CN111377049A - Portable foldable unmanned aerial vehicle and working method thereof - Google Patents
Portable foldable unmanned aerial vehicle and working method thereof Download PDFInfo
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- CN111377049A CN111377049A CN202010246365.8A CN202010246365A CN111377049A CN 111377049 A CN111377049 A CN 111377049A CN 202010246365 A CN202010246365 A CN 202010246365A CN 111377049 A CN111377049 A CN 111377049A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K5/00—Casings, cabinets or drawers for electric apparatus
- H05K5/02—Details
- H05K5/0213—Venting apertures; Constructional details thereof
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- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05K—PRINTED CIRCUITS; CASINGS OR CONSTRUCTIONAL DETAILS OF ELECTRIC APPARATUS; MANUFACTURE OF ASSEMBLAGES OF ELECTRICAL COMPONENTS
- H05K7/00—Constructional details common to different types of electric apparatus
- H05K7/20—Modifications to facilitate cooling, ventilating, or heating
- H05K7/20009—Modifications to facilitate cooling, ventilating, or heating using a gaseous coolant in electronic enclosures
- H05K7/20127—Natural convection
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Abstract
The invention discloses a portable foldable unmanned aerial vehicle and a working method thereof, the unmanned aerial vehicle comprises a body assembly and wing assemblies, wherein the four wing assemblies are distributed on the body assembly in an annular array manner, the body assembly comprises an upper body shell, a lower body shell, an upper heat dissipation shell and a lower heat dissipation shell, the upper body shell is fixedly arranged at the top of the lower body shell, cavities are formed in the upper body shell and the lower body shell, the upper heat dissipation shell is arranged at the top of the cavity of the upper body shell, and the lower heat dissipation shell is arranged at the bottom of the cavity of the lower body shell. This unmanned aerial vehicle is rotatory around the bolt hole with four arc folded sheets when not using, and in the space of first wing folding area and second wing folding area was folded into completely to four wing subassemblies, only appeared fuselage subassembly on the whole, not only saved the place space, conveniently carried, the rotor can not take place to damage because of colliding with hard thing and wiping moreover, has prolonged life.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a portable foldable unmanned aerial vehicle and a working method thereof.
Background
The unmanned aerial vehicle consists of an aircraft body, a flight control system, a data link system, an emission and recovery system, a power supply system and the like, is an unmanned aircraft controlled by radio remote control equipment and a self-contained program control device, and has wide application in the fields of aerial photography, surveying and mapping, agricultural plant protection, electric power inspection, disaster relief, movie and television shooting and the like.
The structural component of unmanned aerial vehicle usually includes the fuselage and extends a plurality of horn from the fuselage, and the terminal that the fuselage was kept away from to the horn sets up the power device of a plurality of drives flight. Prior art (CN209290675U) discloses a foldable unmanned aerial vehicle, including fuselage and horn, horn one end articulates on the fuselage, power component is installed to the other end, the horn epirelief is equipped with places the arch, the horn has expansion state and fold condition, the horn can be followed the first direction by expansion state and rotated to fold condition, when the horn is located fold condition, the horn is equipped with the below of placing bellied part and rotating to the fuselage, and place the one side that the arch is located the bottom that the horn deviates from the fuselage, power component is including fixing the motor at the horn tip and by the rotatory screw of motor drive, it highly is greater than the radial protrusion on the horn surface of motor edge horn to place bellied. Place the arch through the setting, can utilize this to place the arch after unmanned aerial vehicle is folding and separate placing surface such as unmanned aerial vehicle and ground, desktop to prevent that placing surface and unmanned aerial vehicle especially motor direct contact on the unmanned aerial vehicle from wearing and tearing.
The following technical problems exist in the existing foldable unmanned aerial vehicle: 1) the wing assembly cannot be completely folded in the space of the fuselage assembly, so that the placing space of the unmanned aerial vehicle is increased, the unmanned aerial vehicle is inconvenient to carry, and the rotor wing can be damaged due to the fact that the rotor wing collides with a hard object, so that the service life is shortened; 2) heat generated in the working process of the electronic device cannot be dissipated in time, and accumulated heat causes reduction of unmanned aerial vehicle control efficiency and flight quality; 3) the rotor subassembly's weight is great, and the in-process windage is big, and the flight process is not stable enough.
Disclosure of Invention
In order to solve the technical problem, the invention aims to provide a portable foldable unmanned aerial vehicle and a working method thereof.
Through rotating around the bolt hole with four arc folded sheets for in four wing subassemblies are folded completely and are gone into the space in first wing folding district and second wing folding district, only present fuselage subassembly on the whole, not only saved and placed the space, conveniently carry, the rotor can not take place to damage because of colliding with hard thing and wiping moreover, has prolonged life.
Through set up the louvre on last heat dissipation casing with lower heat dissipation casing for the heat that produces in the electronic device working process such as power, panel, flight controller in time gives off, prevents to cause the circumstances that unmanned aerial vehicle control efficiency reduces, flight quality reduces because of gathering the heat.
The buffer plates, the first buffer columns and the second buffer columns are all made of elastic rubber materials, so that the friction force of the arc-shaped folding plates on the upper body shell, the lower body shell and the second bolts in the folding process is buffered, and the vibration generated in the flying process of the unmanned aerial vehicle is reduced; a plurality of lightening hole has not only alleviateed the weight of rotor subassembly, and flight in-process air current passes from the lightening hole, has reduced unmanned aerial vehicle's windage for the flight process is more stable.
The purpose of the invention can be realized by the following technical scheme:
the invention provides a portable foldable unmanned aerial vehicle, which comprises a fuselage assembly and wing assemblies, wherein the four wing assemblies are distributed on the fuselage assembly in an annular array manner, the fuselage assembly comprises an upper fuselage shell, a lower fuselage shell, an upper heat dissipation shell and a lower heat dissipation shell, the upper fuselage shell is fixedly arranged at the top of the lower fuselage shell, cavities are formed in the upper fuselage shell and the lower fuselage shell, the upper heat dissipation shell is arranged at the top of the cavity of the upper fuselage shell, and the lower heat dissipation shell is arranged at the bottom of the cavity of the lower fuselage shell;
the central part of the upper radiating shell is provided with a plurality of upper radiating holes, and the outer edge of the upper radiating shell is provided with four upper mounting holes distributed in a circumferential array; the central part of the lower radiating shell is provided with a central hole, the periphery of the central hole is provided with a plurality of lower radiating holes, and the outer edge of the lower radiating shell is provided with four lower mounting holes distributed in a circumferential array;
the wing assembly comprises an arc-shaped folding piece, a buffer assembly, a second bolt, a rotor wing assembly and a nut, the arc-shaped folding piece comprises an arc-shaped folding plate, one end of the arc-shaped folding plate is provided with a bolt hole, the other end of the arc-shaped folding plate is provided with a rotor wing mounting hole, and a plurality of lightening holes are formed between the bolt hole and the rotor wing mounting hole; the buffer components comprise buffer plates, first buffer columns and second buffer columns, the first buffer columns and the second buffer columns are respectively connected to two ends of the buffer plates, and the plurality of buffer components are horizontally stacked into a plurality of layers from top to bottom; the second bolt passes through first installation cavity, bolt hole, behind the second installation cavity through the nut fastening.
As a further scheme of the invention, the upper body shell comprises an upper shell body, the upper shell body is in a similar ring shape with an inner cavity, four first arc-shaped convex parts and four first arc-shaped concave parts are distributed on the outer edge of the upper shell body in an annular array, and the first arc-shaped convex parts and the first arc-shaped concave parts are arranged adjacently; a first mounting cavity is arranged on the first arc-shaped protruding part in a penetrating mode and provided with internal threads; an annular mounting part protruding outwards is arranged in an inner cavity of the upper shell body, and four first screw holes are distributed in an annular array at the outer edge of the annular mounting part;
the first bolt penetrates through the upper mounting hole, the first screw hole, the fourth screw hole and the lower mounting hole to fasten the upper body shell, the lower body shell, the upper heat dissipation shell and the lower heat dissipation shell.
As a further scheme of the invention, the upper shell body is provided with a plurality of second screw holes; the bottom surface of the upper shell body is provided with a first mounting ring enclosed on the second screw hole, and four first wing folding areas are formed between the first mounting ring and the outer edge of the upper shell body.
As a further scheme of the invention, the lower machine body shell comprises a lower shell body, the lower shell body is in a similar ring shape with an inner cavity, four second arc-shaped protruding parts and four second arc-shaped recessed parts are distributed on the outer edge of the lower shell body in an annular array, the second arc-shaped protruding parts are arranged corresponding to the first arc-shaped protruding parts, and the second arc-shaped recessed parts are arranged corresponding to the first arc-shaped recessed parts; a second mounting cavity corresponding to the first mounting cavity is arranged on the second arc-shaped protruding part in a penetrating mode, and the second mounting cavity is provided with an internal thread; the lower shell body is provided with a plurality of third screw holes, and the third screw holes and the second screw holes are correspondingly arranged; the mounting plate is arranged at the outer edge of the cavity of the lower shell body, and the supporting area is arranged at the center of the cavity of the lower shell body; and a second mounting ring enclosed on the third screw hole is arranged on the bottom surface of the lower shell body.
As a further scheme of the invention, a flight controller, a power supply, a distribution board and a radio receiver are arranged in an area enclosed by the second mounting ring and the mounting plate, the power supply and the distribution board are electrically connected with the flight controller, and the radio receiver is in signal connection with the flight controller.
As a further scheme of the invention, four buffer cavities are arranged in the second mounting ring, and fourth screw holes corresponding to the first screw holes are arranged in the buffer cavities; four second wing folding areas are formed between the second mounting ring and the outer edge of the lower shell body.
As a further scheme of the invention, three fan-shaped mounting holes are arranged in the supporting area; and fan-shaped support columns for supporting the upper heat dissipation shell and the lower heat dissipation shell are correspondingly arranged in the fan-shaped mounting holes.
As a further scheme of the invention, the first buffer column penetrates through the bolt hole section of the arc-shaped folding plate and abuts against the second bolt, and the second buffer column abuts against the buffer cavity.
As a further scheme of the invention, the rotor assembly comprises a rotor, a sealing ring, reinforcing columns, a rotating shaft and a motor, wherein the motor penetrates through the bottom of a rotor mounting hole, the three arc-shaped reinforcing columns are arranged on the upper surface of the motor, the sealing ring is clamped outside an area enclosed by the reinforcing columns, one end of the rotating shaft penetrates through the rotating shaft mounting hole in the center of the motor, and the other end of the rotating shaft is connected with the rotor.
The invention also provides a working method of the portable foldable unmanned aerial vehicle, which comprises the following steps:
s1, before use, the four arc-shaped folding plates rotate around the bolt holes, so that the four wing assemblies are completely folded into the space between the first wing folding area and the second wing folding area, and only the fuselage assembly is shown as a whole; when the wing folding device is used, the four arc-shaped folding plates rotate around the bolt holes, so that the four wing assemblies completely rotate out of the space between the first wing folding area and the second wing folding area, and the second bolt and the nut are screwed tightly;
s2, power is turned on, the distribution board distributes the electric energy to the flight controller, the hand-held remote controller sends flight signals, the flight signals are received by the radio receiver and then fed back to the flight controller, the flight controller controls the motor to start, the motor drives the rotating shaft to rotate, the rotating shaft drives the rotor to rotate, and the lift force generated by the rotation of the rotor drives the unmanned aerial vehicle to fly upwards.
The invention has the beneficial effects that:
1. the portable foldable unmanned aerial vehicle comprises four wing assemblies, wherein the four wing assemblies are distributed on a fuselage assembly in an annular array manner, the wing assemblies are detachably connected with the fuselage assembly through bolts and nuts, the fuselage assembly comprises an upper fuselage shell, a lower fuselage shell, an upper heat dissipation shell and a lower heat dissipation shell, each wing assembly comprises an arc-shaped folding piece, a buffer assembly, a second bolt, a rotor wing assembly and a nut, a first installation ring enclosed on a second screw hole is arranged on the bottom surface of an upper shell body, and four first wing folding areas are formed between the first installation ring and the outer edge of the upper shell body; four second wing folding areas are formed between the second mounting ring and the outer edge of the lower shell body; the structural design of fuselage subassembly and wing subassembly for this unmanned aerial vehicle is rotatory around the bolt hole with four arc folded sheets when not using, and in four wing subassemblies are folded into the space in first wing folding zone and second wing folding zone completely, only present the fuselage subassembly on the whole, not only saved and placed the space, conveniently carry, the rotor can not take place to damage because of colliding with the hard thing in addition, has prolonged life.
2. Go up the heat dissipation casing and with a plurality of louvre designs on the heat dissipation casing down for the heat that produces in the electronic device working process such as power, panel, flight controller in time gives off, prevents to lead to the fact the circumstances that unmanned aerial vehicle control efficiency reduces, flight quality reduces because of gathering the heat.
3. The buffer components comprise buffer plates, first buffer columns and second buffer columns, the first buffer columns and the second buffer columns are respectively connected to two ends of the buffer plates, and the plurality of buffer components are horizontally stacked into a plurality of layers from top to bottom; the buffer plate, the first buffer column and the second buffer column are all made of elastic rubber materials; the design of the buffer assembly buffers the friction force of the arc-shaped folding plate on the upper body shell, the lower body shell and the second bolt in the folding process, and reduces the vibration generated in the flight process of the unmanned aerial vehicle; a plurality of lightening hole has not only alleviateed the weight of rotor subassembly, and flight in-process air current passes from the lightening hole, has reduced unmanned aerial vehicle's windage for the flight process is more stable.
Drawings
The invention will be further described with reference to the accompanying drawings.
Fig. 1 is a three-dimensional view of the portable foldable drone of the present invention.
Fig. 2 is a three-dimensional view of the portable and foldable drone of the present invention with the upper hull shell removed.
Figure 3 is a three-dimensional view of the wing assembly of the present invention.
Figure 4 is an exploded view of the wing assembly of the present invention.
Fig. 5 is a three-dimensional view of the upper housing shell of the present invention.
Fig. 6 is a bottom view of the upper housing shell of the present invention.
Fig. 7 is a top view of the lower body shell of the present invention.
Fig. 8 is a schematic structural view of an upper heat dissipation housing according to the present invention.
Fig. 9 is a schematic structural diagram of a lower heat dissipation housing according to the present invention.
Figure 10 is a schematic structural view of a fan-shaped support column.
In the figure: 100. a fuselage assembly; 110. an upper body shell; 111. an upper case body; 112. a first arcuate projection; 113. a first arcuate recess; 114. a first mounting cavity; 115. an annular mounting portion; 116. a first screw hole; 117. a second screw hole; 118. a first mounting ring; 119. a first wing fold area; 120. a lower body shell; 121. a lower case body; 122. a second arc-shaped convex part; 123. a second arcuate recess; 124. a second mounting cavity; 125. a third screw hole; 126. a second mounting ring; 127. a second wing fold region; 128. mounting a plate; 129. a support region; 130. an upper heat dissipation housing; 131. a fan-shaped mounting hole; 132. an upper heat dissipation hole; 133. an upper mounting hole; 134. a buffer chamber; 135. a fourth screw hole; 136. a first bolt; 140. a lower heat dissipation housing; 141. a central bore; 142. a lower heat dissipation hole; 143. a lower mounting hole; 150. a flight controller; 160. a power source; 170. a distribution board; 180. a radio receiver; 190. a fan-shaped support column; 200. a wing assembly; 210. an arc-shaped folding member; 211. an arc-shaped folding plate; 212. bolt holes; 213. a rotor wing mounting hole; 214. lightening holes; 220. a buffer assembly; 221. a buffer plate; 222. a first buffer column; 223. a second buffer column; 230. a second bolt; 240. a rotor assembly; 241. a rotor; 242. a seal ring; 243. a reinforcement column; 244. a rotating shaft; 245. a motor; 246. a rotating shaft mounting hole; 250. and (4) a nut.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1 to 10, the present embodiment provides a portable foldable unmanned aerial vehicle, which includes a fuselage assembly 100 and wing assemblies 200, wherein four wing assemblies 200 are distributed on the fuselage assembly 100 in an annular array, and the wing assemblies 200 are detachably connected to the fuselage assembly 100. When in use, the wing assembly 200 is placed in the fuselage assembly 100 after being rotated and folded, and is convenient to carry. The number of the wing assemblies 200 of the present embodiment is not limited to four, and may be six or eight.
Specifically, the body assembly 100 includes an upper body housing 110, a lower body housing 120, an upper heat dissipation housing 130, and a lower heat dissipation housing 140, wherein the upper body housing 110 is fixedly mounted on the top of the lower body housing 120, the upper body housing 110 and the lower body housing 120 both have a cavity therein, the upper heat dissipation housing 130 is mounted on the top of the cavity of the upper body housing 110, and the lower heat dissipation housing 140 is mounted on the bottom of the cavity of the lower body housing 120. Wherein, upper shell casing 110 includes upper shell body 111, and upper shell body 111 is the similar ring form that has the inner chamber, and the outer fringe annular array of upper shell body 111 distributes and has four first arc bellying 112 and four first arc depressed part 113, and first arc bellying 112 sets up with first arc depressed part 113 is adjacent. A first mounting cavity 114 is arranged on the first arc-shaped protruding part 112 in a penetrating mode, and the first mounting cavity 114 is provided with internal threads. An annular mounting part 115 protruding outwards is arranged in the inner cavity of the upper shell body 111, and four first screw holes 116 are distributed in an annular array on the outer edge of the annular mounting part 115. The upper shell body 111 is provided with a plurality of second screw holes 117. The bottom surface of the upper shell body 111 is provided with a first mounting ring 118 enclosed on the second screw hole 117, and four first wing folding areas 119 are formed between the first mounting ring 118 and the outer edge of the upper shell body 111.
The portable collapsible unmanned aerial vehicle of this embodiment, it is rotatory around bolt hole 212 with four arc folded sheet 211 when not using for in four wing subassembly 200 are folded into the space of first wing folding zone 119 and second wing folding zone 127 completely, only present fuselage subassembly 100 on the whole, not only saved and placed the space, conveniently carry, the rotor can not take place to damage because of colliding with hard thing and rubbing in addition, has prolonged life.
The central portion of the upper heat dissipation housing 130 is provided with a plurality of upper heat dissipation holes 132, and the outer edge of the upper heat dissipation housing 130 is provided with four upper mounting holes 133 distributed in a circumferential array. The central portion of the lower heat dissipation casing 140 is provided with a central hole 141, the periphery of the central hole 141 is provided with a plurality of lower heat dissipation holes 142, and the outer edge of the lower heat dissipation casing 140 is provided with four lower mounting holes 143 distributed in a circumferential array. The first bolt 136 passes through the upper mounting hole 133, the first screw hole 116, the fourth screw hole 135, and the lower mounting hole 143 to fasten the upper body case 110, the lower body case 120, the upper heat dissipation case 130, and the lower heat dissipation case 140. Go up heat dissipation casing 130 and heat dissipation casing 140's structural design down, a plurality of louvres make the heat that produces in the electronic device working process such as power 160, panel 170, flight controller 150 in time give off, prevent to lead to the fact the circumstances that unmanned aerial vehicle control efficiency reduces, flight quality reduces because of gathering the heat.
The working method of the portable foldable unmanned aerial vehicle comprises the following steps:
s1, before use, the four arc-shaped folding plates 211 are rotated around the bolt holes 212, so that the four wing assemblies 200 are completely folded into the space between the first wing folding area 119 and the second wing folding area 127, and only the fuselage assembly 100 is shown as a whole; in use, the four arc-shaped folding plates 211 are rotated around the bolt holes 212, so that the four wing assemblies 200 are completely rotated out of the space between the first wing folding area 119 and the second wing folding area 127, and the second bolts 230 and the nuts 250 are tightened;
s2, power supply 160 is turned on, distribution board 170 distributes electric energy to flight controller 150, the hand-held remote controller sends flight signals, flight signals are received by radio receiver 180 and then fed back to flight controller 150, flight controller 150 controls motor 245 to start, motor 245 drives rotating shaft 244 to rotate, rotating shaft 244 drives rotor 241 to rotate, and the lift force generated by rotation of rotor 241 drives the unmanned aerial vehicle to fly upwards.
In the description herein, references to the description of "one embodiment," "an example," "a specific example" or the like are intended to mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The foregoing is illustrative and explanatory only and is not intended to be exhaustive or to limit the invention to the precise embodiments described, and various modifications, additions, and substitutions may be made by those skilled in the art without departing from the scope of the invention or exceeding the scope of the claims.
Claims (10)
1. A portable foldable unmanned aerial vehicle comprises a fuselage assembly (100) and wing assemblies (200), wherein the four wing assemblies (200) are distributed on the fuselage assembly (100) in an annular array manner, and is characterized in that the fuselage assembly (100) comprises an upper fuselage shell (110), a lower fuselage shell (120), an upper heat dissipation shell (130) and a lower heat dissipation shell (140), wherein the upper fuselage shell (110) is fixedly arranged at the top of the lower fuselage shell (120), cavities are formed in the upper fuselage shell (110) and the lower fuselage shell (120), the upper heat dissipation shell (130) is arranged at the top of the cavity of the upper fuselage shell (110), and the lower heat dissipation shell (140) is arranged at the bottom of the cavity of the lower fuselage shell (120);
the central part of the upper heat dissipation shell (130) is provided with a plurality of upper heat dissipation holes (132), and the outer edge of the upper heat dissipation shell (130) is provided with four upper mounting holes (133) distributed in a circumferential array; a central hole (141) is formed in the center of the lower radiating shell (140), a plurality of lower radiating holes (142) are formed in the periphery of the central hole (141), and four lower mounting holes (143) distributed in a circumferential array are formed in the outer edge of the lower radiating shell (140);
the wing assembly (200) comprises an arc-shaped folding piece (210), a buffer assembly (220), a second bolt (230), a rotor wing assembly (240) and a nut (250), wherein the arc-shaped folding piece (210) comprises an arc-shaped folding plate (211), a bolt hole (212) is formed in one end of the arc-shaped folding plate (211), a rotor wing mounting hole (213) is formed in the other end of the arc-shaped folding plate (211), and a plurality of lightening holes (214) are formed between the bolt hole (212) and the rotor wing mounting hole (213); the buffer components (220) comprise buffer plates (221), first buffer columns (222) and second buffer columns (223), the first buffer columns (222) and the second buffer columns (223) are respectively connected to two ends of the buffer plates (221), and the buffer components (220) are horizontally stacked into a plurality of layers from top to bottom; the second bolt (230) passes through the first mounting cavity (114), the bolt hole (212) and the second mounting cavity (124) and then is fastened through a nut (250).
2. The portable foldable unmanned aerial vehicle of claim 1, wherein the upper body housing (110) comprises an upper housing body (111), the upper housing body (111) is in a ring-like shape with an inner cavity, four first arc-shaped protrusions (112) and four first arc-shaped recesses (113) are distributed in an annular array on the outer edge of the upper housing body (111), and the first arc-shaped protrusions (112) and the first arc-shaped recesses (113) are arranged adjacently; a first mounting cavity (114) penetrates through the first arc-shaped protruding part (112), and the first mounting cavity (114) is provided with internal threads; an annular mounting part (115) protruding outwards is arranged in an inner cavity of the upper shell body (111), and four first screw holes (116) are distributed in an annular array at the outer edge of the annular mounting part (115);
the first bolt (136) passes through the upper mounting hole (133), the first screw hole (116), the fourth screw hole (135) and the lower mounting hole (143) to fasten the upper body case (110), the lower body case (120), the upper heat dissipation case (130) and the lower heat dissipation case (140).
3. The portable foldable unmanned aerial vehicle of claim 2, wherein the upper shell body (111) is provided with a plurality of second screw holes (117); the bottom surface of the upper shell body (111) is provided with a first mounting ring (118) enclosed on the second screw hole (117), and four first wing folding areas (119) are formed between the first mounting ring (118) and the outer edge of the upper shell body (111).
4. The portable foldable unmanned aerial vehicle of claim 1, wherein the lower body housing (120) comprises a lower shell body (121), the lower shell body (121) is in a ring-like shape with an inner cavity, four second arc-shaped protrusions (122) and four second arc-shaped recesses (123) are distributed in an annular array on the outer edge of the lower shell body (121), the second arc-shaped protrusions (122) are arranged corresponding to the first arc-shaped protrusions (112), and the second arc-shaped recesses (123) are arranged corresponding to the first arc-shaped recesses (113); a second mounting cavity (124) corresponding to the first mounting cavity (114) penetrates through the second arc-shaped protruding part (122), and the second mounting cavity (124) is provided with internal threads; a plurality of third screw holes (125) are formed in the lower shell body (121), and the third screw holes (125) and the second screw holes (117) are correspondingly arranged; the outer edge of the cavity of the lower shell body (121) is provided with a mounting plate (128), and the central part of the cavity of the lower shell body (121) is provided with a supporting area (129); and a second mounting ring (126) enclosed on the third screw hole (125) is arranged on the bottom surface of the lower shell body (121).
5. The portable and foldable unmanned aerial vehicle of claim 4, wherein the second mounting ring (126) and the mounting plate (128) enclose an area in which a flight controller (150), a power supply (160), a power board (170) and a radio receiver (180) are arranged, the power supply (160) and the power board (170) are electrically connected with the flight controller (150), and the radio receiver (180) is in signal connection with the flight controller (150).
6. A portable foldable drone according to claim 4, characterised in that four buffer chambers (134) are provided in the second mounting ring (126), fourth screw holes (135) corresponding to the first screw holes (116) being provided in the buffer chambers (134); four second wing folding areas (127) are formed between the second mounting ring (126) and the outer edge of the lower shell body (121).
7. Portable foldable drone according to claim 4, characterised in that three sector-shaped mounting holes (131) are provided in the support area (129); and fan-shaped supporting columns (190) for supporting the upper heat dissipation shell (130) and the lower heat dissipation shell (140) are correspondingly arranged in the fan-shaped mounting holes (131).
8. A portable foldable drone according to claim 1, characterised in that the first buffer column (222) passes through the section of bolt hole (212) of the arc-shaped folding plate (211) and abuts on the second bolt (230), the second buffer column (223) abutting inside the buffer chamber (134).
9. The portable foldable unmanned aerial vehicle of claim 1, wherein the rotor assembly (240) comprises a rotor (241), a sealing ring (242), a reinforcing column (243), a rotating shaft (244) and a motor (245), the motor (245) penetrates from the bottom of the rotor mounting hole (213), the three arc-shaped reinforcing columns (243) are arranged on the upper surface of the motor (245), the sealing ring (242) is clamped outside an area enclosed by the reinforcing columns (243), one end of the rotating shaft (244) penetrates through the rotating shaft mounting hole (246) in the center of the motor (245), and the other end of the rotating shaft is connected with the rotor (241).
10. A working method of a portable foldable unmanned aerial vehicle is characterized by comprising the following steps:
s1, before use, the four arc-shaped folding plates (211) are rotated around the bolt holes (212), so that the four wing assemblies (200) are completely folded into the space between the first wing folding area (119) and the second wing folding area (127), and only the fuselage assembly (100) is shown as a whole; when in use, the four arc-shaped folding plates (211) are rotated around the bolt holes (212), so that the four wing assemblies (200) are completely rotated out of the space between the first wing folding area (119) and the second wing folding area (127), and the second bolts (230) and the nuts (250) are screwed;
s2, power (160) is turned on, distribution panel (170) distribute electric energy to flight controller (150), handheld remote controller sends flight signal, flight signal feeds back to flight controller (150) after receiving through radio receiver (180), flight controller (150) control motor (245) start, motor (245) drive pivot (244) rotate, pivot (244) drive rotor (241) rotate, rotor (241) rotate the lift that produces and drive unmanned aerial vehicle flight upwards.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010246365.8A CN111377049A (en) | 2020-03-31 | 2020-03-31 | Portable foldable unmanned aerial vehicle and working method thereof |
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| CN202010246365.8A CN111377049A (en) | 2020-03-31 | 2020-03-31 | Portable foldable unmanned aerial vehicle and working method thereof |
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| CN111377049A true CN111377049A (en) | 2020-07-07 |
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