CN220032234U - Unmanned aerial vehicle power assembly and unmanned aerial vehicle - Google Patents

Abstract

The present disclosure relates to an unmanned aerial vehicle power assembly and unmanned aerial vehicle, the power assembly is used for installing on unmanned aerial vehicle's fuselage body, and the power assembly includes: the screw rods are arranged in the machine body and are provided with internal threads; one end of each screw rod is screwed in the corresponding screw rod barrel, and the other end of each screw rod is used for extending out of the machine body; a plurality of rotor assemblies, each rotor assembly being mounted at an end of its corresponding lead screw remote from the lead screw barrel; a plurality of limit mechanisms, each limit mechanism is used for limiting the corresponding screw rod to move only along the axial direction of the screw rod barrel; and a driving mechanism for driving the plurality of screw barrels to rotate about the axis thereof. When the flight angle of the unmanned aerial vehicle needs to be adjusted, the screw rod barrel is driven to rotate, and under the assistance of the limiting mechanism, the screw rod moves along the axial direction, and then the rotor wing assembly positioned at the end part of the screw rod is driven to change the position.

Description

Unmanned aerial vehicle power assembly and unmanned aerial vehicle

Technical Field

The present disclosure relates to the field of unmanned aerial vehicles, and in particular, to an unmanned aerial vehicle power assembly and an unmanned aerial vehicle.

Background

With the development of unmanned aerial vehicle technology, unmanned aerial vehicles are favored by more and more industries. Can be used for light show, aerial photography, pesticide spraying, real-time monitoring and the like. When the unmanned plane performs various works, the flying posture, the flying angle and the like are required to be continuously adjusted according to actual requirements. For example, when unmanned aerial vehicle is used for taking photo by plane and monitoring, it flies in the air, need adjust flight angle in real time according to monitoring environment and wind direction, if flight angle appears the error and can not obtain real-time adjustment, can seriously influence unmanned aerial vehicle's effect of taking photo by plane, can appear the accident even.

In the related art, unmanned aerial vehicle is provided with a plurality of rotor assemblies, when needing adjustment flight angle, through the rotational speed and the rotation direction that change each rotor assembly, and then realizes the adjustment of flight angle. However, since the positions between the individual rotor assemblies are fixed and are spaced farther from each other (larger overall size) in flight, the drone is slow in adjusting the angle of flight, resulting in lower adjustment efficiency. Therefore, there is an urgent need for an unmanned aerial vehicle capable of adjusting the spacing between the rotor assemblies in real time.

Disclosure of Invention

It is an object of the present disclosure to provide an unmanned aerial vehicle power assembly and an unmanned aerial vehicle to at least partially solve the problems in the related art.

To achieve the above object, the present disclosure provides an unmanned aerial vehicle power assembly for mounting on an unmanned aerial vehicle's fuselage body, the power assembly includes: the screw rods are arranged on the machine body and are provided with internal threads; one end of each screw rod is screwed in the corresponding screw rod barrel, and the other end of each screw rod is used for extending out of the machine body; a plurality of rotor assemblies, each rotor assembly being mounted at an end of its corresponding lead screw remote from the lead screw barrel; each limiting mechanism is used for limiting the corresponding screw rod to move only along the axial direction of the screw rod barrel; and a driving mechanism for driving a plurality of the screw barrels to rotate around the axis thereof.

Optionally, each of the limit mechanisms includes: the guide cylinder is used for being arranged inside the machine body; one end of the guide rod extends into the guide cylinder, and the other end of the guide rod is used for extending out of the machine body; and a connecting rod for connecting between a set of guide rods corresponding to the guide rods and the screw rods, wherein the guide cylinders and the screw rods corresponding to the guide cylinders are parallel to each other, and the guide rods can move in the guide cylinders along the axial direction of the guide cylinders.

Optionally, the unmanned aerial vehicle power assembly includes two that the interval set up and are parallel to each other lead screw section of thick bamboo, every lead screw section of thick bamboo corresponds and is provided with one the guide cylinder, wherein, the internal thread at the both ends of lead screw section of thick bamboo revolves to opposite directions, just the both ends of lead screw section of thick bamboo are revolved respectively and are twisted one the lead screw, the both ends of guide cylinder stretch into respectively one the guide bar, corresponding one of same one side lead screw with one the guide bar passes through one the connecting rod is connected.

Optionally, one end of each lead screw far away from the lead screw barrel is provided with a mounting block, one end of the connecting rod is connected with the guide rod, the other end is connected with a corresponding mounting block, and the top of each mounting block is provided with one rotor wing assembly.

Optionally, the mounting block is formed with a threaded hole matched with the screw rod, and one end of the screw rod extending out of the body of the machine body is screwed in the threaded hole.

Optionally, the driving mechanism comprises a motor and a transmission rod connected between the motor and the screw rod barrel in a transmission manner so as to drive the screw rod barrel to rotate around the axis of the screw rod barrel.

Optionally, the driving mechanism further comprises a first gear sleeved on the periphery of the screw rod barrel and a second gear arranged at the end part of the transmission rod, wherein the first gear and the second gear are meshed with each other.

Optionally, the motor is in transmission connection with a position of the transmission rod, which is close to the middle, the axial direction of the transmission rod is perpendicular to the axial direction of the screw rod barrel, and two ends of the transmission rod are respectively in transmission connection with one screw rod barrel, wherein the first gear and the second gear are bevel gears.

Optionally, the transmission rod is rotatably mounted on the body through two first bearings spaced apart from each other, and the screw barrel is rotatably mounted on the body through two second bearings spaced apart from each other.

According to a second aspect of the present disclosure, there is provided an unmanned aerial vehicle, including the unmanned aerial vehicle power assembly and a fuselage body described above, the unmanned aerial vehicle power assembly being fixed on the fuselage body.

Through above-mentioned technical scheme, when need adjust unmanned aerial vehicle's flight angle, actuating mechanism can drive the screw section of thick bamboo rotatory to under stop gear's assistance, make the screw shrink along the axis direction, and then drive the rotor assembly that is located the screw tip and move towards the direction that is close to the fuselage body, thereby reduce unmanned aerial vehicle volume, with the change that can cooperate rotor assembly turn to and the rotational speed, quick efficient realization flight angle's adjustment. After the angle adjustment is completed, the driving mechanism can be driven reversely, so that the screw rod extends outwards along the axial direction, and further the rotor wing assembly positioned at the end part of the screw rod is driven to move towards the direction away from the machine body, and the flying state is restored.

Additional features and advantages of the present disclosure will be set forth in the detailed description which follows.

Drawings

The accompanying drawings are included to provide a further understanding of the disclosure, and are incorporated in and constitute a part of this specification, illustrate the disclosure and together with the description serve to explain, but do not limit the disclosure. In the drawings:

FIG. 1 is a schematic illustration of an exemplary disclosed unmanned power assembly mounted on a fuselage body;

FIG. 2 is an enlarged view of portion A of FIG. 1;

FIG. 3 is an enlarged view of portion B of FIG. 1;

fig. 4 is a schematic diagram of an exemplary drone according to the present disclosure.

Description of the reference numerals

100-a fuselage body; 210-a screw barrel; 220-screw rod; 300-rotor assembly; 400-limiting mechanism; 410-a guide cylinder; 420-a guide rod; 430-connecting rods; 510-an electric motor; 520-drive rod; 531-first gear; 532—a second gear; 600-mounting blocks; 701-a first bearing; 702-a second bearing.

Detailed Description

Specific embodiments of the present disclosure are described in detail below with reference to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating and illustrating the disclosure, are not intended to limit the disclosure.

In the present disclosure, unless otherwise indicated, terms such as "inner" and "outer" may be used based on the structure of the relevant components themselves, or may be used based on the orientation of the relevant components when they are used in combination, for example: the screw rod cylinder is provided with an 'internal' thread, which means that the screw rod cylinder is provided with a thread on the inner wall surface for screwing the screw rod in the screw rod cylinder; the first gear sleeved on the outer periphery of the screw rod cylinder means that the screw rod cylinder extends into the inner ring of the first gear.

In this disclosure, the terms "first," "second," and the like are used to distinguish one element from another without sequence or importance. When the following description refers to the accompanying drawings, the same numbers in different drawings refer to the same or similar elements, unless otherwise indicated.

Referring to fig. 1 to 3, according to a first aspect of the present disclosure, there is provided a power assembly of an unmanned aerial vehicle for mounting on a fuselage body 100 of the unmanned aerial vehicle, the power assembly including a plurality of screw barrels 210 for mounting on the fuselage body 100 and respectively having internal threads, a plurality of screws 220 having one ends screwed into the corresponding screw barrels 210 and the other ends for extending out of the fuselage body 100, a plurality of rotor assemblies 300 mounted at ends of the corresponding screws 220 remote from the screw barrels 210, a plurality of limit mechanisms 400 for limiting movement of the corresponding screws 220 only in an axial direction of the screw barrels 210, and a driving mechanism for driving the plurality of screw barrels 210 to rotate about axes thereof. Here, rotor assembly 300 is referred to as including a rotor body and a mating power generating device for driving the rotor body to rotate.

The present disclosure is not limited as to how the rotor assembly 300 is secured to the end of the lead screw 220, which may be secured by the mounting block 600, for example, as will be described below. In addition, in other embodiments, it may be fixed to the end of the screw 220 by other mounting brackets. Alternatively, it may be directly welded to the end of the screw 220.

The present disclosure does not limit the limit mechanism 400 as long as the limit mechanism 400 can limit the rotation of the screw 220 corresponding thereto about its own axis so that it can only move in the axial direction of the screw barrel 210. Similarly, the present disclosure also does not limit the driving mechanism as long as it can drive the screw barrel 210 to rotate forward or backward about its own axis. The specific structure of the stop mechanism 400 and the drive mechanism will be described in the embodiments below.

The present disclosure is also not limited to the arrangement of the plurality of screw barrels 210, for example, in the embodiment of the present disclosure, the screw barrels 210 may be centrally disposed on the body 100 in parallel with each other, in which case both ends of the screw barrels 210 may be provided with one screw 220, respectively, so that the plurality of rotor assemblies 300 may be symmetrically disposed on both sides of the body 100. In addition, in other embodiments, the plurality of screw barrels 210 may be arranged radially such that the plurality of rotor assemblies 300 encircle the fuselage body 100.

Through using above-mentioned technical scheme, when need adjust unmanned aerial vehicle's flight angle, actuating mechanism can drive screw barrel 210 rotation to under stop gear 400's assistance, make screw 220 shrink along the axis direction, and then drive the rotor assembly 300 that is located screw 220 tip and move towards the direction that is close to fuselage body 100, thereby reduce unmanned aerial vehicle volume, with the change that can cooperate rotor assembly 300 turn to and the rotational speed, quick efficient realization flight angle's adjustment. After the angle adjustment is completed, the driving mechanism can be reversely driven, so that the screw rod 220 extends outwards along the axial direction, and further the rotor assembly 300 positioned at the end part of the screw rod 220 is driven to move towards a direction away from the fuselage body 100, and the flying state is restored.

Referring to fig. 1-3, in an embodiment of the present disclosure, each of the limit mechanisms 400 may include a guide cylinder 410 for mounting inside the body 100; a guide bar 420 having one end extended into the guide cylinder 410 and the other end extended out of the body 100; and a connection rod 430 for connecting between a set of guide bars 420 corresponding thereto and the lead screw 220. Wherein the guide cylinder 410 and the screw cylinder 210 corresponding thereto are parallel to each other, and the guide rod 420 is movable in the guide cylinder 410 in the axial direction of the guide cylinder 410. When the screw shaft 210 rotates around the axis, the screw shaft 220 cannot rotate around the axis thereof under the limit action of the connecting rod 430 and the guide rod 420, and can only reciprocate along the axis direction of the screw shaft 210.

The present disclosure is not limited by the manner in which the connecting rod 430 is connected to the guide rod 420, for example, in some embodiments, both the connecting rod 430 and the guide rod 420 may be integrally formed. Furthermore, in other embodiments, the connecting rod 430 and the guide rod 420 may be welded together.

In an embodiment of the present disclosure, the outer diameter of the guide rod 420 may be smaller than the inner diameter of the guide cylinder 410 to enable the guide rod 420 to extend into the guide cylinder 410 and guide through the inner wall of the guide cylinder 410. In addition, in other embodiments, the guide rod 420 may be configured as a hollow shape, and the inner diameter of the guide rod 420 may be larger than the outer diameter of the guide cylinder 410 (in this case, the guide cylinder 410 may be rod-shaped), so that the guide rod 420 may be sleeved on the outer wall of the guide cylinder 410 and guided by the outer wall of the guide cylinder 410.

Referring to fig. 1, in an embodiment of the present disclosure, the unmanned aerial vehicle power assembly may include two screw barrels 210 disposed at intervals and parallel to each other, and each screw barrel 210 is provided with a guide barrel 410 corresponding thereto. Wherein, the internal threads at both ends of the screw barrel 210 are reversely rotated, and both ends of the screw barrel 210 may be respectively screwed with one screw 220. The guide cylinder 410 may have two ends respectively inserted into a guide bar 420, and a corresponding one of the lead screws 220 and one of the guide bars 420 on the same side may be connected by a connecting rod 430. So designed, one screw barrel 210 is screwed with two screws 220, and one guide barrel 410 is extended into two guide rods 420, so that the number of the guide barrels 410 and the screw barrels 210 can be reduced, and the weight of the unmanned aerial vehicle is further reduced. In addition, by screwing one screw 220 at each end of the screw barrel 210 (the female screw at each end of the screw barrel 210 is rotated in opposite directions), the two screws 220 connected at both ends can be moved in opposite directions in synchronization, i.e., simultaneously extended or simultaneously retracted.

To enable the rotor assembly 300 to be secured to the end of the lead screws 220, referring to the figures, in embodiments of the present disclosure, one end of each lead screw 220 remote from the lead screw barrel 210 may be provided with a mounting block 600. One end of the connection rod 430 is connected to the guide rod 420, and the other end is connected to the corresponding mounting block 600, and the top of each mounting block 600 may be provided with one rotor assembly 300. Here, in an embodiment of the present disclosure, the connection rod 430 may be welded to each other with the mounting block 600. In addition, in other embodiments, the ends of the connecting rod 430 may be fixedly connected to the mounting block 600 by bolts and nuts.

The present disclosure is not limited to the structure of mounting block 600, so long as it can connect the ends of connecting rod 430 and lead screw 220 together and can provide a mounting location for rotor assembly 300. For example, it may be a cube structure as shown in fig. 1.

In an embodiment of the present disclosure, the mounting block 600 may be formed with a screw hole matching the screw 220, and an end of the screw 220 protruding from the body 100 may be screwed into the screw hole. By the design, the mounting block 600 is convenient to detach from the screw rod 220 in the later period, so that the damaged screw rod 220 or the mounting block 600 can be replaced and maintained, and the maintenance cost is reduced. Furthermore, in other embodiments, the ends of the lead screw 220 may also be welded to the mounting block 600.

In order to be able to drive the rotation of the screw barrel 210 about its own axis, referring to fig. 1, in an embodiment of the present disclosure, the drive mechanism may include a motor 510 and a transmission rod 520 drivingly connected between the motor 510 and the screw barrel 210 to drive the screw barrel 210 to rotate about its own axis. When in use, the motor 510 drives the transmission rod 520 to rotate, and the transmission rod 520 can drive the screw rod barrel 210 in transmission connection with the transmission rod to rotate. It should be noted that the present disclosure is not limited to the number and types of motors 510, and each motor 510 may drive a corresponding screw shaft 210. Alternatively, one motor 510 may drive at least two screw barrels 210 simultaneously.

In an embodiment of the present disclosure, the drive rod 520 may be drivingly connected to the output shaft of the motor 510 through a gear set. Alternatively, in other embodiments, the drive rod 520 may be directly coupled to the output shaft of the motor 510 via a coupling.

The present disclosure is not limited to a transmission manner between the transmission rod 520 and the screw shaft 210, and for example, referring to fig. 3, in an embodiment of the present disclosure, the driving mechanism may further include a first gear 531 sleeved on the outer circumference of the screw shaft 210, and a second gear 532 disposed at an end of the transmission rod 520. Wherein the first gear 531 and the second gear 532 are engaged with each other. The torque of the transmission rod 520 can be transmitted to the screw cylinder 210 by providing the first gear 531 and the second gear 532 which are engaged with each other between the transmission rod 520 and the screw cylinder 210. In addition to the transmission through gears, in other embodiments, external threads may be provided on the exterior of the screw barrel 210, and gears may be provided on the ends of the transmission rod 520 to form a worm and gear structure to effect rotation of the screw barrel 210.

Referring to fig. 1, in the embodiment of the present disclosure, a motor 510 may be in driving connection with a position of a driving rod 520 near the middle, an axial direction of the driving rod 520 is perpendicular to an axial direction of the screw shaft 210, and both ends of the driving rod 520 may be in driving connection with one screw shaft 210, respectively. Wherein the first gear 531 and the second gear 532 are bevel gears. So designed, only one motor 510 and one drive rod 520 are required to drive the rotation of the two screw barrels 210. When the screw rods 220 are arranged at the two ends of the screw rod barrel 210, one motor 510 can drive the four rotor assemblies 300 to change positions simultaneously, so that the internal structure is simplified, and the self weight of the unmanned aerial vehicle is reduced. In addition, the transmission mode can ensure that the expansion and contraction of the four rotor assemblies 300 are kept synchronous, and the stability of the unmanned aerial vehicle when the flying posture of the unmanned aerial vehicle is changed is improved.

Referring to fig. 1-3, in an embodiment of the present disclosure, a transmission lever 520 may be used to be rotatably mounted on the body 100 by two first bearings 701 spaced apart from each other. The screw barrel 210 may be adapted to be rotatably mounted to the fuselage body 100 by two second bearings 702 spaced apart from one another. By means of this bearing design, on the one hand, the drive rod 520 and the screw shaft 210 can be supported. On the other hand, it is ensured that both the transmission rod 520 and the screw shaft 210 can rotate around their own axes with less rotation friction than the body 100. The present disclosure is not limited to the kind of the first bearing 701 and the second bearing 702, and may be a ball bearing, a roller bearing, a needle bearing, or the like.

According to a second aspect of the present disclosure, referring to fig. 4, an unmanned aerial vehicle is provided, including the unmanned aerial vehicle power assembly and the fuselage body 100 described above, the unmanned aerial vehicle power assembly is fixed on the fuselage body 100, and since the unmanned aerial vehicle has all the beneficial effects of the unmanned aerial vehicle power assembly described above, the description thereof is omitted here.

The preferred embodiments of the present disclosure have been described in detail above with reference to the accompanying drawings, but the present disclosure is not limited to the specific details of the above embodiments, and various simple modifications may be made to the technical solutions of the present disclosure within the scope of the technical concept of the present disclosure, and all the simple modifications belong to the protection scope of the present disclosure.

In addition, the specific features described in the foregoing embodiments may be combined in any suitable manner, and in order to avoid unnecessary repetition, the present disclosure does not further describe various possible combinations.

Moreover, any combination between the various embodiments of the present disclosure is possible as long as it does not depart from the spirit of the present disclosure, which should also be construed as the disclosure of the present disclosure.

Claims (10)

1. An unmanned aerial vehicle power assembly for install on unmanned aerial vehicle's fuselage body, its characterized in that, power assembly includes:

the screw rods are arranged on the machine body and are provided with internal threads;

one end of each screw rod is screwed in the corresponding screw rod barrel, and the other end of each screw rod is used for extending out of the machine body;

a plurality of rotor assemblies, each rotor assembly being mounted at an end of its corresponding lead screw remote from the lead screw barrel;

each limiting mechanism is used for limiting the corresponding screw rod to move only along the axial direction of the screw rod barrel; and

and the driving mechanism is used for driving a plurality of screw barrels to rotate around the axis of the screw barrels.

2. The unmanned aerial vehicle power assembly of claim 1, wherein each of the limit mechanisms comprises:

the guide cylinder is used for being arranged inside the machine body;

one end of the guide rod extends into the guide cylinder, and the other end of the guide rod is used for extending out of the machine body; and

a connecting rod for connecting between a group of guide rods corresponding to the connecting rod and the screw rod,

the guide cylinder and the corresponding screw cylinder are parallel to each other, and the guide rod can move in the guide cylinder along the axial direction of the guide cylinder.

3. The unmanned aerial vehicle power assembly of claim 2, wherein the unmanned aerial vehicle power assembly comprises two screw barrels which are arranged at intervals and are parallel to each other, each screw barrel is correspondingly provided with one guide barrel, wherein internal threads at two ends of the screw barrels are oppositely screwed, two ends of the screw barrels are respectively screwed with one screw, two ends of the guide barrels are respectively extended into one guide rod, and one corresponding screw and one guide rod at the same side are connected through one connecting rod.

4. The unmanned aerial vehicle power assembly of claim 2, wherein one end of each screw far away from the screw barrel is provided with a mounting block, one end of the connecting rod is connected with the guide rod, the other end is connected with the corresponding mounting block, and the top of each mounting block is provided with one rotor assembly.

5. The unmanned aerial vehicle power assembly of claim 4, wherein the mounting block has a threaded bore formed therein that mates with the lead screw, an end of the lead screw that extends out of the fuselage body being threaded into the threaded bore.

6. The unmanned aerial vehicle power assembly of any of claims 1-5, wherein the drive mechanism comprises a motor and a drive link drivingly connected between the motor and the lead screw barrel to drive the lead screw barrel to rotate about its own axis.

7. The unmanned aerial vehicle power assembly of claim 6, wherein the drive mechanism further comprises a first gear sleeved on the periphery of the screw barrel and a second gear disposed at the end of the drive rod, wherein the first gear and the second gear are intermeshed.

8. The unmanned aerial vehicle power assembly of claim 7, wherein the motor is in driving connection with a position of the transmission rod near the middle, the axial direction of the transmission rod is perpendicular to the axial direction of the screw barrel, and two ends of the transmission rod are respectively in driving connection with one screw barrel, wherein the first gear and the second gear are bevel gears.

9. The unmanned aerial vehicle power assembly of claim 6, wherein the drive link is for rotational mounting on the fuselage body via two first bearings spaced apart from each other, and the screw barrel is for rotational mounting on the fuselage body via two second bearings spaced apart from each other.

10. An unmanned aerial vehicle comprising the unmanned aerial vehicle power assembly of any of claims 1-9 and a fuselage body, the unmanned aerial vehicle power assembly being secured to the fuselage body.