side that disc (16) are close to fixed plate (5) fixed mounting has spring (15), the one end and fixed plate (5) fixed connection of disc (16) are kept away from in spring (15).
4. An aircraft rotatable through 360 ° according to claim 3, wherein: recess (23) have all been seted up to the corresponding both sides of clamp splice (7) inner wall, the inner wall fixedly connected with rectangular plate (21) of recess (23), sliding connection has round bar (22) in rectangular plate (21), the first magnetic path of one end fixedly connected with (19) of recess (23) is kept away from in round bar (22), the second magnetic path (20) that the first magnetic path of inner wall fixedly connected with (19) of recess (23) repel each other.
5. An aircraft rotatable through 360 ° according to claim 4, wherein: one end, far away from the round rod (22), of the first magnetic block (19) is fixedly connected with a rubber block (18), and the rubber block (18) is arc-shaped.
6. An aircraft rotatable through 360 ° according to claim 5, wherein: the aircraft is characterized in that a supporting plate (24) is fixedly mounted on the top end face of the aircraft body (1), a sliding groove (25) is formed in the surface of the supporting plate (24) in a penetrating mode, a pressing plate (26) is connected to the inner wall of the sliding groove (25), a supporting block (27) is fixedly connected to one side, far away from the camera (4), of the supporting plate (24), a threaded rod (28) is connected to the supporting block (27) in an internal thread mode, and the bottom end of the threaded rod (28) is connected with the pressing plate (26) in a rotating mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223319929.XU CN218662395U (en) | 2022-12-09 | 2022-12-09 | Aircraft capable of rotating by 360 degrees |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202223319929.XU CN218662395U (en) | 2022-12-09 | 2022-12-09 | Aircraft capable of rotating by 360 degrees |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218662395U true CN218662395U (en) | 2023-03-21 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202223319929.XU Active CN218662395U (en) | 2022-12-09 | 2022-12-09 | Aircraft capable of rotating by 360 degrees |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN218662395U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117682121A (en) * | 2024-02-04 | 2024-03-12 | 山东润达工程设计有限公司 | Measuring equipment for planning homeland space |
-
2022
- 2022-12-09 CN CN202223319929.XU patent/CN218662395U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117682121A (en) * | 2024-02-04 | 2024-03-12 | 山东润达工程设计有限公司 | Measuring equipment for planning homeland space |
| CN117682121B (en) * | 2024-02-04 | 2024-04-09 | 山东润达工程设计有限公司 | Measuring equipment for planning homeland space |
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