CN215663983U - Multi-rotor unmanned aerial vehicle - Google Patents
Multi-rotor unmanned aerial vehicle Download PDFInfo
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- CN215663983U CN215663983U CN202122446496.3U CN202122446496U CN215663983U CN 215663983 U CN215663983 U CN 215663983U CN 202122446496 U CN202122446496 U CN 202122446496U CN 215663983 U CN215663983 U CN 215663983U
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Abstract
The utility model discloses a multi-rotor unmanned aerial vehicle, which comprises a vehicle body; the rotary shaft of the propeller is inclined relative to the longitudinal axis of the fuselage, and the rotary shafts of the propeller are arranged in parallel relative to the longitudinal axis of the fuselage. By adopting the multi-rotor unmanned aerial vehicle, at least two propellers which are parallel to the longitudinal axis of the vehicle body and are positioned at opposite angles rotate at a constant high rotating speed, so that high usable lift force is ensured in the whole flight process, and the effective load of the multi-rotor unmanned aerial vehicle is improved.
Description
Technical Field
The utility model relates to the technical field of unmanned aerial vehicles, in particular to a multi-rotor unmanned aerial vehicle.
Background
Many rotor unmanned aerial vehicle, because its horizontal plane internal rotation inertia is great, the problem that steering torque is little exists in the positive reverse rotation screw differential mode that small-size many rotor unmanned aerial vehicle adopted. For this part of unmanned aerial vehicle models, the rotating plane of the propeller is inclined, and steering moment in the horizontal plane is generated, however, the scheme also has the problem of influencing the maximum available lift of the unmanned aerial vehicle.
Therefore, how to promote many rotor unmanned aerial vehicle's payload is the technical problem that technical field technical staff letter was waited to solve.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a multi-rotor unmanned aerial vehicle to improve the effective load of the multi-rotor unmanned aerial vehicle.
To achieve the above object, the present invention provides a multi-rotor drone, comprising:
a body;
six arms arranged on the machine body, wherein the tail end of each arm is provided with an engine, each engine drives a propeller to rotate, and the rotating axes of at least two propellers at diagonal positions are obliquely arranged relative to the longitudinal axis of the machine body so that the generated pulling force has component force in the horizontal plane; the axes of rotation of at least two diagonally positioned propellers are arranged parallel with respect to the longitudinal axis of the fuselage.
Preferably, the six arms are two lift arms and four control arms which are arranged on the machine body respectively, the two lift arms are symmetrical relative to the longitudinal section of the machine body, the tail end of each lift arm is provided with a lift engine, each lift engine drives a first propeller, and the rotating axial direction of the first propeller is parallel to the longitudinal axis of the machine body;
the four control arms are symmetrical with respect to the longitudinal section of the fuselage, each control arm having a control motor mounted at its end, one control motor driving a second propeller, the axes of rotation of at least two second propellers located diagonally being arranged obliquely with respect to the longitudinal axis of the fuselage, so that the resulting pulling force has a component in the horizontal plane.
Preferably, the inclination directions of the four control engines are the same, wherein two control engines are inclined to the first side of the body, and the control engines are inclined to the second side of the body, and the inclination directions of the two control engines at the diagonal positions are the same.
Preferably, the lift engine is a powerful engine to boost the maximum load of the drone.
Preferably, the lift engine is of the same construction as the control engine.
Preferably, the lift engine is mounted with the first propeller by mounting a speed reducer.
Preferably, the first end of the horn is removably disposed on the fuselage and/or the engine is removably disposed on the second end of the horn.
Preferably, the horn is of an integral or split construction.
Preferably, a reinforcing link is provided between adjacent horn.
By adopting the multi-rotor unmanned aerial vehicle, the rotating axes of at least two propellers at diagonal positions are obliquely arranged relative to the longitudinal axis of the vehicle body, so that the generated pulling force has component force in a horizontal plane; the axes of rotation of at least two diagonally positioned propellers are arranged parallel with respect to the longitudinal axis of the fuselage. When unmanned aerial vehicle flies, the screw that is in diagonal position with the parallel at least two branches of longitudinal axis of fuselage rotates with invariable great rotational speed, ensures that the whole journey of flight all has great available lift, has promoted many rotor unmanned aerial vehicle's effective load.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings 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 embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic perspective view of a multi-rotor drone according to an embodiment of the present invention;
fig. 2 is a schematic perspective view of a multi-rotor drone according to an embodiment of the present invention;
fig. 3 is a schematic front view of a multi-rotor drone provided in an embodiment of the present invention when deployed.
Wherein: 100 is a fuselage, 201 is a first lift arm, 202 is a second lift arm, 301 is a first control arm, 302 is a second control arm, 303 is a third control arm, and 304 is a fourth control arm; reference numeral 401 denotes a first lift engine, 402 denotes a second lift engine, 501 denotes a first control engine, 502 denotes a second control engine, 503 denotes a third control engine, 504 denotes a fourth control engine, 601 denotes a first propeller, and 602 denotes a second propeller.
Detailed Description
The core of the utility model is to provide the multi-rotor unmanned aerial vehicle so as to improve the effective load of the multi-rotor unmanned aerial vehicle.
In order to make the technical solutions of the present invention better understood by those skilled in the art, the present invention will be further described in detail with reference to the accompanying drawings and embodiments.
Referring to fig. 1 to 3, the present invention discloses a multi-rotor drone, including: the device comprises a machine body and six machine arms arranged on the machine body, wherein each machine arm is provided with an engine, each engine drives a propeller to rotate, and the rotating axes of at least two propellers at diagonal positions are obliquely arranged relative to the longitudinal axis of the machine body so that the generated pulling force has component force in a horizontal plane; the axes of rotation of at least two diagonally positioned propellers are arranged parallel with respect to the longitudinal axis of the fuselage. When unmanned aerial vehicle flies, the screw that is in diagonal position with the parallel at least two branches of longitudinal axis of fuselage rotates with invariable great rotational speed, ensures that the whole journey of flight all has great available lift, has promoted many rotor unmanned aerial vehicle's effective load.
The six arms are two lifting force arms and four control arms respectively, wherein the two lifting force arms are arranged on the machine body and are symmetrical relative to the longitudinal section of the machine body, the tail end of each lifting force arm is provided with a lifting force engine, each lifting force engine drives a first propeller 601, and the rotating axial direction of the first propeller 601 is parallel to the longitudinal axis of the machine body; four control arms are arranged on the fuselage, the four control arms being symmetrical with respect to the longitudinal section of the fuselage, a control motor being mounted at the end of each control arm, one control motor driving a second propeller 602, the axis of rotation of at least two diagonally positioned second propellers 602 being arranged obliquely with respect to the longitudinal axis of the fuselage, so that the resulting pulling force has a component in the horizontal plane.
By adopting the multi-rotor unmanned aerial vehicle, the two lift arms are symmetrical relative to the longitudinal section of the vehicle body, and the rotating axial direction of the propeller of the multi-rotor unmanned aerial vehicle is parallel to the longitudinal axis of the vehicle body. When unmanned aerial vehicle flies, the lift engine rotates with invariable great rotational speed, ensures that the whole journey of flight all has great available lift, has promoted many rotor unmanned aerial vehicle's effective load.
It should be noted that, the four corners of the body 100 are respectively a first corner, a second corner, a third corner and a fourth corner, in the diagram, the center line O1O2 of the body 100 is used as a boundary, the four corners respectively correspond to the first corner and the second corner, the third corner and the fourth corner, the fourth corner and the fourth corner are arranged oppositely, and the second corner and the third corner are arranged oppositely. A right or left first side of the body 100 and a left or right second side of the body 100.
Furthermore, the four control engines are inclined in the same direction, wherein the two control engines are inclined towards the first side of the machine body, the two control engines are inclined towards the second side of the machine body, and the two control engines in the opposite angle positions are inclined in the same direction. Improve to turn to the flexibility with increase unmanned aerial vehicle's steering torque.
In the utility model, the lift force engine is a high-power engine so as to improve the maximum load of the unmanned aerial vehicle.
Preferably, the lift engine is of the same construction as the control engine. And additionally installing a speed reducer and a larger-sized propeller to improve the maximum available lift.
Preferably, the lift engine is mounted with the first propeller by mounting a speed reducer.
The first end of the lift arm is not detachably arranged on the machine body 100, or the first end of the lift arm is detachably arranged on the machine body 100, and the purpose of connecting the machine body 100 with the lift engine can be achieved within the protection scope of the utility model. Preferably, the first end of the lift arm is detachably mounted to the fuselage 100. Further, the lift engine is not detachably disposed on the fuselage 100, or the lift engine is detachably disposed on the lift arm, so long as the connection form that the lift engine is mounted on the lift arm is realized, is within the scope of the present invention.
Specifically, the lift engine comprises a first lift engine 401 and a second lift engine 402, the lift arms comprise a first lift arm 201 and a second lift arm 202, wherein a first end of the first lift arm 201 and a first end of the second lift arm 202 are symmetrically arranged on two sides of the fuselage 100, the first lift engine 401 is arranged on the first lift arm 201, the second lift engine 402 is arranged on the second lift arm 202, and the first lift engine 401 and the second lift engine 402 are symmetrical about a center line O1O2 of the fuselage 100. The first lift engine 401 drives the first propeller 601 to rotate through a first speed reducer, and the second lift engine 402 drives the first propeller 602 to rotate through a second speed reducer.
The lift arm is of an integrated structure or a split structure, wherein in the split structure, the lift arm is of a telescopic structure or a folding structure. The lift horn is through flexible or folding in order to reduce many rotor unmanned aerial vehicle's occupation volume.
The lift engine of the utility model drives the propeller to rotate through the reducer, and the reducer is driven by a conventional reducer, so long as the purpose of speed reduction can be realized, and the utility model is within the protection scope of the utility model. The first propeller 601 is driven by the first lift engine 401 through the first speed reducer to rotate, in this embodiment, the first speed reducer 301 can realize one-stage speed reduction, but the first speed reducer 301 can also realize two-stage speed reduction, three-stage speed reduction and four-stage speed reduction, and in this example, the one-stage speed reduction is taken as an example for description.
The first end of control horn is undetachable and sets up on fuselage 100, perhaps the first end detachable of control horn sets up on fuselage 100, and wherein, detachable setting mode is bolted connection, staple bolt connection etc.. Similarly, the control engine is arranged at the second end of the control machine arm in a non-detachable mode, or the control engine is arranged at the second end of the control machine arm in a detachable mode. Wherein, detachable setting mode is bolted connection, and the staple bolt is connected the connection mode that can dismantle such as, and the replacement is carried out when convenient arbitrary one takes place to damage.
For convenience of description, the control engines include a first control engine 501, a second control engine 502, a third control engine 503, and a fourth control engine 504; the control arm comprises a first control arm 301, a second control arm 302, a third control arm 303 and a fourth control arm 304; wherein, the first end of the first control horn 301 is arranged at the first corner of the fuselage 100, and the first control engine 501 is arranged at the second end of the first control horn 301; a first end of the second control horn 302 is disposed at a second corner of the fuselage 100 and a second control motor 502 is disposed at a second end of the second control horn 302; a first end of a third control arm 303 is provided at a third corner of the body 100, and a third control motor 503 is provided at a second end of the third control arm 303; a first end of the fourth control arm 304 is disposed at a fourth corner of the body 100, and a fourth control motor 504 is disposed at a second end of the fourth control arm 304. Since the first corner is disposed opposite the fourth corner and the second corner is disposed opposite the third corner, the first control arm 301 is disposed diagonally to the fourth control arm 304, and the second control arm 302 is disposed diagonally to the third control arm 303.
In order to improve the connection strength between the control and lift arms and the fuselage 100, a reinforcing link 700 is provided between adjacent control and lift arms and/or between adjacent control and fuselage 100 and/or between lift arms and fuselage 100.
From the above description it can be seen that the lift arm comprises a first lift arm 201 and a second lift arm 202, the first control arm 301 comprises a first control arm 301, a second control arm 302, a third control arm 303 and a fourth control arm 304, the first lift arm 201 is located between the first control arm 301 and the second control arm 302, the second lift arm 202 is located between the third control arm 303 and the fourth control arm 304, such that the first lift arm 201 is adjacent to the first control arm 301 and the second control arm 302, the second lift arm 202 is adjacent to the third control arm 303 and the fourth control arm 304, the first control arm 301 is adjacent to the first lift arm 201 and the third control arm 303, the second control arm 302 is adjacent to the first lift arm 201 and the fourth control arm 304, the third control arm 303 is adjacent to the first control arm 301 and the second lift arm 202, the fourth control arm 304 is adjacent to the second control arm 302 and the second lift arm 202, and therefore the reinforcing links are provided between the first control arm 301 and the first lift arm 201, between the first lift arm 201 and the second control arm 302, between the second control arm 302 and the fourth control arm 304, between the first control arm 301 and the third control arm 303, between the first control arm 301 and the second lift arm 202, and between the second lift arm 202 and the fourth control arm 304, respectively.
Finally, it should also be 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. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
Those of skill would further appreciate that the various illustrative elements and algorithm steps described in connection with the embodiments disclosed herein may be implemented as electronic hardware, computer software, or combinations of both, and that the various illustrative components and steps have been described above generally in terms of their functionality in order to clearly illustrate this interchangeability of hardware and software. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the implementation. Skilled artisans may implement the described functionality in varying ways for each particular application, but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.
The steps of a method or algorithm described in connection with the embodiments disclosed herein may be embodied directly in hardware, in a software module executed by a processor, or in a combination of the two. A software module may reside in Random Access Memory (RAM), memory, Read Only Memory (ROM), electrically programmable ROM, electrically erasable programmable ROM, registers, hard disk, a removable disk, a CD-ROM, or any other form of storage medium known in the art.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the utility model. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. A multi-rotor unmanned aerial vehicle, comprising:
a body;
six arms arranged on the machine body, wherein the tail end of each arm is provided with an engine, each engine drives a propeller to rotate, and the rotating axes of at least two propellers in diagonal positions are obliquely arranged relative to the longitudinal axis of the machine body so that the generated pulling force has component force in a horizontal plane; the axes of rotation of at least two diagonally positioned propellers are arranged parallel with respect to the longitudinal axis of the fuselage.
2. The multi-rotor unmanned aerial vehicle of claim 1, wherein the six arms are two lift arms and four control arms, respectively, the two lift arms are symmetrical with respect to a longitudinal section of the fuselage, a lift engine is mounted at a distal end of each lift arm, each lift engine drives a first propeller, and an axial direction of rotation of the first propeller is parallel to a longitudinal axis of the fuselage;
the four control arms are symmetrical relative to the longitudinal section of the fuselage, the tail end of each control arm is provided with a control engine, one control engine drives a second propeller, and the rotating axes of at least two second propellers at diagonal positions are obliquely arranged relative to the longitudinal axis of the fuselage, so that the generated pulling force has component force in the horizontal plane.
3. A multi-rotor drone according to claim 2, wherein four of said control engines are arranged in an inclined manner.
4. A multi-rotor drone according to claim 3, wherein two of said control engines are inclined to a first side of said fuselage, two of said control engines are inclined to a second side of said fuselage, and the inclination of two of said control engines in diagonal positions is the same.
5. A multi-rotor drone according to claim 2, wherein the lift engine is a powerful engine to lift the maximum load of the drone.
6. A multi-rotor drone according to claim 2, wherein the lift engine is structurally identical to the control engine.
7. A multi-rotor drone according to claim 2, wherein the lift engine mounts the first propeller by mounting a speed reducer.
8. A multi-rotor drone according to claim 1, wherein the first end of the horn is removably disposed on the fuselage and/or the engine is removably disposed at the second end of the horn.
9. The multi-rotor drone of claim 1, wherein the horn is a unitary or split structure.
10. A multi-rotor drone according to claim 2, wherein a reinforcing link is provided between adjacent said arms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122446496.3U CN215663983U (en) | 2021-10-11 | 2021-10-11 | Multi-rotor unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122446496.3U CN215663983U (en) | 2021-10-11 | 2021-10-11 | Multi-rotor unmanned aerial vehicle |
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| CN215663983U true CN215663983U (en) | 2022-01-28 |
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| CN202122446496.3U Active CN215663983U (en) | 2021-10-11 | 2021-10-11 | Multi-rotor unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023182127A1 (en) * | 2022-03-23 | 2023-09-28 | 株式会社石川エナジーリサーチ | Flying apparatus |
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- 2021-10-11 CN CN202122446496.3U patent/CN215663983U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2023182127A1 (en) * | 2022-03-23 | 2023-09-28 | 株式会社石川エナジーリサーチ | Flying apparatus |
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