CN211196627U - Eight-rotor unmanned aerial vehicle - Google Patents
Eight-rotor unmanned aerial vehicle Download PDFInfo
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- CN211196627U CN211196627U CN201922165467.2U CN201922165467U CN211196627U CN 211196627 U CN211196627 U CN 211196627U CN 201922165467 U CN201922165467 U CN 201922165467U CN 211196627 U CN211196627 U CN 211196627U
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Abstract
The application provides an eight rotor unmanned aerial vehicle, cantilever system (3) including fuselage (1), undercarriage (2) and support motor (4), every motor (4) all have screw (5), cantilever system (3) include four main arms (31) of being connected with fuselage (1), and the end of every main arm (31) is outwards stretched out and is had two support arms (32), and the end-to-end support of every support arm (32) has one motor (4) that have screw (5). The utility model provides an eight rotor unmanned aerial vehicle through two support arms of outwards stretching out at the end of four main arms, has reduced the quantity of main arm, has increaseed the interval between the main arm, has also reduced the length of main arm. The support arm is located the end of main arm, through the angle between reasonable setting support arm and the main arm, can choose for use shorter support arm. Shorter main arm and support arm can obtain littleer structure size, therefore can greatly reduced unmanned aerial vehicle's volume, the unmanned aerial vehicle's of being convenient for quick assembly disassembly and transportation.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicles, especially relates to an unmanned aerial vehicle of many rotors, in particular to unmanned aerial vehicle with eight rotors.
Background
The unmanned aerial vehicle at present is multiaxis unmanned aerial vehicle mostly, like four-axis, six, the complete machine weight of taking off is very little, but the cantilever expansion is very big, brings certain difficulty for unmanned aerial vehicle's transportation, carry and save etc.. For example, CN 204587305U discloses eight rotor electric unmanned aerial vehicle of multi-functional folded cascade, mainly solves the problem that current rotor electric unmanned aerial vehicle usage is single, the structure is complicated, complete machine transportation difficulty. The angle such as eight rotors of above-mentioned prior art unmanned aerial vehicle sets up around the organism, leads to the application load of carrying on the organism to set up under the organism only, and because all directions all receive blockking of rotor, the load of carrying can only develop the operation downwards, can not launch the weapon or observe to oblique top, can only be suitable for in its description the operation such as spray below to unmanned aerial vehicle.
In order to solve the technical problem, CN 207550499U provides an electric unmanned aerial vehicle, which comprises a vehicle body, two landing gears, and eight motors connected to the eight motors supported by cantilevers on the vehicle body, wherein a longitudinal load channel is arranged below the vehicle body, and a first group of four cantilevers and a second group of four cantilevers are symmetrically arranged on two sides of the longitudinal load channel respectively. This prior art's electric unmanned aerial vehicle sets up a longitudinal load passageway that does not shelter from through in the fuselage below, can conveniently set up loads such as photoelectricity hanging storehouse and weapon launch canister, and take place to interfere with cantilever and screw when avoiding surveing and the weapon transmission, influence use and combat efficiency, improved unmanned aerial vehicle's range of application. In addition, this prior art has reduced the volume after folding through setting for the overall layout structure of optimization, the low-cost transportation of the unmanned aerial vehicle of being convenient for.
The above prior art effectively overcomes the deficiencies of the prior art, but there is still room for improvement. Especially when the folding volume of unmanned aerial vehicle needs further to dwindle to in quick assembly disassembly, when transporting, current unmanned aerial vehicle's beta structure still has further improved space.
Disclosure of Invention
The technical problem that this application will be solved provides an eight rotor unmanned aerial vehicle to reduce or avoid the aforementioned problem.
For solving above-mentioned technical problem, the application provides an eight rotor unmanned aerial vehicle, including fuselage, undercarriage and the cantilever system who supports the motor, every motor all has the screw, the cantilever system includes four main arms of being connected with the fuselage, and the terminal of every main arm is outwards stretched out there are two support arms, and the end-to-end support of every support arm has one the motor that has the screw.
Preferably, each main arm is formed in a star-shaped configuration with a 120-degree interval between two arms connected to the tip end thereof. Preferably, the distances a between the main shafts of the motors of the two adjacent arms on any two adjacent main arms are equal.
Preferably, the distance b between the main shafts of the motors of the two arms on each main arm is equal.
Preferably, the distance a and the distance b are equal.
Preferably, the angular intervals between the four main arms are all 90 degrees.
Preferably, a longitudinal load channel is arranged below the machine body, and the included angles between the central axes of the four main arms and the central axis of the longitudinal load channel are all 45 degrees.
Preferably, a main arm folding mechanism is arranged at the joint of the main arm and the fuselage, the main arm can be folded downwards through the main arm folding mechanism, and the tail end of the folded main arm does not exceed the lowest point of the undercarriage.
Preferably, the two support arms on the main arm are connected with the main arm through a support arm folding mechanism, and the two support arms can be folded towards the direction opposite to the main arm through the support arm folding mechanism.
Preferably, two sides of the longitudinal load channel are respectively and symmetrically provided with an undercarriage, and the undercarriage comprises two vertical rods connected with the machine body and a cross rod arranged at the tail ends of the vertical rods; the main arm may extend in a length direction of the stem after being folded.
The utility model provides an eight rotor unmanned aerial vehicle through two support arms of outwards stretching out at the end of four main arms, has reduced the quantity of main arm, has increaseed the interval between the main arm, has also reduced the length of main arm. The support arm is located the end of main arm, through the angle between reasonable setting support arm and the main arm, can choose for use shorter support arm. Shorter main arm and support arm can obtain littleer structure size, therefore can greatly reduced unmanned aerial vehicle's volume, the unmanned aerial vehicle's of being convenient for quick assembly disassembly and transportation.
Drawings
The drawings are only for purposes of illustrating and explaining the present application and are not to be construed as limiting the scope of the present application. Wherein,
fig. 1 shows a schematic perspective view of an eight-rotor drone according to a specific embodiment of the present application;
figure 2 shows a schematic top view of the eight-rotor drone of figure 1;
fig. 3 shows a schematic view of a folded configuration of an eight-rotor drone according to another particular embodiment of the present application;
fig. 4 shows a schematic view of the folded structure of the cantilever system shown in fig. 3.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present application, embodiments of the present application will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
Just as the background art said, this application is directed against the not enough of the electric unmanned aerial vehicle that discloses in prior art CN 207550499U, has proposed an eight rotor unmanned aerial vehicle who improves structure, can obtain littleer structure size, and unmanned aerial vehicle's folding volume is littleer moreover to quick assembly disassembly and transportation are convenient for.
That is, to achieve the above object, the present application provides an eight-rotor drone, as shown in fig. 1-4, wherein fig. 1 shows a schematic perspective view of an eight-rotor drone according to an embodiment of the present application; figure 2 shows a schematic top view of the eight-rotor drone of figure 1; fig. 3 shows a schematic view of a folded configuration of an eight-rotor drone according to another particular embodiment of the present application; fig. 4 shows a schematic view of the folded structure of the cantilever system shown in fig. 3.
Referring to fig. 1-4, the eight rotor drone of the present application comprises a fuselage 1, two undercarriages 2 and a cantilever system 3 supporting motors 4, each motor 4 carrying a propeller 5. The fuselage 1 is generally elongate and is provided with a longitudinal load channel 6 thereunder, the fuselage 1 being arranged parallel to the longitudinal load channel 6 as shown in dotted lines in figure 1. Set up a vertical load passageway 6 that does not shelter from through the below at eight rotor unmanned aerial vehicle's fuselage 1, be favorable to setting up loads such as photoelectricity hangar and weapon launching tube, take place to interfere with cantilever system 3 and screw 5 etc. when avoiding surveing and the weapon transmission, influence and use and combat efficiency, improved unmanned aerial vehicle's range of application. In addition, due to the arrangement of the longitudinal load channel 6, the cantilever system 3 and the motor 4 and other structures on the cantilever system are distributed on two sides of the machine body 1 on two sides of the longitudinal load channel 6, so that a larger range of load mounting points can be obtained in the longitudinal direction of the machine body, and the load layout is easy to expand.
The difference between this application and the prior art is that eight rotor unmanned aerial vehicle's cantilever system 3 of this application includes four main arms 31 of being connected with fuselage 1, and the terminal of every main arm 31 outwards stretches out has two support arms 32, and the end support of every support arm 32 has a motor 4 that has screw 5.
The unmanned aerial vehicle's of prior art cantilever quantity is the same with rotor quantity, and the waste of structure weight is very big. The interference problem between the adjacent rotor owing to need avoid in prior art, or the quantity that can only reduce the rotor leads to the lift not enough, or can only increase the length of unmanned aerial vehicle's cantilever for obtain sufficient interval between the distal end of adjacent cantilever, the volume that finally leads to unmanned aerial vehicle becomes very big, inconvenient carrying transportation, the volume after folding also hardly reduces.
The eight-rotor unmanned aerial vehicle of the application has the advantages that the number of main arms 31 is reduced by outwards extending the two support arms 32 from the tail ends of the four main arms 31, the interval between the main arms 31 is increased, and the length of the main arms 31 is also reduced. The arm 32 is located at the end of the main arm 31, and by arranging the angle between the arm 32 and the main arm 31 appropriately (as will be described in further detail below), a shorter arm 32 can be used. Shorter main arm 31 and support arm 32 can obtain littleer structure size, therefore can greatly reduced unmanned aerial vehicle's volume, the quick assembly disassembly and the transportation of the unmanned aerial vehicle of being convenient for.
In the illustrated embodiment, as particularly shown by the reference numerals in fig. 2, each main arm 31 is formed with two arms 32 connected at their distal ends in a star configuration at 120-degree intervals. The structure with equal angular intervals is convenient for the uniform distribution of the lifting force structure, is favorable for simplifying the calculation of flight control software, and the control of the unmanned aerial vehicle is simpler and more stable. It will be understood by those skilled in the art that the 120 degree angular separation, strictly speaking, refers to the angle between the central axes of the main arm and the arm.
Further, in one embodiment, it is preferable that the distance a between the main shafts 41 of the motors 4 of the adjacent two arms 32 on any two adjacent main arms 31 is equal. Similarly, the distance b between the main shafts 41 of the motors 4 of the two arms 32 on each main arm 31 is preferably equal. Further preferably, the distance a and the distance b are equal.
The above preferred structural design can obtain an approximately fully symmetrical structure, and the intervals between the rotors 5 on each motor 4 are all equal, so that the size of the cantilever system 3 can be shortened as much as possible, and the volume of the unmanned aerial vehicle can be compressed to the minimum state. Of course, it will be understood by those skilled in the art that the above-mentioned distances a and b can only be approximately equal due to manufacturing and assembling error, there is always a certain difference in theory, it is difficult to make all the distances a equal and all the distances b equal, and considering the problems of handling, the distances a and b can only be kept approximately equal, and the difference between the distances is within 5%.
Further, for further simplifying the manipulation, it is preferable that the angular intervals between the four main arms 31 are all 90 degrees, and of course, the angular interval of 90 degrees refers to the included angle between the central axes of the four main arms. In addition, in order to keep the longitudinal load channel 6 unobstructed, the included angles between the central axes of the four main arms 31 and the central axis of the longitudinal load channel 6 are all 45 degrees, so that the influence of the structural layout of the main arms 31 on the longitudinal load channel 6 is reduced as much as possible, even if the arm 32 at the tail end of the main arm 31 tends to be deviated from the longitudinal load channel 6, and then the interference of the arm 32 on the longitudinal load channel 6 is reduced as much as possible due to the aforementioned structure of the present application, which can greatly reduce the length of the arm 32.
The application provides eight rotor unmanned aerial vehicle's structure for this unmanned aerial vehicle possesses better overall arrangement structure and suitability, and can be better carry out the load setting. In addition, the eight rotor unmanned aerial vehicle that this application provided can be directed against different application scenes, no matter what kind of eight rotor unmanned aerial vehicle of size need, as long as follow this kind of characteristic design of this application, all can be fine with load fit, the operation of being convenient for is used, consequently, this kind of design of this application possesses better commonality.
Further, as shown in fig. 1 to 4, a main arm folding mechanism 11 is disposed at a connection position of a main arm 31 and a fuselage 1 of the eight-rotor unmanned aerial vehicle, the main arm 31 can be folded downward by the main arm folding mechanism 11, and a tail end of the folded main arm 31 does not exceed a lowest point of the landing gear 2. Further, the two arms 32 of the main arm 31 are connected to the main arm 31 by the arm folding mechanism 12, and the two arms 32 can be folded back toward the main arm 31 by the arm folding mechanism 12.
In the design process of the folding structure, the folding space is required to be minimized, and the problem of optimizing the weight of the structure is also required to be considered. For example, in the folding structure of the existing design, the tail end of the cantilever after folding exceeds the lowest point of the undercarriage, so when the box is transported, a waste space exists below the undercarriage, and the structure is not optimal. It is therefore preferred in the present application that the end of main arm 31 does not exceed the lowest point of undercarriage 2, and that undercarriage 2 may be used to provide protection to main arm 31. Two support arms 32 are through reverse folding towards main arm 31 for whole cantilever system 3 has passed through twice folding, and the structure after folding can obtain further reduction, thereby can choose for use shorter undercarriage 2, can further reduce unmanned aerial vehicle's height, improves the stability of unmanned aerial vehicle landing. That is, this application has avoided the unclear problem of various structural parameter correlations entanglement through optimal design's overall arrangement structure, has optimized structural design, has reduced the volume after folding, the unmanned aerial vehicle's of being convenient for low-cost transportation.
Further, as shown in the figure, two sides of the longitudinal load channel 6 are respectively and symmetrically provided with one landing gear 2, and the landing gear 2 comprises two vertical rods 21 connected with the fuselage 1 and a cross rod 22 arranged at the tail ends of the vertical rods 21. The main arm 31 may extend along the length of the vertical bar 21 after being folded. That is, as shown in fig. 3, by setting the extending direction of the folded main arm 31 to be parallel to the vertical rod 21 of the undercarriage 2, the folded cantilever system 3 is conveniently fixed on the vertical rod 21 of the undercarriage 2 by a binding means, and the problem of structural damage due to collision during transportation is reduced.
It should be appreciated by those skilled in the art that while the present application is described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is thus given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including all technical equivalents which are encompassed by the claims and are to be interpreted as combined with each other in a different embodiment so as to cover the scope of the present application.
The above description is only illustrative of the present invention and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations that may be made by those skilled in the art without departing from the spirit and principles of this application shall fall within the scope of this application.
Claims (8)
1. The utility model provides an eight rotor unmanned aerial vehicle, includes cantilever system (3) of fuselage (1), undercarriage (2) and support motor (4), and every motor (4) all has screw (5), its characterized in that: the cantilever system (3) comprises four main arms (31) connected with the machine body (1), the tail end of each main arm (31) extends outwards to form two support arms (32), and the tail end of each support arm (32) is supported with the motor (4) with the propeller (5); each main arm (31) is formed into a star-shaped structure with 120-degree intervals between two arms (32) connected with the tail end of the main arm.
2. An eight-rotor drone according to claim 1, characterised in that the distance a between the main axes (41) of the motors (4) of two adjacent arms (32) on any two adjacent main arms (31) is equal.
3. An eight-rotor drone according to claim 2, characterised in that the distance b between the main axes (41) of the motors (4) of the two arms (32) of each main arm (31) is equal.
4. An eight-rotor drone according to claim 3, wherein said distance a and distance b are equal.
5. An eight-rotor drone according to any one of claims 1 to 4, characterised in that the angular intervals between the four main arms (31) are all 90 degrees.
6. An eight-rotor unmanned aerial vehicle according to claim 5, wherein a longitudinal load channel (6) is provided below the fuselage (1), and the central axes of the four main arms (31) and the central axis of the longitudinal load channel (6) are all at an angle of 45 degrees.
7. An eight-rotor unmanned aerial vehicle according to claim 1, wherein a main arm folding mechanism (11) is provided at the junction of the main arm (31) and the fuselage (1), the main arm (31) can be folded downwards by the main arm folding mechanism (11), and the end of the main arm (31) after folding does not exceed the lowest point of the landing gear (2).
8. An eight-rotor drone according to claim 7, characterised in that the two arms (32) of the main arm (31) are connected to the main arm (31) by means of arm folding means (12), said two arms (32) being able to be folded back towards said main arm (31) by means of said arm folding means (12).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922165467.2U CN211196627U (en) | 2019-12-06 | 2019-12-06 | Eight-rotor unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201922165467.2U CN211196627U (en) | 2019-12-06 | 2019-12-06 | Eight-rotor unmanned aerial vehicle |
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| CN211196627U true CN211196627U (en) | 2020-08-07 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112212881A (en) * | 2020-12-14 | 2021-01-12 | 成都飞航智云科技有限公司 | Flight navigator based on big dipper is used |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112212881A (en) * | 2020-12-14 | 2021-01-12 | 成都飞航智云科技有限公司 | Flight navigator based on big dipper is used |
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