CN215554113U - Full-electric tilt rotor unmanned aerial vehicle convenient to maintain - Google Patents
Full-electric tilt rotor unmanned aerial vehicle convenient to maintain Download PDFInfo
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- CN215554113U CN215554113U CN202121991218.XU CN202121991218U CN215554113U CN 215554113 U CN215554113 U CN 215554113U CN 202121991218 U CN202121991218 U CN 202121991218U CN 215554113 U CN215554113 U CN 215554113U
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- 230000000149 penetrating effect Effects 0.000 claims abstract description 7
- 238000012423 maintenance Methods 0.000 abstract description 10
- 238000003780 insertion Methods 0.000 description 4
- 230000037431 insertion Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 230000004888 barrier function Effects 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model discloses a full-electric tilting rotor unmanned aerial vehicle convenient to maintain, which relates to the technical field of unmanned aerial vehicles and comprises a body, wherein an annular groove is formed in the front side surface of the body, a cover plate is fixedly connected to the inner wall of the annular groove, a through groove is formed in the front side surface of the cover plate in a penetrating manner, a first motor is fixedly connected to the front side surface of the body, the rear end of the first motor is positioned at the geometric center of the cover plate, a fixed block is fixedly connected to the front side surface of a rotating shaft of the first motor, sliders are fixedly connected to the upper surface and the lower surface of each fixed block, a connecting pipe is arranged at the front end of the body, a sliding groove is formed in the rear end of the inner wall of the connecting pipe, and one end, far away from the fixed block, of each slider is slidably connected with the inner wall of the sliding groove of the connecting pipe, so that the tilting rotor unmanned aerial vehicle is very fast due to the special flying mode, an operator is easy to control if not experienced, the unmanned aerial vehicle is collided and falls, and the integrated body can only be completely scrapped and replaced after being damaged, inconvenient maintenance and increased use cost.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a full-electric tilt rotor unmanned aerial vehicle convenient to maintain.
Background
The tiltrotor aircraft is a novel aircraft integrating a fixed-wing aircraft and a helicopter, has the capabilities of taking off and landing a common helicopter and hovering in the air, has the capability of cruising and flying at a high speed of a turboprop aircraft, and is applied to an unmanned aerial vehicle by the technology at present.
According to "a full-electric rotor unmanned aerial vehicle that verts that chinese patent authorizes bulletin number CN 210455231U provides", can vert the rotor aircraft paddle and rotate through the power motor drive, the rotor aircraft paddle that verts of motor drive verts, thereby accomplish the switching of different flight modes, however, the rotor unmanned aerial vehicle that verts is because the mode of its flight is special, often speed is very fast, the operator if not experienced controls very easily, lead to the unmanned aerial vehicle collision to fall, the fuselage of integral type can only all scrap the replacement after receiving the damage, be not convenient for maintain, increase use cost.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a full-electric tilt rotor unmanned aerial vehicle convenient to maintain, and solves the technical problems that the tilt rotor unmanned aerial vehicle is very high in speed due to a special flight mode, an operator is easy to control if the tilt rotor unmanned aerial vehicle is not skilled, the unmanned aerial vehicle is collided and falls off, an integrated body can only be completely scrapped and replaced after being damaged, the maintenance is inconvenient, and the use cost is increased.
In order to achieve the purpose, the utility model provides the following technical scheme: a full-electric tilting rotor unmanned aerial vehicle convenient to maintain comprises a vehicle body, wherein an annular groove is formed in the front side surface of the vehicle body, a cover plate is fixedly connected to the inner wall of the annular groove, a through groove is formed in the front side surface of the cover plate in a penetrating manner, a first motor is fixedly connected to the front side surface of the vehicle body, the rear end of the first motor is located at the geometric center of the cover plate, a fixed block is fixedly connected to the front side surface of a rotating shaft of the first motor, sliders are fixedly connected to the upper surface and the lower surface of each fixed block, a connecting pipe is arranged at the front end of the vehicle body, a sliding groove is formed in the rear end of the inner wall of the connecting pipe, one end, away from the fixed block, of each slider is slidably connected to the inner wall of the sliding groove of the connecting pipe, a clamping block is fixedly connected to the rear ends of the left side surface and the right side surface of the connecting pipe, the inner wall of the annular groove of the vehicle body is rotatably connected to the rear side surface of the connecting pipe, the front side center fixedly connected with connecting rod of connecting pipe, the leading flank fixedly connected with motor two of connecting rod, fixed surface is connected with the rotor in the pivot of motor two, the side structure is to this setting around the fuselage, the side runs through and has seted up the spread groove about the fuselage, the left side of fuselage is provided with the leading-in aircraft body.
Preferably, the fixed plate is fixedly connected with the upper end of the opening of the connecting groove on the right side surface of the machine body, the clamping rod is connected with the upper surface of the fixed plate in a penetrating and sliding mode, the inserting rod is fixedly connected with the right side surface of the front-end processor body, the inserting hole is formed in the right end of the upper surface of the inserting rod in a penetrating mode, the inner wall of the connecting groove in the sliding mode is connected with the side surface of the inserting rod in a penetrating mode, and the inner wall of the inserting hole in the sliding mode is connected with the lower end of the clamping rod in a penetrating mode.
Preferably, the left side surface of the front-end engine body is fixedly connected with the engine head, the front side surface and the rear side surface of the front-end engine body are fixedly connected with the wings, and the wings are symmetrically arranged in the front and the rear direction by taking the front-end engine body as a central shaft.
Preferably, the lower surfaces of the front-end processor body and the machine body are fixedly connected with a support.
Preferably, the right end of the upper surface of the machine body is fixedly connected with a supporting rod, and the upper surface of the supporting rod is fixedly connected with an empennage.
Preferably, the nose is bullet shaped.
Compared with the prior art, the full-electric tilting rotor unmanned aerial vehicle convenient to maintain has the following beneficial effects:
the utility model provides a full-electric tilting rotor unmanned aerial vehicle convenient to maintain, which is characterized in that an annular groove and a clamping block are arranged, when a maintenance device is recovered, if the front side structure and the rear side structure of a machine body are damaged, a connecting pipe is manually rotated to enable the clamping block to be aligned with an opening of a through groove, then the connecting pipe is taken out of the annular groove of the machine body, a sliding block slides along the sliding groove at the rear end of the inner wall of the connecting pipe until the sliding block slides out, then a new group of motor II and a rotor wing are replaced, the corresponding clamping block is inserted into the through groove and rotates, a rotating shaft of the motor II is in a vertical upward angle, so that the initial state is recovered, the through groove is arranged at a position which enables the clamping block not to pass through the opening of the through groove when the motor I drives the motor II to rotate, so as to avoid the sliding groove, the structure is convenient and fast to replace by matching with the sliding groove of the inner wall of the sliding block and the connecting pipe, the maintenance is convenient, and the problem that the tilting rotor unmanned aerial vehicle is special in flying mode is solved, often speed is very fast, and the operator if not familiar controls very easily and does not live, leads to the unmanned aerial vehicle collision to fall, and the fuselage of integral type can only all scrap the replacement after receiving the damage, and the maintenance of not being convenient for increases use cost's technical problem.
The utility model provides a full-electric tilting rotor unmanned aerial vehicle convenient to maintain, which is characterized in that an inserting rod and a clamping rod are arranged, when a left structure of a machine body needs to be replaced, the clamping rod is pulled upwards to enable the lower end of the clamping rod to slip from the inner wall of an inserting hole, then a front-end machine body is pulled leftwards to enable the inserting rod to slip from the inner wall of a connecting groove, a new group of structures are replaced, the corresponding inserting rod is inserted into the connecting groove, the lower end of the clamping rod is inserted into the inserting hole, so that the replacement is completed quickly, the device can flexibly replace the structures by matching with a detachable connecting pipe without integral scrapping replacement, and the loss caused by crash is reduced.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a disassembled view of the overall structure of the present invention;
FIG. 3 is a disassembled view of the fuselage structure of the present invention;
FIG. 4 is an enlarged view of a portion of FIG. 3 according to the present invention.
In the figure: 1. fuselage, 2, apron, 3, logical groove, 4, motor one, 5, fixed block, 6, slider, 7, connecting pipe, 8, fixture block, 9, connecting rod, 10, motor two, 11, rotor, 12, spread groove, 13, fixed plate, 14, kelly, 15, leading-in machine body, 16, wing, 17, aircraft nose, 18, inserted bar, 19, jack, 20, support, 21, bracing piece, 22, fin.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments; all other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The first embodiment is as follows:
referring to fig. 1, 3 and 4, the utility model provides a technical scheme, which includes a machine body 1, wherein an annular groove is formed on the front side surface of the machine body 1, a cover plate 2 is fixedly connected to the inner wall of the annular groove, a through groove 3 is formed through the front side surface of the cover plate 2, a motor 1 is fixedly connected to the front side surface of the machine body 1, the rear end of the motor 4 is located at the geometric center of the cover plate 2, a fixed block 5 is fixedly connected to the front side surface of a rotating shaft of the motor 4, sliding blocks 6 are fixedly connected to the upper and lower surfaces of the fixed block 5, a connecting pipe 7 is arranged at the front end of the machine body 1, a sliding groove is formed at the rear end of the inner wall of the connecting pipe 7, one end of the sliding block 6, which is far away from the fixed block 5, is slidably connected to the inner wall of the connecting pipe 7, a clamping block 8 is fixedly connected to the rear ends of the left and right side surfaces of the connecting pipe 7, the side surfaces of the clamping block 8 are slidably connected to the inner wall of the through groove 3, the rear side surface of the connecting pipe 7 is rotatably connected to the inner wall of the annular groove of the machine body 1, fixedly connected with connecting rod 9 is located at the leading flank center of connecting pipe 7, leading flank fixedly connected with motor two 10 of connecting rod 9, fixed surface is connected with rotor 11 in the pivot of motor two 10, side structure is setting up to this around fuselage 1, the side runs through and has seted up spread groove 12 about fuselage 1, the left side of fuselage 1 is provided with leading fuselage 15, the left surface fixedly connected with aircraft nose 17 of leading fuselage 15, the equal fixedly connected with wing 16 in side around leading fuselage 15, wing 16 is the central axis symmetry setting around leading fuselage 15, the equal fixedly connected with support 20 of lower surface of leading fuselage 15 and fuselage 1, the upper surface right-hand member fixedly connected with bracing piece 21 of fuselage 1, the upper surface fixedly connected with fin 22 of bracing piece 21, aircraft nose 17 shape is warhead shape.
In this embodiment: the device is placed on a flat table board, in an initial state, a rotating shaft of a motor II 10 is vertically upward, a rotor wing 11 rotates to blow downwards to generate upward thrust to lift the device, after the device rises to a proper height, a motor I4 drives a fixing block 5 to rotate, the fixing block 5 drives a connecting pipe 7 to rotate through a sliding block 6, so that the rotor wing 11 changes direction, the rotor wing 11 rotates towards one side of a wing 16 to realize tilting, when the connecting pipe 7 rotates, the rear end of the connecting pipe 7 and a clamping block 8 rotate along the inner wall of an annular groove on the side surface of a machine body 1, a cover plate 2 clamps the clamping block 8 to prevent slipping, an internal program of the device is set, when the device is collided, the motor II 10 is impacted and automatically powered off, at the moment, a machine head 17 or the wing 16 firstly contacts with an impactor and is pressed to deform, so that impact force is absorbed, the rotor wing 11 is positioned on the right side of the wing 16, and the wing 16 plays a role of protective barrier, when the maintenance device is recovered, if the front side structure and the rear side structure of the machine body 1 are damaged, the connecting pipe 7 is manually rotated to enable the clamping block 8 to be aligned with the opening of the through groove 3, then the connecting pipe 7 is taken out of the annular groove of the machine body 1, the sliding block 6 slides along the sliding groove at the rear end of the inner wall of the connecting pipe 7 until sliding out, then a new group of motor II 10 and the rotor wing 11 are replaced, the corresponding clamping block 8 is inserted into the through groove 3 and rotates, the rotating shaft of the motor II 10 is in a vertical upward angle, so that the initial state is recovered, the through groove 3 is arranged at a position that the clamping block 8 cannot pass through the opening of the through groove 3 when the motor I4 drives the motor II 10 to rotate, so as to avoid slipping, the annular groove and the clamping block 8 are arranged, and the sliding grooves of the sliding block 6 and the inner wall of the connecting pipe 7 are matched, so that the structure is convenient and quick to replace, the maintenance is convenient, and the problem that the unmanned aerial vehicle with the tilting mode is special, often speed is very fast, and the operator if not familiar controls very easily and does not live, leads to the unmanned aerial vehicle collision to fall, and the fuselage of integral type can only all scrap the replacement after receiving the damage, and the maintenance of not being convenient for increases use cost's technical problem.
Example two:
referring to fig. 1-2, on the basis of the first embodiment, the present invention provides a technical solution: fixed plate 13 is connected to the right flank spread groove 12 opening upper end fixedly of fuselage 1, and sliding connection has a kelly 14 to the upper surface of fixed plate 13 runs through, and the right flank fixedly connected with inserted bar 18 of front-end processor 15, the upper surface right-hand member of inserted bar 18 run through and have seted up jack 19, and the side of inserted bar 18 runs through the inner wall of sliding connection spread groove 12, and the lower extreme of kelly 14 runs through the inner wall of sliding connection jack 19.
In this embodiment: when needing to replace 1 left side structure of fuselage, go up pull-up kelly 14 and make 14 lower extremes of kelly from 19 inner walls slippage of jack, then pull leading-in fuselage 15 left side and make inserted bar 18 follow the inner wall slippage of spread groove 12, change a new set of structure, inserted bar 18 that will correspond inserts spread groove 12, insert jack 19 with 14 lower extremes of kelly, thereby accomplish the replacement fast, cooperation detachable connecting pipe 7, the device can replace the structure in a flexible way, need not wholly scrap the replacement, reduce the loss that the crash brought.
The working principle is as follows: the device is placed on a flat table board, in an initial state, a rotating shaft of a motor II 10 is vertically upward, a rotor wing 11 rotates to blow downwards to generate upward thrust to lift the device, after the device rises to a proper height, a motor I4 drives a fixing block 5 to rotate, the fixing block 5 drives a connecting pipe 7 to rotate through a sliding block 6, so that the rotor wing 11 changes direction, the rotor wing 11 rotates towards one side of a wing 16 to realize tilting, when the connecting pipe 7 rotates, the rear end of the connecting pipe 7 and a clamping block 8 rotate along the inner wall of an annular groove on the side surface of a machine body 1, a cover plate 2 clamps the clamping block 8 to prevent slipping, an internal program of the device is set, when the device is collided, the motor II 10 is impacted and automatically powered off, at the moment, a machine head 17 or the wing 16 firstly contacts with an impactor and is pressed to deform, so that impact force is absorbed, the rotor wing 11 is positioned on the right side of the wing 16, and the wing 16 plays a role of protective barrier, when the maintenance device is recovered, if the front side structure and the rear side structure of the machine body 1 are damaged, the connecting pipe 7 is manually rotated to enable the clamping block 8 to be aligned with the opening of the through groove 3, then the connecting pipe 7 is taken out of the annular groove of the machine body 1, the sliding block 6 slides along the sliding groove at the rear end of the inner wall of the connecting pipe 7 until sliding out, then a new group of motor II 10 and the rotor 11 are replaced, the corresponding clamping block 8 is inserted into the through groove 3 and rotates, the rotating shaft of the motor II 10 is in a vertical upward angle, so that the initial state is recovered, the through groove 3 is arranged at a position that the clamping block 8 cannot pass through the opening of the through groove 3 when the motor I4 drives the motor II 10 to rotate, so as to avoid slipping, the structure is conveniently and quickly replaced by arranging the annular groove and the clamping block 8 and matching the sliding grooves of the sliding block 6 and the inner wall of the connecting pipe 7, the maintenance device is convenient, when the left side structure of the machine body 1 needs to be replaced, the upper pulling of the clamping rod 14 causes the lower end of the clamping rod 14 to slip off the inner wall of the insertion hole 19, then the front-end processor body 15 is pulled to the left side to cause the insertion rod 18 to slip off the inner wall of the connecting groove 12, a new set of structure is replaced, the corresponding insertion rod 18 is inserted into the connecting groove 12, the lower end of the clamping rod 14 is inserted into the insertion hole 19, and therefore replacement is completed quickly.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides a full-electric rotor unmanned aerial vehicle that verts convenient to maintain, includes fuselage (1), its characterized in that: the improved structure of the airplane is characterized in that an annular groove is formed in the front side face of the airplane body (1), a cover plate (2) is fixedly connected to the inner wall of the annular groove, a through groove (3) is formed in the front side face of the cover plate (2) in a penetrating mode, a motor I (4) is fixedly connected to the front side face of the airplane body (1), the rear end of the motor I (4) is located at the geometric center of the cover plate (2), a fixing block (5) is fixedly connected to the front side face of a rotating shaft of the motor I (4), a sliding block (6) is fixedly connected to the upper surface and the lower surface of the fixing block (5), a connecting pipe (7) is arranged at the front end of the airplane body (1), a sliding groove is formed in the rear end of the inner wall of the connecting pipe (7), the sliding groove inner wall of the sliding block (6) is connected to one end of the connecting pipe (7) in a sliding mode, and a clamping block (8) is fixedly connected to the rear end of the left side face and right side face of the connecting pipe (7), the inner wall that leads to groove (3) is connected to the side sliding of fixture block (8), the trailing flank of connecting pipe (7) rotates the annular groove inner wall of connecting fuselage (1), fixedly connected with connecting rod (9) are located at the leading flank center of connecting pipe (7), the leading flank fixedly connected with motor two (10) of connecting rod (9), fixed surface is connected with rotor (11) in the pivot of motor two (10), fuselage (1) front and back side structure is to this setting, fuselage (1) is left and right sides side and is run through and has been seted up spread groove (12), the left side of fuselage (1) is provided with leading-in aircraft body (15).
2. A full-electric tilt rotor unmanned aerial vehicle convenient to maintain according to claim 1, characterized in that: right flank spread groove (12) opening upper end fixedly connected with fixed plate (13) of fuselage (1), the upper surface of fixed plate (13) runs through sliding connection has kelly (14), the right flank fixedly connected with inserted bar (18) of leading fuselage (15), the upper surface right-hand member of inserted bar (18) runs through and has seted up jack (19), the inner wall of sliding connection spread groove (12) is run through to the side of inserted bar (18), the inner wall of sliding connection jack (19) is run through to the lower extreme of kelly (14).
3. A full-electric tilt rotor unmanned aerial vehicle convenient to maintain according to claim 1, characterized in that: the left side surface of the front-end processor body (15) is fixedly connected with a machine head (17), the front side surface and the rear side surface of the front-end processor body (15) are fixedly connected with wings (16), and the wings (16) are symmetrically arranged in the front and the rear direction by taking the front-end processor body (15) as a central shaft.
4. A full-electric tilt rotor unmanned aerial vehicle convenient to maintain according to claim 1, characterized in that: the lower surfaces of the front-end processor body (15) and the processor body (1) are fixedly connected with a support (20).
5. A full-electric tilt rotor unmanned aerial vehicle convenient to maintain according to claim 1, characterized in that: the right end of the upper surface of the machine body (1) is fixedly connected with a supporting rod (21), and the upper surface of the supporting rod (21) is fixedly connected with an empennage (22).
6. A full-electric tilt rotor unmanned aerial vehicle convenient to maintain according to claim 3, wherein: the nose (17) is bullet-shaped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121991218.XU CN215554113U (en) | 2021-08-23 | 2021-08-23 | Full-electric tilt rotor unmanned aerial vehicle convenient to maintain |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121991218.XU CN215554113U (en) | 2021-08-23 | 2021-08-23 | Full-electric tilt rotor unmanned aerial vehicle convenient to maintain |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215554113U true CN215554113U (en) | 2022-01-18 |
Family
ID=79840876
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121991218.XU Expired - Fee Related CN215554113U (en) | 2021-08-23 | 2021-08-23 | Full-electric tilt rotor unmanned aerial vehicle convenient to maintain |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215554113U (en) |
-
2021
- 2021-08-23 CN CN202121991218.XU patent/CN215554113U/en not_active Expired - Fee Related
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Granted publication date: 20220118 |
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| CF01 | Termination of patent right due to non-payment of annual fee |