CN209889104U - Composite wing aerial survey unmanned aerial vehicle - Google Patents
Composite wing aerial survey unmanned aerial vehicle Download PDFInfo
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- CN209889104U CN209889104U CN201920643479.9U CN201920643479U CN209889104U CN 209889104 U CN209889104 U CN 209889104U CN 201920643479 U CN201920643479 U CN 201920643479U CN 209889104 U CN209889104 U CN 209889104U
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Abstract
The utility model relates to an unmanned air vehicle technique field specifically is a compound wing aerial survey unmanned aerial vehicle, including the unmanned aerial vehicle body, the both sides of unmanned aerial vehicle body all are provided with the wing, are equipped with many rotor horn on the wing, and the both ends of many rotor horn all closely bond and have the sleeve, install the motor in the sleeve, are equipped with a plurality of screw on the rotation head on the output of motor. This unmanned aerial vehicle is surveyed in compound wing aviation, all be provided with many rotor horn on the wing that unmanned aerial vehicle body both sides set up, the motor is installed at many rotor horn both ends, overhead a plurality of screw that is equipped with rotates on the motor output, can provide a comparatively balanced lift for taking off and descending of unmanned aerial vehicle body after the screw rotates for the unmanned aerial vehicle body is taking off and descending in-process and is moving more steadily, solves the problem that unmanned aerial vehicle is not convenient for take off and descend.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field specifically is a compound wing aerial survey unmanned aerial vehicle.
Background
The aerial survey unmanned aerial vehicle has the characteristics of flexibility, high efficiency, rapidness, fineness, accuracy, low operation cost, wide application range and short production period, has obvious advantages in the aspect of rapidly acquiring high-resolution images in small areas and areas with difficult flight, and along with the development of the unmanned aerial vehicle and the digital camera technology, the aerial survey unmanned aerial vehicle is widely applied to the fields of national major engineering construction, disaster response, emergency and treatment, national surveillance, resource development and the like in recent years.
The current mode of taking off at unmanned aerial vehicle is thrown or launches for the hand, receives crosswind easily and takes off and in the twinkling of an eye the gesture influence cause unmanned aerial vehicle take off the failure to fall the machine, and the descending mode is automatic parachute opening and descends, receives gravity and wind-force influence under the parachute opening normal condition, and the descending precision is low, and the easy skew settlement landing point that falls, and the impact force is great when the organism falls to the ground, can cause certain damage to organism and the precision equipment that carries on, and unmanned aerial vehicle takes off and descends not be convenient for. In view of this, we propose a composite wing aerial survey unmanned aerial vehicle.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a compound wing aerial survey unmanned aerial vehicle to solve the problem that the unmanned aerial vehicle that provides is not convenient for take off and descend in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
a composite wing aerial survey unmanned aerial vehicle comprises an unmanned aerial vehicle body, wherein wings are arranged on two sides of the unmanned aerial vehicle body, a multi-rotor wing arm is arranged on each wing, sleeves are tightly bonded at two ends of each multi-rotor wing arm, a motor is arranged in each sleeve, a rotating head is tightly bonded at the output end of each motor, a plurality of propellers are tightly bonded on each rotating head, a socket is arranged at the middle position of each multi-rotor wing arm, a bottom plate is arranged on the upper surface of each multi-rotor wing arm, a plug is arranged at the middle position of each bottom plate, through holes are formed in four corners of each bottom plate, a fixing plate is arranged on each through hole and is tightly bonded with the lower surface of each wing, a screwed pipe is tightly bonded at one end of each fixing plate, a third bolt is arranged at one end of each screwed pipe penetrating through each through hole, and an inserting pipe is tightly bonded at the other end of, a limiting plate is arranged between the two insertion pipes positioned on the same side, and bolts are tightly adhered to two ends of the limiting plate.
Preferably, the plug is matched with the socket in size, and the plug is matched with the socket in a plugging mode.
Preferably, the outer diameter of the threaded pipe is matched with the diameter of the through hole, and the third bolt is in threaded connection with the threaded pipe.
Preferably, the diameter of the plug is matched with the inner diameter of the insertion pipe, and two ends of the limiting plate are in insertion fit with the insertion pipe through the plug.
Preferably, the both sides of socket all are provided with first bolt, the socket pass through first bolt with the upper surface fixed connection of many rotor-wing horn.
Preferably, both sides of the plug are provided with second bolts, and the plug is fixedly connected with the lower surface of the bottom plate through the second bolts.
Preferably, the number of the propellers is 2-4, and the propellers are arranged in an annular and equidistant mode.
Compared with the prior art, the beneficial effects of the utility model are that: this unmanned aerial vehicle is surveyed in compound wing aviation, all be provided with many rotor horn on the wing that unmanned aerial vehicle body both sides set up, the motor is installed at many rotor horn both ends, overhead a plurality of screw that is equipped with rotates on the motor output, can provide a comparatively balanced lift for taking off and descending of unmanned aerial vehicle body after the screw rotates, make the unmanned aerial vehicle body take off and descend the in-process and operate more steadily taking off, moreover, the steam generator is simple in structure, high durability and convenient use, solve the problem that unmanned aerial vehicle is not convenient for take off and descend.
Drawings
Fig. 1 is a schematic view of the overall structure of the present invention;
fig. 2 is a bottom plan view of the unmanned aerial vehicle body of the present invention;
fig. 3 is a schematic structural view of a multi-rotor horn according to the present invention;
FIG. 4 is an enlarged view of the structure A in FIG. 3 according to the present invention;
FIG. 5 is a schematic view of a part of the structure of the motor of the present invention;
FIG. 6 is a schematic view of the overall structure of the bottom surface of the middle bottom plate of the present invention;
fig. 7 is a schematic bottom structure view of the middle bottom plate of the present invention;
fig. 8 is the utility model discloses the structure schematic diagram of well fixed plate and limiting plate.
In the figure: 1. an unmanned aerial vehicle body; 11. an airfoil; 2. a multi-rotor horn; 21. a sleeve; 22. a motor; 23. rotating the head; 231. a propeller; 24. a socket; 241. a first bolt; 3. a base plate; 31. a plug; 311. a second bolt; 32. a through hole; 33. a fixing plate; 331. a threaded pipe; 332. a third bolt; 333. inserting a pipe; 34. a limiting plate; 341. and (4) a bolt.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first", "second", "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", "third" may explicitly or implicitly include one or more of the features. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.
Example 1
A compound wing aerial survey unmanned aerial vehicle is disclosed, as shown in figures 1-8, comprising an unmanned aerial vehicle body 1, wings 11 are arranged on both sides of the unmanned aerial vehicle body 1, a multi-rotor wing arm 2 is arranged on the wings 11, sleeves 21 are tightly adhered on both ends of the multi-rotor wing arm 2, a motor 22 is arranged in each sleeve 21, a rotating head 23 is tightly adhered on an output end of each motor 22, a plurality of propellers 231 are tightly adhered on each rotating head 23, a socket 24 is arranged at the middle position of the multi-rotor wing arm 2, a bottom plate 3 is arranged on the upper surface of the multi-rotor wing arm 2, a plug 31 is arranged at the middle position of the bottom plate 3, through holes 32 are arranged at four corners of the bottom plate 3, a fixing plate 33 is arranged on each through hole 32, the fixing plate 33 is tightly adhered to the lower surface of the wings 11, a screwed pipe 331 is tightly adhered on one end of the fixing plate 33, a, the other end of the fixed plate 33 is tightly bonded with the plug-in pipe 333, a limit plate 34 is arranged between the two plug-in pipes 333 at the same side, and the two ends of the limit plate 34 are tightly bonded with the bolts 341.
In this embodiment, many rotor horn 2 and screw 231 all adopt the composite carbon fiber material to make, and this material has good wear-resisting corrosion resistance, and the structure is firm, and the quality advantage such as lighter prolongs the life of many rotor horn 2 and screw 231.
Furthermore, the plug 31 is matched with the socket 24 in size, and the plug 31 is matched with the socket 24 in an inserting manner, so that the motor 22 can be conveniently powered by connecting an external battery after the plug 31 is inserted into the socket 24.
In addition, the outer diameter of the threaded tube 331 is adapted to the diameter of the through hole 32, and the third bolt 332 is screwed into the threaded tube 331, and in this embodiment, the outer diameter of the threaded tube 331 is preferably 2cm, so that the fixing plate 33 can be easily installed above the bottom plate 3 by screwing the third bolt 332 into the threaded tube 331.
It is worth to be noted that the diameter of the plug 341 is adapted to the inner diameter of the plug tube 333, and the two ends of the limiting plate 34 are in plug fit with the plug tube 333 through the plug 341, so that the limiting plate 34 is fixed on the plug tube 333 by using the plug 341, and the limiting plate 34 limits the two ends of the multi-rotor arm 2.
Specifically, the number of the propellers 231 is 2-4, and the propellers 231 are arranged in a ring shape at equal intervals, and the number of the propellers 231 in the embodiment is preferably 2.
In this embodiment, all be provided with many rotor horn 2 on the wing 11 that unmanned aerial vehicle body 1 both sides set up, many rotor horn 2 are convenient for play to unmanned aerial vehicle body 1 and rise and descend, specifically do: the socket 24 arranged on the multi-rotor aircraft arm 2 is inserted and matched with the plug 31 arranged on the bottom plate 3, the motors 22 arranged at the two ends of the multi-rotor aircraft arm 2 are connected with an external power supply to enable the multi-rotor aircraft arm to work, meanwhile, the limit plates 34 are covered at the two ends of the multi-rotor wing aircraft arm 2, and the plugs 341 arranged at the two ends of the limit plates 34 are matched with the plug pipes 333 in a plug way, when the output end of the motor 22 is provided with the rotating head 23, and the rotating head 23 is provided with the plurality of propellers 231, the propellers 231 can provide a relatively balanced lift force for taking off and landing of the unmanned aerial vehicle body 1 after rotating, in addition, because the four corners of bottom plate 3 all is provided with through-hole 32 to through making screwed pipe 331 on the fixed plate 33 pass through-hole 32, utilize third bolt 332 to install the four corners of bottom plate 3 on fixed plate 33, the dismouting and the maintenance of bottom plate 3 of being convenient for, simple structure, convenient to use solve the problem that unmanned aerial vehicle is not convenient for take off and descend.
Example 2
As the utility model discloses a second kind preferred embodiment, the both sides of socket 24 all are provided with first bolt 241, and socket 24 is connected through the last fixed surface of first bolt 241 with many rotor horn 2, is equipped with the screw with first bolt 241 looks adaptation on many rotor horn 2 for first bolt 24 and this screw threaded connection, the installation of the socket 24 of being convenient for is fixed.
Example 3
As the third preferred embodiment of the present invention, the two sides of the plug 31 are all provided with the second bolt 311, the plug 31 is connected with the lower surface fixing of the bottom plate 3 through the second bolt 311, and the bottom plate 3 is provided with a screw hole adapted to the second bolt 311, so that the second bolt 311 is connected with the screw hole by screw threads, and the plug 31 is convenient to install and fix.
The utility model discloses a compound wing aerial survey unmanned aerial vehicle all is provided with many rotor horn 2 on the wing 11 that unmanned aerial vehicle body 1 both sides set up when using, and many rotor horn 2 are convenient for to rising to rise and descending of unmanned aerial vehicle body 1, specifically do: the socket 24 arranged on the multi-rotor wing arm 2 is matched with the plug 31 arranged on the bottom plate 3 in an inserting way, the motor 22 arranged at the two ends of the multi-rotor wing arm 2 is connected with an external power supply to enable the multi-rotor wing arm 2 to work, meanwhile, the limiting plate 34 is covered at the two ends of the multi-rotor wing arm 2, the plug pins 341 arranged at the two ends of the limiting plate 34 are matched with the plug pipes 333 in an inserting way, when the output end of the motor 22 is provided with the rotating head 23, and the rotating head 23 is provided with a plurality of propellers 231, after the propellers 231 rotate, a more balanced lifting force can be provided for the takeoff and landing of the unmanned aerial vehicle body 1, in addition, as the four corners of the bottom plate 3 are all provided with through holes 32, and the threaded pipes 331 on the fixing plate 33 pass through the through holes 32, the four corners of the bottom plate 3 are arranged on the fixing plate 33 by utilizing the third bolts 332, is convenient for popularization and promotion.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It should be understood by those skilled in the art that the present invention is not limited by the above embodiments, and the description in the above embodiments and the description is only preferred examples of the present invention, and is not intended to limit the present invention, and that the present invention can have various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications all fall into the scope of the claimed invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (7)
1. The utility model provides a compound wing air survey unmanned aerial vehicle, includes unmanned aerial vehicle body (1), its characterized in that: both sides of the unmanned aerial vehicle body (1) are provided with wings (11), the wings (11) are provided with a plurality of rotor arms (2), both ends of the rotor arms (2) are tightly bonded with sleeves (21), a motor (22) is installed in the sleeves (21), the output end of the motor (22) is tightly bonded with a rotating head (23), the rotating head (23) is tightly bonded with a plurality of propellers (231), a socket (24) is arranged at the middle position of the rotor arms (2), the upper surface of the rotor arms (2) is provided with a bottom plate (3), a plug (31) is arranged at the middle position of the bottom plate (3), four corners of the bottom plate (3) are provided with through holes (32), a fixing plate (33) is arranged on the through holes (32), and the fixing plate (33) is tightly bonded with the lower surfaces of the wings (11), the one end of fixed plate (33) closely bonds and has screwed pipe (331), screwed pipe (331) pass the one end of through-hole (32) is equipped with third bolt (332), the other end of fixed plate (33) closely bonds and has grafting pipe (333), is located to be equipped with limiting plate (34) between two grafting pipes (333) of same side, the both ends of limiting plate (34) all closely bond and have bolt (341).
2. The compound wing aerial survey drone of claim 1, wherein: the plug (31) is matched with the socket (24) in size, and the plug (31) is in plug-in fit with the socket (24).
3. The compound wing aerial survey drone of claim 1, wherein: the outer diameter of the threaded pipe (331) is matched with the diameter of the through hole (32), and the third bolt (332) is in threaded connection with the threaded pipe (331).
4. The compound wing aerial survey drone of claim 1, wherein: the diameter of the plug pin (341) is matched with the inner diameter of the plug pipe (333), and two ends of the limiting plate (34) are in plug fit with the plug pipe (333) through the plug pin (341).
5. The compound wing aerial survey drone of claim 1, wherein: the both sides of socket (24) all are provided with first bolt (241), socket (24) pass through first bolt (241) with the upper surface fixed connection of many rotor-wing horn (2).
6. The compound wing aerial survey drone of claim 1, wherein: and second bolts (311) are arranged on two sides of the plug (31), and the plug (31) is fixedly connected with the lower surface of the bottom plate (3) through the second bolts (311).
7. The compound wing aerial survey drone of claim 1, wherein: the number of the propellers (231) is 2-4, and the propellers are arranged in an annular and equidistant mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920643479.9U CN209889104U (en) | 2019-05-03 | 2019-05-03 | Composite wing aerial survey unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920643479.9U CN209889104U (en) | 2019-05-03 | 2019-05-03 | Composite wing aerial survey unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN209889104U true CN209889104U (en) | 2020-01-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920643479.9U Expired - Fee Related CN209889104U (en) | 2019-05-03 | 2019-05-03 | Composite wing aerial survey unmanned aerial vehicle |
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| Country | Link |
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| CN (1) | CN209889104U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112537444A (en) * | 2020-12-15 | 2021-03-23 | 彩虹无人机科技有限公司 | Hovering automatic wind alignment method for composite wing unmanned aerial vehicle |
-
2019
- 2019-05-03 CN CN201920643479.9U patent/CN209889104U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112537444A (en) * | 2020-12-15 | 2021-03-23 | 彩虹无人机科技有限公司 | Hovering automatic wind alignment method for composite wing unmanned aerial vehicle |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200103 Termination date: 20210503 |
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| CF01 | Termination of patent right due to non-payment of annual fee |