WO2017206070A1 - Airframe of unmanned aerial vehicle and unmanned aerial vehicle - Google Patents

Abstract

Disclosed are an airframe of an unmanned aerial vehicle and an unmanned aerial vehicle (100, 200, 300) comprising a body (10, 10', 10") and an arm (20, 20', 20") connected to the body (10, 10', 10"). The arm (20, 20', 20") is provided with a mounting portion (202) for mounting a power assembly (40, 40'). The airframe of the unmanned aerial vehicle further comprises a shock isolating member (30, 30', 30"). The shock isolating member (30, 30', 30") is provided on the arm (20, 20', 20") and located between the mounting portion (202) and the body (10, 10', 10") to isolate the shock of the power assembly (40, 40').

Description

Unmanned aerial vehicle racks and unmanned aerial vehicles Technical field

The present invention relates to the field of aircraft, and more particularly to a frame of an unmanned aerial vehicle and an unmanned aerial vehicle.

Background technique

Today, unmanned aerial vehicles have been widely used in aerial photography, surveillance, exploration, rescue, agricultural plant protection and other fields. In order to perform the mission and the need for its own flight, the unmanned aerial vehicle is usually equipped with a certain number of functional modules, such as a sensor, an inertial measurement unit (IMU), a flight control module, a shooting unit, and the like. However, existing unmanned aerial vehicles, especially multi-rotor UAVs, generate vibrations due to the operation of their power units (such as rotors), which in turn affects the functional modules, causing the functional modules to fail to function properly or even be damaged. .

Summary of the invention

In view of this, it is necessary to provide a rack of unmanned aerial vehicles and an unmanned aerial vehicle that avoid the above problems.

A frame of an unmanned aerial vehicle includes a fuselage and an arm coupled to the fuselage. The arm is provided with a mounting portion for mounting a power assembly. The frame of the UAV further includes a vibration isolating member disposed on the arm and located between the mounting portion and the fuselage to block vibration of the power assembly.

An unmanned aerial vehicle includes a frame and a power assembly. The frame includes a body and an arm coupled to the body. The arm is provided with a mounting portion for the mounting power assembly. The frame of the UAV further includes a vibration isolating member disposed on the arm and located between the mounting portion and the fuselage to block vibration of the power assembly.

Compared with the prior art, the rack of the UAV and the UAV are provided with the vibration isolating member to prevent the vibration of the power component from being transmitted to the airframe through the arm, thereby ensuring The components within the fuselage are protected from the shock.

DRAWINGS

1 is a perspective view of an unmanned aerial vehicle according to an embodiment of the present invention.

2 is an exploded view of the arm of the UAV of FIG. 1.

3 is a further exploded view of the arm of the UAV of FIG. 2.

4 to 6 are schematic views of the assembly of the arm of the UAV of Fig. 3.

Fig. 7 is a schematic view of an unmanned aerial vehicle according to a second embodiment of the present invention.

Fig. 8 is a schematic view of an unmanned aerial vehicle according to a third embodiment of the present invention.

Main component symbol description

Aircraft 100, 200, 300 body 10, 10’, 10’’ Upper shell 11 Lower case 12 Arm 20, 20’, 20’’ First paragraph twenty one End face 210 Limiting department 211 supporting item 2111 Stopper 2112 First splice 21a Second splice 21b Second paragraph twenty two Arm 201 First arm 221 First snap-in bulge 2211 First connecting column 2212 Connection hole 2212a Second arm 223 Second connecting column 2232 Through hole 2233 Installation department 202 First installation 222 Second installation 224 Fixed structure 2241 perforation 2221 Third joint 22a Fourth joint 22b Isolation part 30, 30’, 30’’ Nesting hole 301 Abutment 31 Power component 40, 40’ Tripod 50 Connector 60

The invention will be further illustrated by the following detailed description in conjunction with the accompanying drawings.

detailed description

The technical solutions in the embodiments of the present invention are clearly and completely described in the following with reference to the accompanying drawings in the embodiments of the present invention. It is obvious that the described embodiments are only a part of the embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative efforts are within the scope of the present invention.

It should be noted that when a component is referred to as being "fixed" to another component, it can be directly on the other component or the component can be present. When a component is considered to "connect" another component, it can be directly connected to another component or possibly a central component. When a component is considered to be "set to" another component, it can be placed directly on another component or possibly with a centered component. The terms "vertical," "horizontal," "left," "right," and the like, as used herein, are for illustrative purposes only.

All technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs, unless otherwise defined. The terminology used in the description of the present invention is for the purpose of describing particular embodiments and is not intended to limit the invention. The term "or/and" as used herein includes any and all combinations of one or more of the associated listed items.

Referring to FIG. 1 , an unmanned aerial vehicle 100 according to an embodiment of the present invention includes a fuselage 10 , an arm 20 , a vibration isolating member 30 , a power assembly 40 , and a stand 50 . In this embodiment, the UAV 100 is a quadrotor unmanned aerial vehicle, so the power assembly 40 is a rotor assembly and the number is four, and the four power components 40 are supported by the corresponding arm 20 . And distributed in a rectangular area around the body 10, and each of the power components 40 is located at one vertex of the rectangle. According to the aerodynamic principle, in order to avoid the turbulence of the power assembly 40 during rotation, the adjacent power components 40 have different rotational directions during operation, and the opposite rotational directions of the power components 40 are the same.

Of course, the number of the power components 40 can be appropriately changed according to different requirements. For example, the number of the power components 40 can be two, three, six, eight, sixteen, etc., even The number of power components 40 can be only one.

The airframe 10 is a carrier of the unmanned aerial vehicle 100, and an electrical installation portion may be disposed on or in the body 10. The electrical installation portion may mount and carry a sensor, a circuit board, a processor, and a communication module. And electronic components such as batteries. The outer casing (not numbered) of the fuselage 10 is streamlined to reduce air resistance during flight. In other embodiments, the outer casing of the fuselage 10 may have other shapes, such as a polygon, a circle, an ellipse, and the like. It can be understood that the outer casing of the fuselage 10 can also be omitted, and the fuselage 10 is formed only by the bracket overlapping.

In this embodiment, the body 10 includes an upper casing 11 and a lower casing 12, and the upper casing 11 and the lower casing 12 are spliced and joined to each other to form an integral casing of the body 10. It can be understood that the upper case 11 and the lower case 12 can be connected to each other by means of snapping, fastener connection, gluing or the like.

A cavity (not shown) is formed between the upper casing 11 and the lower casing 12, and the sensor, the circuit board, the processor, the communication module, and the battery are housed in the cavity.

The arm 20 is used to support the power assembly 40 and distribute the power assembly 40 around the fuselage 10 in a predetermined pattern. In the present embodiment, the number of the arms 20 corresponds to the number of the power components 40, and is four.

It can be understood that in other embodiments, the number of the arms 20 may be different from the number of the power components 40. For example, each of the arms 20 can support two or more of the power assemblies 40. Specifically, each of the arms 20 can form two or more branches, each of which can support one The power assembly 40. For another example, each of the arms 20 may not include a branch. As long as the arms 20 and the power assembly 40 are sized, a plurality of the power components 40 may be disposed on each of the arms 20. .

Referring to FIG. 2 and FIG. 3 , the arm 20 is connected to the side of the body 10 , and the plurality of the arms 20 are radially connected to the circumference of the body 10 . In this embodiment, The angles between the adjacent arms 20 are the same. Each of the arms 20 includes a first section 21 and a second section 22. The first section 21 is coupled to the fuselage 10, and the second section 22 supports the corresponding power assembly 40. The vibration isolating member 30 is disposed between the first segment 21 and the second segment 22 . The first segment 21 and the second segment 22 are separated by the isolating member 30. In other words, the first segment 21 and the second segment 22 are not in direct contact.

A limiting portion 211 is protruded from an end surface 210 of each of the first segments 21 facing away from the fuselage 10 , and the limiting portion 211 includes a supporting member 2111 and a stopping member 2112 . The support member 2111 is a protrusion formed on the end surface 210 of the first segment 21. In the embodiment, the support member 2111 is a cylindrical protrusion. It can be understood that the support member 2111 can also be Prism or other shaped studs. The cross-sectional dimension of the support member 2111 is smaller than the size of the end surface 210 of the first segment 21 such that at least a portion of the end surface 210 protrudes from the circumferential side of the first segment 21. The stopper 2112 is a flange formed at the end of the support member 2111. In the embodiment, the stopper 2112 protrudes substantially perpendicularly from the circumferential side of the support member 2111. 2112 is a continuous annular flange. It can be understood that in other embodiments, the stopper 2112 may also be discontinuous. For example, the stopper 2112 may be composed of a plurality of arcuate flanges.

In this embodiment, the support member 2111 and the stopper 2112 are integrally formed, and the support member 2111 is integrally formed with the first segment 21. It can be understood that the support member 2111, the stopper member 2112 and the first segment 21 can also be separately formed and assembled by the above-mentioned structure, and the connection can be a snap connection, a glue connection, a welding, etc. , no longer repeat them one by one.

In the embodiment, the first segment 21 is a hollow structure, and the inside thereof communicates with the internal space of the body 10.

In this embodiment, the first segment 21 includes a plurality of splice portions, and the plurality of splice portions are spliced to form the first segment 21 . Specifically, the first segment 21 includes a first splicing portion 21a and a second splicing portion 21b, and the first splicing portion 21a and the second splicing portion 21b are spliced to each other to form the first segment 21. The first joint portion 21a is integrally formed with the upper casing 11 of the body 10, and the second joint portion 21b is integrally formed with the lower casing 12 of the body 10. The upper case 11 and the lower case 12 are spliced and joined to each other to form an integral outer casing of the body 10. It can be understood that the first splicing portion 21a and the second splicing portion 21b can be connected to each other by means of snapping, fastener connection, gluing or the like. It can be understood that the first segment 21 may further include other splicing portions than the first splicing portion 21a and the second splicing portion 21b, and details are not described herein.

The second section 22 is a hollow structure whose end facing the first section 21 is an open end. The second segment 22 includes a third splicing portion 22a and a fourth splicing portion 22b that can be spliced to each other. The third joint portion 22a includes a first arm portion 221 and a first mounting portion 222 connected to the first arm portion 221, and the fourth joint portion 22b includes a second arm portion 223 and the second arm portion The second mounting portion 224 is connected to the portion 223. After the third joint portion 22a and the fourth joint portion 22b are fastened to each other, the first arm portion 221 and the second arm portion 223 together constitute an integral arm portion 201 of the arm 20 The first mounting portion 222 and the second mounting portion 224 together constitute an integral mounting portion 202 of the arm 20 . The arm portion 201 can be coupled to the first segment 21, the arm portion 201 having a length such that the corresponding power assembly 40 can be supported at a predetermined position.

In this embodiment, the length of the second segment 22 is greater than the length of the first segment 21 .

In the present embodiment, the arm portion 201 has a substantially truncated cone shape, and a cross-sectional dimension of the end portion of the arm portion 201 away from the body 10 is smaller than a cross-sectional dimension toward an end of the first segment 21 . The inner surface of the arm portion 201 is substantially tapered, and the inner dimension of the arm portion 201 is gradually reduced from a side close to the first segment 21 toward a side away from the body 10.

A plurality of first latching protrusions 2211 are formed on an inner surface of the first arm portion 221 at an end adjacent to the first segment 21 . In this embodiment, the number of the first latching protrusions 2211 is two, and the two first latching protrusions 2211 are parallel and spaced apart from each other. Specifically, the first latching protrusion 2211 is along The first arm portions 221 are arranged in the longitudinal direction. In this embodiment, the first engaging protrusions 2211 are all semi-annular protrusions.

It can be understood that in other embodiments, the number of the first latching protrusions 2211 may be changed to one, three, four, and the like; in addition, at least one of the first latching protrusions 2211 may also have Multi-section arc-shaped protrusions.

An inner surface of the first arm portion 221 is further formed with a first connecting post 2212, and the first connecting post 2212 extends from a surface of the first arm portion 221 toward the second arm portion 223, the first A connecting hole 2212a is formed in the connecting post 2212 toward the end surface of the second arm portion 223. In this embodiment, the number of the first connecting posts 2212 is two, and the connecting holes 2212a are threaded holes.

The first mounting portion 222 is located at an end of the first arm portion 221 facing away from the body 10 . The first mounting portion 222 is provided with a through hole 2221 , and the through hole 2221 can pass through a part of the structure of the power assembly 40 .

The second arm portion 223 has a structure substantially similar to the first arm portion 221, and includes a second snap-in protrusion (not labeled) corresponding to the first snap-in protrusion 2211 and The first connecting post 2212 corresponds to the second connecting post 2232. The second snap-in protrusion is substantially similar to the structure of the first latching protrusion 2211 and will not be described in detail. The second arm portion 223 defines a through hole 2233 corresponding to the second connecting post 2232 , and the through hole 2233 extends from the outer surface of the second arm portion 223 to the corresponding second connecting post 2232 The end surface of the first arm portion 221 is faced.

The second mounting portion 224 is located at an end of the second arm portion 223 that faces away from the body 10. The first mounting portion 222 and the second mounting portion 224 together form a mounting groove structure for mounting the power assembly 40. The mounting groove structure is in communication with the interior of the first section 21. The second mounting portion 224 is provided with a fixing structure 2241 for fixing the power assembly 40.

The vibration isolating member 30 is for eliminating the influence of the vibration of the power assembly 40 on the body 10. The vibration isolating member 30 is made of an elastic material. Alternatively, the material of the vibration isolating member 30 may be soft rubber, rubber, silica gel or the like. The vibration isolating member 30 has a substantially sleeve shape, and a sleeve hole 301 is formed inside thereof. In this embodiment, the sleeve hole 301 is a circular hole, and the inner diameter of the sleeve hole 301 is matched with the outer diameter of the support member 2111, and the inner diameter of the sleeve hole 301 is smaller than the stop. The outer diameter of the piece 2112. An abutting portion 31 is formed on a circumferential side surface of the vibration isolating member 30. In the present embodiment, the abutting portion 31 is a plurality of flanges that are convex with respect to the circumferential side surface of the vibration isolating member 30, and the plurality of flanges are spaced along the central axis of the sleeve hole 301. Settings. In this embodiment, the outer diameters of the flanges are different from each other, and the outer diameter of the flanges is sequentially decreased along the direction in which the vibration isolating members 30 face away from the body 10. The decreasing extent of the outer diameter dimension of the flange is adapted to the taper of the inner surface of the arm portion 201. The outer diameter of the flange farthest from the fuselage 10 is larger than the outer diameter of the stopper 2112.

In this embodiment, the number of the flanges is three, and the separation distance between the flanges is matched with the thickness of the first locking protrusion 2211 and the second locking protrusion; The thickness of the flange is adapted to the spacing of the first latching projections 2211 and the spacing of the second latching projections. In other words, the flange can be clamped to and engaged with the first engaging projection 2211 and the second engaging projection.

It can be understood that the number of the flanges can also be changed according to requirements, for example, four, five, six, etc., and even the flanges can be one of the whole.

Referring to FIG. 4 to FIG. 6 , the shock absorbing member 30 is sleeved on the support member 2111 , and the stopper member 2112 can resist the end of the vibration isolation member 30 facing away from the body 10 . a portion for preventing the vibration-isolating member 30 from coming off the support member 2111; the fourth joint portion 22b is sleeved from the lower portion of the body 10 on the vibration-isolating member 30, and the second snap-in The protrusion and the abutting portion 31 of the vibration isolating member 30 abut each other, specifically, the flange is engaged with the space between the second locking protrusions, and the second card is inserted into the convex card. Into the gap between the flanges, the flange closest to the fuselage 10 is located between the fuselage 10 and the fourth joint portion 22b; the third joint portion 22a is from the machine The upper portion of the body 10 is sleeved on the vibration isolating member 30, and the first engaging projection 2211 and the abutting portion 31 of the vibration isolating member 30 abut each other. Specifically, the flange is engaged. a spacing between the first snap-in protrusions 2211, the first snap-in protrusion 2211 snaps into the space between the flanges, and the flange closest to the fuselage 10 is located at the machine Body 10 and the third joint The second splicing portion 22a and the fourth splicing portion 22b are mutually engaged to form the second segment 22, and the second segment 22 is internally connected to the first segment 21, the machine The electronic component in the body 10 can be electrically connected to the power component 40 through a conductive line (not shown) disposed in the first segment 21 and the second segment 22; the first connecting post 2212 and The second connecting portion 2232 is aligned with each other, and the third joint portion 22a and the fourth joint portion 22b are fixedly connected to each other by a connecting member 60. In the embodiment, the connecting member 60 is a bolt, which can The first connecting post 2212 is threaded so that the arm 20 clamps the shock absorbing member 30; the vibration isolating member 30 is located between the body 10 and the arm 20, thereby avoiding The direct contact between the fuselage 10 and the arm 20 is such that the isolating member 30 can eliminate the influence of vibrations from the arm 20 on the fuselage 10.

Referring again to FIG. 1, the power assembly 40 is configured to provide flight power to the UAV 100. The power assembly 40 includes a motor 41 and a propeller 42. The motor 41 includes a stator 411 and a rotor 412 rotatable relative to the stator 411. Specifically, in conjunction with FIG. 3, the stator 411 is fixed on the second mounting portion 224 of the fourth joint portion 22b, and the rotor 412 and a portion of the stator 411 pass through the third joint portion 22a. A through hole 2221 of the mounting portion 222.

In this embodiment, the motor 41 may be any suitable type of motor such as a brushless motor or a brushed motor.

The motor 41 can be electrically connected to electronic components (such as a flight control, a power source, etc.) of the body 10.

The propeller 42 is coupled to the rotor 412 and is rotatable by the rotation 412. The propeller 42 can be a foldable paddle.

The stand 50 is a support structure when the UAV 100 is landing. The stand 50 is coupled to the bottom of the body 10 and extends away from the body 10 by a predetermined distance. The number of the stand 50 is two. In an embodiment, the connection angle of the stand 50 relative to the body 10 can be adjusted, and when the UAV 100 is in a flight state, the stand 50 can be retracted relative to the body 10. In order to prevent the tripod 50 from blocking the load (not shown) under the fuselage 10, for example, a sensor, a camera, a camera, or the like. In another embodiment, the antenna 50 (not shown) of the UAV 100 is disposed inside or outside the stand 50, such that the antenna can be remote from the electronic components in the body 10, avoiding the The interference of the electronic component to the antenna.

The unmanned aerial vehicle 100 isolates the arm 20 and the body 10 by the vibration isolating member 30, so that the vibration isolating member 30 can eliminate vibration from the arm 20 to the body 10. The effect is that the functional modules in the fuselage 10 are prevented from being abnormally affected or damaged by the vibration.

Referring to FIG. 7, a schematic diagram of an unmanned aerial vehicle 200 according to a second embodiment of the present invention is shown. The UAV 200 has a structure similar to that of the UAV 100 described in the first embodiment. Furthermore, the length of the first section 21' of the arm 20' of the UAV 200 is greater than the length of the second section 22', so that the isolation member 30' is closer than the first embodiment. Corresponding to the power assembly 40', the weight of the second segment 22' can be reduced due to being disposed closer to the power assembly 40', so the second segment 22' and the power assembly 40' function The torque on the vibration isolating member 30' becomes smaller. Therefore, the arm 20' of the UAV 200 is less prone to chattering.

Referring to FIG. 8, a schematic diagram of an unmanned aerial vehicle 300 according to a third embodiment of the present invention is shown. The UAV 300 has a structure similar to the UAV 100 described in the first embodiment. In addition, the vibration isolation member 30" of the UAV 300 is disposed between the arm 20" and the airframe 10". The UAV 300 can also avoid the functions in the airframe 10". The module is affected by the vibration of the power assembly 40'' and functions abnormally or is damaged.

The specific structure of the vibration isolating member 30 ′′ and the connection between the vibration isolating member 30 ′′ and the arm 20 ′′ may be the same as the vibration isolating member 30 described in the first embodiment, and no longer A detailed description.

It is to be understood that those skilled in the art can make other variations and the like in the spirit of the present invention for use in the design of the present invention as long as it does not deviate from the technical effects of the present invention. All changes made in accordance with the spirit of the invention are intended to be included within the scope of the invention.

Claims (75)

 A rack of an unmanned aerial vehicle includes a fuselage and an arm connected to the fuselage, the arm being provided with a mounting portion for mounting a power component, wherein the rack of the unmanned aerial vehicle is further The vibration isolating member is disposed on the arm and located between the mounting portion and the fuselage to block vibration of the power component.  A frame for an unmanned aerial vehicle according to claim 1, wherein said arm includes a first section and a second section, said first section being coupled to said body, said mounting portion being located In the second segment, the vibration isolating member is disposed between the first segment and the second segment to space the first segment and the second segment.  The frame of the unmanned aerial vehicle of claim 2, wherein the vibration isolating member is sleeved on the first segment, and the second segment is sleeved on the vibration isolation.  The frame of the unmanned aerial vehicle of claim 2, wherein a limiting portion is protruded from an end surface of the first segment, the vibration isolating member is disposed on the limiting portion, and the The periphery of the limiting portion is elastically resisted by the vibration isolating member and the arm.  The frame of the unmanned aerial vehicle of claim 4, wherein the limiting portion comprises a support member and a stopper, the support member being a protrusion formed on the end surface of the first segment The stopper is a flange formed at an end of the support member, and the vibration isolating member is sleeved on the support member, and the stopper abuts against the vibration isolation member facing away from the body One side.  A stand for an unmanned aerial vehicle according to claim 5, wherein said stopper is an annular flange projecting from a circumferential side of said support member.  The frame of the unmanned aerial vehicle according to claim 6, wherein the stopping member is a continuous annular flange; or the stopping member is formed by a plurality of arcuate flanges arranged in an annular shape. .  A frame for an unmanned aerial vehicle according to claim 2, wherein said first section is a hollow structure and includes a plurality of splices, said plurality of splices being detachably connectable to form said first segment.  A frame for an unmanned aerial vehicle according to claim 8, wherein said body comprises an upper casing and a lower casing disposed opposite said upper casing; and said first section has two joint portions. The first joint portion and the second joint portion are respectively connected to the upper shell, and the second joint portion is connected to the lower shell.  A stand for an unmanned aerial vehicle according to claim 9, wherein said upper splice portion is integrally formed with said upper casing, and said lower splice portion is integrally formed with said lower casing.  The frame of the unmanned aerial vehicle according to claim 2, wherein the end of the second section connected to the first section is an open end, and the open end of the first section is sleeved in the On the isolation parts.  A frame for an unmanned aerial vehicle according to claim 11, wherein said vibration isolating member is engaged with the open end of said second segment.  A stand for an unmanned aerial vehicle according to claim 11 wherein said first section is a hollow structure and said communicating with said open end of said second section.  A frame for an unmanned aerial vehicle according to claim 2, wherein the length of said second section is less than the length of said first section.  A frame for an unmanned aerial vehicle according to claim 2, wherein said plurality of said arms are radially protruded from said main body, and each of said arms is The second section is provided with one of the mounting portions away from the end of the fuselage.  A stand for an unmanned aerial vehicle according to claim 15 wherein the angles between the adjacent arms are the same.  A frame for an unmanned aerial vehicle according to claim 2, wherein said second section includes an arm portion and said mounting portion at an end of said second section facing away from said first section, said An arm is coupled to the first section by the vibration isolating member for mounting and supporting the power assembly.  A stand for an unmanned aerial vehicle according to claim 17, wherein said arm portion is hollow, and an inner surface of said arm portion abuts against an outer peripheral edge of said vibration isolating member of said vibration isolating member.  A frame for an unmanned aerial vehicle according to claim 18, wherein an inner surface of said arm portion is a tapered surface, and a peripheral side surface of said vibration isolating member is adapted to an inner surface of said arm portion. Conical face.  The frame of the unmanned aerial vehicle according to claim 18, wherein an inner surface of the arm portion is formed with a locking projection, and a circumferential side of the vibration isolating member is formed with the engaging projection The mating abutting portion, the latching protrusion and the abutting portion are in abutting engagement with each other.  The rack of the unmanned aerial vehicle according to claim 20, wherein the plurality of latching projections are plural, and the plurality of the latching projections are parallel and spaced apart from each other, and the abutting portion is a plurality of a flange that protrudes from a circumferential side of the vibration isolating member, and the flange and the engaging projection are in abutting engagement with each other.  A stand for an unmanned aerial vehicle according to claim 21, wherein said flange closest to said body is elastically held between an end surface of said first section and an end surface of said arm.  A stand for an unmanned aerial vehicle according to claim 21, wherein said snap-in projections are arranged along a length direction of said arm portion.  A stand for an unmanned aerial vehicle according to claim 21, wherein said snap-in projections are all semi-annular projections.  A frame for an unmanned aerial vehicle according to claim 21, wherein said flanges have outer diameters different from each other and are outwardly of said flanges in a direction away from said body by said vibration isolating member The diameter dimensions are successively reduced, and the decreasing extent of the outer diameter dimension of the flange is adapted to the taper of the inner surface of the arm.  A frame for an unmanned aerial vehicle according to claim 20, wherein said second section comprises a third splicing portion and a fourth splicing portion that are detachably coupled to each other, and said third splicing portion includes a first arm And a first mounting portion connected to the first arm portion, the fourth joint portion includes a second arm portion and a second mounting portion connected to the second arm portion, and the third joint portion is After the fourth splicing portions are fastened to each other, the first arm portion and the second arm portion together constitute the arm portion, and the first mounting portion and the second mounting portion together constitute the mounting unit.  A stand for an unmanned aerial vehicle according to claim 26, wherein an inner surface of said first arm portion forms a first snap-in projection, and an inner surface of said second arm portion forms a second snap-in projection The first latching protrusion and the second latching protrusion together constitute the latching protrusion.  The rack of the unmanned aerial vehicle according to claim 27, wherein the first engaging projection and the second engaging projection are both semi-annular projections.  The frame of the unmanned aerial vehicle according to claim 27, wherein the inner surface of the first arm portion is further formed with a first connecting post, and the first connecting post is from the surface of the first arm portion Extending toward the second arm portion, the second arm portion includes a second connecting post corresponding to the first connecting post, the first arm portion and the second arm portion passing through the first connection The post and the second connecting post are fixedly coupled to each other.  The rack of the unmanned aerial vehicle according to claim 29, wherein the first connecting post is provided with a connecting hole toward the end surface of the second arm portion, and the second arm portion is opened corresponding to the a through hole of the second connecting post, the through hole penetrating from an outer surface of the second arm portion to an end surface of the corresponding second connecting post facing the first arm portion, the arm includes a connecting member, The connecting member passes through the through hole and is fixedly connected to the connecting hole.  A stand for an unmanned aerial vehicle according to claim 30, wherein said connecting hole is a threaded hole, and said connecting member is a bolt.  The rack of the unmanned aerial vehicle according to claim 2, wherein the mounting portion faces away from a mounting groove provided at the other end of the second segment, and the receiving groove is configured to receive a portion of the power Component.  The rack of the unmanned aerial vehicle according to claim 32, wherein the first section and the second section are both hollow and communicate with each other, and the receiving slot is connected to the second section. So that the power supply wires of the power assembly can pass through the first segment and the second segment.  A frame for an unmanned aerial vehicle according to claim 1, wherein said vibration isolating member is made of an elastic material.  The frame of the unmanned aerial vehicle according to claim 1, wherein the material of the vibration isolating member is at least one selected from the group consisting of soft rubber, rubber, and silica gel.  A frame for an unmanned aerial vehicle according to claim 1, wherein said vibration isolating member elastically abuts between said arm and said body and separates said arm from said body .  An unmanned aerial vehicle comprising a frame and a power assembly, the frame comprising a fuselage and an arm coupled to the fuselage, the arm being provided with a mounting portion for the mounting power assembly, characterized in that The rack of the UAV further includes a vibration isolating member disposed on the arm and located between the mounting portion and the body to block vibration of the power component .  An unmanned aerial vehicle according to claim 37, wherein said arm includes a first section and a second section, said first section being coupled to said body, said mounting portion being located in said second section The vibration isolation member is disposed between the first segment and the second segment to space the first segment and the second segment.  The UAV according to claim 38, wherein the vibration isolating member is sleeved on the first segment, and the second segment is sleeved on the vibration isolation.  The UAV according to claim 38, wherein a limiting portion is protruded from an end surface of the first segment, the vibration isolating member is disposed on the limiting portion, and the limiting portion is The peripheral edge is elastically resisted by the vibration isolation member and the arm.  An unmanned aerial vehicle according to claim 40, wherein said limiting portion includes a support member and a stopper, said support member being a boss formed on said end surface of said first segment, said said The stopper is a flange formed at an end of the support member, and the vibration isolating member is sleeved on the support member, and the stopper abuts against a side of the vibration isolating member facing away from the body.  The UAV according to claim 41, wherein said stopper is an annular flange projecting from a circumferential side surface of said support member.  The UAV according to claim 42, wherein said stopper is a continuous annular flange; or said stopper is formed by a plurality of arcuate flanges arranged in an annular shape.  The UAV according to claim 38, wherein said first section is a hollow structure and includes a plurality of splices, said plurality of splices being detachably connectable to form said first section.  An unmanned aerial vehicle according to claim 44, wherein said body comprises an upper casing and a lower casing disposed opposite said upper casing; said first section has two joint portions, respectively a joint portion and a second joint portion, the first joint portion is connected to the upper shell, and the second joint portion is connected to the lower shell.  The UAV according to claim 45, wherein said upper splice portion is integrally formed with said upper casing, and said lower splice portion is integrally formed with said lower casing.  The UAV according to claim 38, wherein the end of the second section connected to the first section is an open end, and the open end of the first section is sleeved at the isolation On the piece.  The UAV according to claim 47, wherein said vibration isolating member is engaged with the open end of said second section.  The UAV according to claim 47, wherein said first section is a hollow structure and said communicating with said open end of said second section.  The UAV according to claim 38, wherein the length of the second segment is less than the length of the first segment.  An unmanned aerial vehicle according to claim 38, wherein said plurality of said arms are radially projecting from said main body, said second of said each of said arms The end portion of the segment away from the fuselage is provided with one of the mounting portions.  The UAV according to claim 51, wherein the angles between the adjacent arms are the same.  An unmanned aerial vehicle according to claim 38, wherein said second section comprises an arm portion and said mounting portion at an end of said second section facing away from said first section, said arm passing The vibration isolating member is coupled to the first segment, and the mounting portion is for mounting and supporting the power assembly.  An unmanned aerial vehicle according to claim 53, wherein said arm portion is hollow, and an inner surface of said arm portion abuts against an outer peripheral edge of said vibration isolating member of said vibration isolating member.  An unmanned aerial vehicle according to claim 54, wherein an inner surface of said arm portion is a tapered surface, and a circumferential side surface of said vibration isolating member is tapered to fit an inner surface of said arm portion. surface.  An unmanned aerial vehicle according to claim 54, wherein an inner surface of said arm portion is formed with a snap-in projection, and a peripheral side of said vibration isolating member is formed to be fitted with said snap-in projection The abutting portion is configured to be engaged with the abutting portion.  The UAV according to claim 56, wherein the plurality of latching projections are plural, and the plurality of latching projections are parallel and spaced apart from each other, and the abutting portions are plurality of a circumferentially convex flange of the vibration isolating member, the flange and the engaging projection being in abutting engagement with each other.  The UAV according to claim 57, wherein said flange closest to said body is elastically held between an end surface of said first section and an end surface of said arm.  An unmanned aerial vehicle according to claim 57, wherein said snap-in projections are arranged along a longitudinal direction of said arm portion.  The UAV according to claim 57, wherein said first snap-in projections are all semi-annular projections.  The UAV according to claim 57, wherein the outer diameters of the flanges are different from each other, and the outer diameter of the flanges is sequentially in a direction away from the body of the vibration isolating member. Decreasing, the decreasing extent of the outer diameter dimension of the flange is adapted to the taper of the inner surface of the arm.  The UAV according to claim 56, wherein said second segment comprises a third splicing portion and a fourth splicing portion that are detachably coupled to each other, said third splicing portion including a first arm portion and a first mounting portion to which the first arm portion is connected, the fourth joint portion includes a second arm portion and a second mounting portion connected to the second arm portion, the third splice portion and the first After the four splice portions are fastened to each other, the first arm portion and the second arm portion together constitute the arm portion, and the first mounting portion and the second mounting portion collectively constitute the mounting portion.  The UAV according to claim 62, wherein the inner surface of the first arm portion forms a first snap-in projection, and the inner surface of the second arm portion forms a second snap-in projection. The first snap-in protrusion and the second snap-in protrusion together constitute the latching protrusion.  The UAV according to claim 63, wherein said first engaging projection and said second engaging projection are both semi-annular projections.  The UAV according to claim 63, wherein the inner surface of the first arm portion is further formed with a first connecting post, the first connecting post from the surface of the first arm portion to the a second arm portion extending, the second arm portion including a second connecting post corresponding to the first connecting post, the first arm portion and the second arm portion passing through the first connecting post and The mutual connection of the second connecting columns is fixedly connected.  The UAV according to claim 65, wherein the first connecting post is provided with a connecting hole toward an end surface of the second arm, and the second arm is opened corresponding to the second connecting a through hole of the column, the through hole penetrating from an outer surface of the second arm portion to an end surface of the corresponding second connecting post facing the first arm portion, the arm includes a connecting member, the connecting The piece passes through the through hole and is fixedly connected to the connecting hole.  The UAV according to claim 66, wherein said connecting hole is a threaded hole, and said connecting member is a bolt.  The UAV according to claim 38, wherein said mounting portion faces away from a mounting groove provided at the other end of said second segment, said receiving groove for receiving a portion of said power assembly.  The UAV according to claim 68, wherein the first segment and the second segment are both hollow and communicate with each other, and the receiving groove communicates with the second segment to enable A power supply lead of the power assembly is traversable through the first segment and the second segment.  The UAV according to claim 37, wherein said vibration isolating member is made of an elastic material.  The UAV according to claim 37, wherein the material of the vibration isolating member is at least one selected from the group consisting of soft rubber, rubber, and silica gel.  The UAV according to claim 37, wherein said vibration isolating member elastically abuts between said arm and said body and separates said arm from said body.  The UAV according to claim 37, wherein said power component is a rotor.  An unmanned aerial vehicle according to claim 73, wherein said rotor comprises a motor and a propeller, said stator of said motor being fixed to said end of said arm facing away from said fuselage, said propeller being coupled to said motor On the rotor.  The UAV according to claim 37, wherein said UAV includes a stand that is coupled to a bottom of said body and extends away from said body by a predetermined distance.

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