Rotor wing assembly and unmanned aerial vehicle

Abstract

The invention relates to a rotor assembly and an unmanned aerial vehicle, the rotor assembly comprises a propeller and a driving part used for driving the propeller to rotate, the propeller is installed on an output shaft of the driving part through a propeller clamp assembly, a guiding gap is formed between the propeller clamp assembly and a shell of the driving part, and the propeller clamp assembly is installed on the driving part. And a cutting piece is arranged in the guide gap and is used for cutting off the wire articles wound in the guide gap. In the rotor assembly provided by the invention, the guide gap is formed between the paddle clamp assembly and the shell of the driving part, and wound wire articles can be stabilized at the guide gap and are cut off by the cutting part at the guide gap, so that an anti-winding function is realized, the problem of explosion of an unmanned aerial vehicle caused by winding of the wire articles is effectively solved, and the service life of the unmanned aerial vehicle is prolonged. And the flight safety of the unmanned aerial vehicle is improved.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the technical field of unmanned aerial vehicles, in particular, to a rotor assembly and an unmanned aerial vehicle. BACKGROUND

[0002] During flight, the unmanned aerial vehicle usually uses the internal sensors to identify and avoid the kite line and other objects, so as to prevent the line from winding around the unmanned aerial vehicle and causing the unmanned aerial vehicle to explode. However, the kite line is usually thin and semi-transparent, and the sensor may not be able to identify it, so it is not possible to effectively avoid the winding of the line and cause the unmanned aerial vehicle to explode. SUMMARY

[0003] The purpose of the present disclosure is to provide a rotor assembly and an unmanned aerial vehicle, which can effectively solve the problem of winding line objects causing the unmanned aerial vehicle to explode.

[0004] In order to achieve the above-mentioned purpose, the present disclosure provides a rotor assembly, which comprises a propeller and a driving member for driving the propeller to rotate, the propeller is installed on the output shaft of the driving member through a propeller clamp assembly, wherein a guide gap is provided between the propeller clamp assembly and the housing of the driving member, and a cutting member is provided in the guide gap, the cutting member is used to cut the line object wound in the guide gap.

[0005] Optionally, the propeller clamp assembly comprises an upper propeller clamp and a lower propeller clamp, the center of the propeller is clamped between the upper propeller clamp and the lower propeller clamp, the lower propeller clamp and the housing are arranged in a spaced manner and form the guide gap, and the cutting member is installed on the surface of the lower propeller clamp facing the housing.

[0006] Optionally, the lower propeller clamp comprises a body portion and a protruding portion provided on the surface of the body portion facing the housing, the projection of the body portion in the axial direction covers the projection of the protruding portion in the axial direction, and the line object is wound on the protruding portion.

[0007] Optionally, a slot is provided on the outer peripheral wall of the protruding portion, and the cutting member is detachably installed at the slot through a fastener.

[0008] Optionally, the cutting member has a fixed end for installation on the protruding portion and a cutting end away from the fixed end, the cutting end extends out of the slot, and the projection of the body portion in the axial direction covers the projection of the cutting end in the axial direction.

[0009] Optionally, the outer peripheral wall of the protruding portion has a first side wall and a second side wall which are at an included angle, and the bottom surface of the body portion, the first side wall and the second side wall together form the slot, the cutting member is a blade which is installed on the first side wall in a fitted manner, and the blade extends beyond the first side wall.

[0010] Optionally, the blade edge of the blade is an arc-shaped blade edge with gradually decreasing thickness from inside to outside in the radial direction.

[0011] Optionally, a connection between the first side wall and the second side wall is provided with an avoiding groove extending in the axial direction, and the side edge of the cutting member is located in the avoiding groove, and / or, The bottom surface of the body part is provided with a limiting groove, and the upper edge of the cutting member is located in the limiting groove.

[0012] Optionally, the propeller includes a plurality of blades arranged radially relative to the center, and the circumferential direction of the protruding part is provided with a plurality of spaced-apart grooves, and each of the grooves is provided with the cutting member.

[0013] Optionally, the driving member is a motor, the housing includes a motor base, a motor stator shell and a motor rotor shell coaxially installed on the motor base, and the motor rotor shell and the paddle clamp assembly form the guide gap.

[0014] According to a second aspect of the present disclosure, a UAV is provided, including an arm and the above-mentioned rotor assembly installed on the arm.

[0015] Through the above technical solution, in the rotor assembly provided by the present disclosure, the guide gap is formed between the paddle clamp assembly and the housing of the driving member, and the wound line-like object can be stably located at the guide gap and cut off by the cutting member at the guide gap, thereby realizing the anti-winding function, effectively eliminating the problem of UAV explosion caused by winding line-like objects, and improving the safety of UAV flight.

[0016] Other features and advantages of the present disclosure will be described in detail in the following specific embodiments. BRIEF DESCRIPTION OF DRAWINGS

[0017] The accompanying drawings are included to provide a further understanding of the present disclosure and constitute a part of the specification, and are used together with the following specific embodiments to explain the present disclosure, but do not constitute a limitation on the present disclosure. In the drawings: Figure 1 is a structural schematic diagram of a UAV arm provided by an exemplary embodiment of the present disclosure.

[0018] Figure 2 is a structural schematic diagram of a UAV propeller provided by an exemplary embodiment of the present disclosure.

[0019] Figure 3 and Figure 4 is a partial enlarged view of the installation position of the UAV propeller provided by an exemplary embodiment of the present disclosure.

[0020] Figure 5 and Figure 6Figure 1 is a structural schematic diagram of a propeller clamp assembly of a UAV provided by an example embodiment of the present disclosure.

[0021] Legend of reference signs 1 - arm; 10 - guide gap; 2 - propeller; 20 - propeller blade; 3 - driving member; 30 - housing; 301 - motor base; 302 - motor stator housing; 303 - motor rotor housing; 4 - cutting member; 40 - cutting edge; 5 - propeller clamp assembly; 51 - upper propeller clamp; 52 - lower propeller clamp; 521 - body part; 522 - protruding part; 523 - slot; 524 - limiting slot; 525 - avoiding slot; 6 - fastener. DETAILED DESCRIPTION

[0022] The detailed description of the present disclosure is described below in conjunction with the accompanying drawings. It should be understood that the detailed description described herein is only used to illustrate and explain the present disclosure, and is not used to limit the present disclosure.

[0023] It should be noted that all actions of obtaining signals, information or data in the present disclosure are carried out in compliance with the corresponding data protection regulations and policies of the country where the device is located, and with the authorization given by the owner of the corresponding device.

[0024] In the present disclosure, unless otherwise stated, the orientation words such as "upper" and "lower" generally refer to the definition in the normal installation of the UAV provided by the present disclosure, "axial" and "radial" refer to the definition relative to the rotation axis of the propeller, and "inner" and "outer" refer to the inner and outer of the profile of the corresponding components. In addition, when the following description refers to the drawings, the same numbers in different drawings represent the same or similar elements, unless otherwise indicated.

[0025] The present disclosure provides a rotor assembly, as shown in Figure 1 and Figure 2 The rotor assembly includes a propeller 2 and a driving member 3 for driving the propeller 2 to rotate, the propeller 2 is installed on the output shaft of the driving member 3 through a propeller clamp assembly 5, wherein a guide gap 10 is provided between the propeller clamp assembly 5 and the housing 30 of the driving member 3, and a cutting member 4 is provided in the guide gap 10, the cutting member 4 is used to cut the line-like object wound at the guide gap 10. The rotor assembly can be applied to UAVs, aircrafts and the like. When a line-like object such as a kite string cannot be avoided during flight, the rotating propeller 2 can wind the line-like object at the guide gap 10 and cut the line-like object through the cutting member 4.

[0026] The propeller clamp assembly 5 is used to install the propeller 2 on the output shaft of the driving member 3, so as to ensure that the propeller 2 is safely and stably connected to the power system of the UAV. In an example embodiment provided by the present disclosure, as shown in Figure 3As shown, the paddle clamp assembly 5 includes an upper paddle clamp 51 and a lower paddle clamp 52, and the center of the propeller 2 is clamped between the upper paddle clamp 51 and the lower paddle clamp 52. The driving member 3 can be a motor, and the housing 30 includes a motor base 301, a motor stator shell 302 coaxially installed on the motor base 301, and a motor rotor shell 303 coaxially installed on the motor stator shell 302. The lower paddle clamp 52 and the top surface of the motor rotor shell 303 are arranged in a spaced manner and form a guide gap 10. The cutting member 4 can be a cutter, and the cutting edge of the cutter can be arranged outward to cut the line-like object wound in the guide gap 10. In other embodiments, the paddle clamp assembly 5 can only include the lower paddle clamp 52, and the center of the propeller 2 is fixed to the top surface of the lower paddle clamp 52. The driving member 3 can include a housing 30 and an output shaft extending out of the housing 30, and the guide gap 10 is formed between the lower paddle clamp 52 and the housing 30.

[0027] The line-like object herein can be a kite string, fishing line, engineering line, etc. The line-like object that can be cut off by the cutting member 4 belongs to the protection scope of the present disclosure, and the kite string will be taken as an example for introduction below. Through multiple simulations and tests, the kite string will eventually stabilize at the position of the guide gap 10 after being wound for a period of time, and the principle is similar to that when there is an electric wire between the rotating fan leaves, the electric wire will be wound at the position of the center of the electric fan provided with a motor. When winding a new round of kite string, the previously wound kite string will be tightened and cut off at the position of the cutting member 4, realizing the anti-winding function. The cutting member 4 can be fixed at the guide gap 10, and the cutting action is realized by the force of tightening the kite string acting on the cutting member 4. In other embodiments, the cutting member 4 can also be designed to be radially retractable, and the wound kite string is cut off by the movement in the radial direction.

[0028] In the rotor assembly provided in the present disclosure, the guide gap 10 is formed between the paddle clamp assembly 5 and the housing 30 of the driving member 3, the wound line-like object can be stabilized at the guide gap 10, and is cut off by the cutting member 4 at the guide gap 10, realizing the anti-winding function, effectively eliminating the problem of unmanned aerial vehicle explosion caused by winding line-like objects, and improving the safety of unmanned aerial vehicle flight.

[0029] In the present disclosure, the lower paddle clamp 52 and the top surface of the motor rotor shell 303 are arranged in a spaced manner to form the guide gap 10, and the spacing therebetween can be designed according to the size of the cutting member 4, and the cutting member 4 can be installed on the surface of the lower paddle clamp 52 facing the housing 30. In other embodiments, the cutting member 4 can also be installed on the top surface of the housing 30, which is not limited in the present disclosure.

[0030] As Figure 4As shown, the lower propeller clamp 52 comprises a body part 521 and a protruding part 522 provided on the surface of the body part 521 facing the shell 30, the projection of the body part 521 in the axial direction covers the projection of the protruding part 522 in the axial direction, a guide gap 10 is formed between the body part 521 and the top surface of the shell 30, and the line article is wound on the protruding part 522. The propeller 2 comprises a plurality of blades 20 arranged radially relative to the center, in the embodiment shown in the figure, three blades 20 are provided, and the upper propeller clamp 51 and the lower propeller clamp 52 are respectively provided with a plurality of petal parts corresponding to the number of blades 20, which protrude outward, and the adjacent two petal parts can play a certain guiding role for the line article. During the driving of the driving member 3 to drive the rotation of the propeller 2, the propeller clamp assembly 5 rotates synchronously, and during the rotation process, the kite line can be guided to the area between the adjacent two petal parts, so as to wind the kite line on the protruding part 522.

[0031] As for the number of cutting members 4, it can be no less than the number of blades 20, in this embodiment, the number of cutting members 4 is equal to the number of blades 20, a plurality of slot grooves 523 are arranged on the circumference of the protruding part 522, each slot groove 523 is provided with a cutting member 4, and the cutting member 4 and the blade 20 correspond one by one. In the embodiment shown in the figure, three blades 20 are provided, the protruding part 522 is provided with three slot grooves 523 arranged along the circumference at intervals corresponding to the positions of the three blades 20, and three cutting members 4 are correspondingly provided, which can be designed according to the needs, and the kite line wound on the protruding part 522 can be cut at the same time, so as to ensure smooth cutting and improve the reliability of the anti-winding function of the unmanned aerial vehicle.

[0032] As shown in Figure 5 and Figure 6 , the outer circumferential wall of the protruding part 522 is provided with a slot groove 523, and the cutting member 4 is detachably installed at the slot groove 523 through the fastener 6. The cutting member 4 is installed on the lower propeller clamp 52 in a replaceable manner, and after a long time of use of the cutting member 4, a new and sharp cutting member 4 can be replaced in time to ensure that the kite line can be cut smoothly. In other embodiments, the cutting member 4 can also be installed at the slot groove 523 in a clamping, plugging, threaded connection or other manner.

[0033] As shown in Figure 5 , the cutting member 4 has a fixed end for being installed on the protruding part 522 and a cutting end away from the fixed end, the cutting end protrudes out of the slot groove 523, and the projection of the body part 521 in the axial direction covers the projection of the cutting end in the axial direction. In this way, the cutting end of the cutting member 4 protrudes out of the slot groove 523, ensuring that the cutting action can be completed smoothly, the cutting end does not protrude to the outside of the body part 521 and will not exceed the body part 521, and can be hidden inside the propeller clamp, so as not to cut the user and ensure the safety of the unmanned aerial vehicle.

[0034] The slot groove 523 can have various forms, and in this disclosure, as shown inFigure 6 As shown, the outer peripheral wall of the protruding portion 522 has a first side wall and a second side wall that are at an included angle, and the bottom surface, the first side wall and the second side wall of the body portion 521 jointly enclose the slot 523, the cutting member 4 can be a blade that is mounted in abutment on the first side wall, the blade extends beyond the first side wall, in the embodiment shown in the figure, by being mounted in abutment with the first side wall, the contact area with the first side wall can be increased, the reliability and stability of the connection between the two can be ensured, at the same time, the width direction of the cutting edge is the axial direction, the multiple turns of the kite line that are wound in the circumferential direction can be simultaneously cut, the blade does not need to be designed to be very thick, and is more compact and convenient. In other embodiments, the cutting member 4 can also be installed in a horizontal manner, at this time, the thickness of the blade can be increased to ensure the cutting action on the wound kite line, the above-mentioned embodiments all belong to the protection range of the present disclosure.

[0035] As shown in the figure, Figure 6 The connection between the first side wall and the second side wall is provided with an avoidance slot 525 that extends in the axial direction, the side edge of the cutting member 4 is located in the avoidance slot 525, and the bottom surface of the body portion 521 is provided with a limiting slot 524, and the upper edge of the cutting member 4 is located in the limiting slot 524. By designing the structure of the slot 523, the cutting member 4 can be stably and reliably mounted on the lower paddle clamp 52, the avoidance slot 525 and the limiting slot 524 can play a certain pre-positioning role on the cutting member 4, and the operation difficulty is reduced when the fastener 6 is installed. In other embodiments, the slot 523 can be a plug-in slot that is open only at the outer end, and one end of the cutting member 4 is inserted into the plug-in slot.

[0036] The cutting edge of the blade can be an arc-shaped cutting edge with a thickness that gradually decreases from the inside to the outside in the radial direction, in this way, the cutting end of the blade is more sharp, by designing the structure of the blade, the arc-shaped blade can quickly cut the kite line that is wound on the protruding portion 522. In other embodiments, the cutting member 4 can also be scissors and the like.

[0037] In the rotor assembly provided in the present disclosure, by designing the paddle clamp assembly 5 and the paddle 20, the wound kite line is stably positioned at the position of the guide gap 10, by arranging multiple cutting members 4 in the circumferential direction of the lower paddle clamp 52, the multiple cutting members 4 are respectively stably and reliably mounted at the corresponding slots 523, the kite line that is wound on the protruding portion 522 can be timely cut, the anti-winding function is realized, and the phenomenon of a drone blowing up a drone is avoided. At the same time, the multiple cutting members 4 are hidden inside the lower paddle clamp 52 and the housing 30 at the positions of the slots 523, do not extend out of the guide gap 10, and do not cut the user, and are more safe and reliable.

[0038] According to a second aspect of the present disclosure, a UAV is provided, which comprises an arm 1 and a rotor assembly mounted on the arm 1, the rotor assembly being the rotor assembly as described above, and has all the beneficial effects of the rotor assembly described above, which will not be repeated here.

[0039] The preferred embodiments of the present disclosure are described in detail above with reference to the drawings, but the present disclosure is not limited to the specific details of the above-described embodiments. Various simple modifications can be made to the technical solutions of the present disclosure within the technical concept of the present disclosure, and all these simple modifications shall fall within the protection scope of the present disclosure.

[0040] In addition, it should be noted that each specific technical feature described in the above specific embodiments can be combined in any appropriate manner without contradiction. In order to avoid unnecessary repetition, the present disclosure will not further describe various possible combinations.

[0041] In addition, various different embodiments of the present disclosure can also be combined in any appropriate manner, as long as they do not deviate from the idea of the present disclosure, and they should also be considered as disclosed by the present disclosure.

Claims

1. A rotor assembly, characterized in that, The device includes a propeller and a drive unit for driving the propeller to rotate. The propeller is mounted on the output shaft of the drive unit via a propeller clamp assembly. A guide gap is provided between the propeller clamp assembly and the housing of the drive unit. A cutting element is provided within the guide gap for cutting thread-like items wrapped around the guide gap.

2. The rotor assembly according to claim 1, characterized in that, The propeller clamp assembly includes an upper propeller clamp and a lower propeller clamp, with the center of the propeller clamped between the upper propeller clamp and the lower propeller clamp. The lower propeller clamp and the housing are spaced apart to form the guide gap, and the cutter is mounted on the surface of the lower propeller clamp facing the housing.

3. The rotor assembly according to claim 2, characterized in that, The lower propeller clamp includes a body portion and a protrusion on the surface of the body portion facing the housing. The axial projection of the body portion covers the axial projection of the protrusion, and the thread-like article is wound around the protrusion.

4. The rotor assembly according to claim 3, characterized in that, The outer peripheral wall of the protrusion is provided with a slot, and the cutting element is detachably installed at the slot by fasteners.

5. The rotor assembly according to claim 4, characterized in that, The cutting element has a fixed end for mounting on the protrusion and a cutting end away from the fixed end, the cutting end extending out of the slot and the axial projection of the body portion covering the axial projection of the cutting end.

6. The rotor assembly according to claim 5, characterized in that, The outer peripheral wall of the protrusion has a first sidewall and a second sidewall that form an angle with each other. The bottom surface of the main body, the first sidewall, and the second sidewall together form the slot. The cutting element is a blade that is fitted and installed on the first sidewall, and the blade extends beyond the first sidewall.

7. The rotor assembly according to claim 6, characterized in that, The connection between the first sidewall and the second sidewall is provided with an axially extending clearance groove, and the side edge of the cutting piece is located within the clearance groove; and / or, A limiting groove is provided on the bottom surface of the main body, and the upper edge of the cutting component is located within the limiting groove; and / or, The blade has an arc-shaped cutting edge with a thickness that gradually decreases radially from the inside to the outside.

8. The rotor assembly according to any one of claims 4-7, characterized in that, The propeller includes multiple blades arranged radially relative to the center, and the protrusion has multiple slots arranged at intervals around its circumference, with the cutting element installed in each slot.

9. The rotor assembly according to claim 1, characterized in that, The driving component is a motor, and the housing includes a motor mount and a motor stator housing and a motor rotor housing coaxially mounted on the motor mount. The guide gap is formed between the motor rotor housing and the paddle clamp assembly.

10. A drone, characterized in that, include: The arm and the rotor assembly mounted on the arm according to any one of claims 1 to 9.

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