CN106956772B

CN106956772B - Foldable unmanned aerial vehicle and implementation method thereof

Info

Publication number: CN106956772B
Application number: CN201710246316.2A
Authority: CN
Inventors: 马宇尘
Original assignee: Shanghai Liangming Technology Development Co Ltd
Current assignee: Shanghai Liangming Technology Development Co Ltd
Priority date: 2017-04-15
Filing date: 2017-04-15
Publication date: 2023-07-21
Anticipated expiration: 2037-04-15
Also published as: CN106956772A

Abstract

The invention discloses a foldable unmanned aerial vehicle and an implementation method thereof, and relates to the technical field of unmanned aerial vehicles. A foldable unmanned aerial vehicle comprising an unmanned aerial vehicle body and a rotor section, the rotor section comprising at least a first rotor module and a second rotor module connected by a flexible material for relative folding or unfolding; in the deployed state of the first rotor module and the second rotor module, the drone body is positioned at a flexible material location as a rigid support between the first rotor module and the second rotor module. The unmanned aerial vehicle is simple and light in structure, and portability of the unmanned aerial vehicle is improved.

Description

Foldable unmanned aerial vehicle and implementation method thereof

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a foldable unmanned aerial vehicle.

Background

Unmanned aircraft is called "unmanned aircraft" for short, and is an unmanned aircraft operated by radio remote control equipment and/or self program control device, and it was first in the 40 th century of 20 th. The unmanned aerial vehicle has wide application, low cost and good efficiency and cost ratio, has extremely important effect in modern war and has wider prospect in civil field. Currently, unmanned aerial vehicles are widely applied to the fields of police, city management, agriculture, geology, weather, electric power, rescue and relief work, video shooting and the like.

In the prior art, some fixed-wing unmanned aerial vehicles may have only one rotor wing, and some helicopter unmanned aerial vehicles may have two or more rotor wings; as known from the mechanical properties of the rotors, each rotor generates a change in the surrounding air flow by rotating, thereby creating lift, and therefore each rotor requires a certain amount of independent space to create lift.

The multi-rotor unmanned aerial vehicle generally adopts a symmetrical distribution mode, and realizes the control of the rotor unmanned aerial vehicle by controlling the differential acting force generated by rotors in different directions. However, the body of the unmanned aerial vehicle with the multi-rotor structure occupies a large area space, and brings trouble to transportation and storage.

Currently, foldable unmanned aerial vehicles have also appeared so that the unmanned aerial vehicle can be folded when not in use, to improve portability of the unmanned aerial vehicle. For example, CN201520580644.2, entitled a foldable unmanned aerial vehicle, provides a hinge type rotor folding solution, which takes a machine body as a central line, and two rotors on two sides are formed into a pair, and a hinge structure is formed by connecting ends on the machine body. However, this approach still suffers from drawbacks: firstly, the weight of the loose-leaf increases the kinetic energy consumed during the operation of the unmanned aerial vehicle, and influences the cruising ability during the operation; secondly, because a piece of loose-leaf that every two rotor constitutes, its link that is located on the main part is a mode of accomplishing fixedly through two upper and lower gears, consequently, just can appear because two upper and lower gears wearing and tearing degree on a piece of loose-leaf are different for long-time the use, cause the unusual rocking of during operation loose-leaf.

Also for example, patent CN201410216866.6, entitled folding rotor type unmanned aerial vehicle, provides a foldable unmanned aerial vehicle having only two rotors. The problem that it exists is, in order to fix its rotor arm after folding, needs the great organism of design volume, and the fixed of rotor after folding just can be realized to this organism and the spacing locking piece cooperation work of F type of its design, and the direct result of bringing is the increase of unmanned aerial vehicle overall weight, influences the duration of during operation.

In view of this, overcoming the drawbacks of the prior art is a problem to be solved in the art.

Disclosure of Invention

The invention aims at: the invention overcomes the defects of the prior art, and provides the foldable unmanned aerial vehicle and the implementation method thereof.

In order to achieve the above object, the present invention provides the following technical solutions:

a foldable unmanned aerial vehicle comprising an unmanned aerial vehicle body and a rotor section, the rotor section comprising at least a first rotor module and a second rotor module connected by a flexible material for relative folding or unfolding; in the deployed state of the first rotor module and the second rotor module, the drone body is positioned at a flexible material location as a rigid support between the first rotor module and the second rotor module.

Further, the flexible material is one or a combination of a wire, a strip and a sheet flexible structure.

Further, be provided with a location structure in the unmanned aerial vehicle main part, the one end movable mounting of unmanned aerial vehicle main part is between first rotor module and second rotor module, and the other end can rotate for the aforesaid end, under the state that first rotor module and second rotor module were expanded, unmanned aerial vehicle main part respectively with the first rotor module and the second rotor module fixed connection of both sides through a location structure.

And a second positioning structure can be further arranged on the unmanned aerial vehicle body, and the second positioning structure is used for fixing the unmanned aerial vehicle body on the flexible material.

Preferably, the first positioning structure is a protrusion or a groove arranged on two sides of the unmanned aerial vehicle main body, and grooves or protrusions matched with the protrusions or the grooves are arranged on opposite sides of the first rotor wing module and the second rotor wing module; the second positioning structure is a magnetic adsorption structure or an adhesive sheet, and a magnetic base material or an adhesive base material is arranged at the corresponding position of the flexible material.

Further, the width of the flexible material can be adjusted according to the distance between the first rotor module and the second rotor module.

Further, the unmanned aerial vehicle further comprises a battery module capable of conducting charging operation for the electric equipment.

Preferably, the unmanned aerial vehicle comprises a third rotor wing module and a fourth rotor wing module, wherein the first rotor wing module and the third rotor wing module are arranged on one side of the unmanned aerial vehicle body, and the second rotor wing module and the fourth rotor wing module are arranged on the other side of the unmanned aerial vehicle body; the battery module is arranged between the first rotor module and the third rotor module and/or between the second rotor module and the fourth rotor module.

Further, each rotor module has a plurality of rotors.

Further, under first rotor module and the second rotor module expansion state, unmanned aerial vehicle main part is arranged in the space that flexible material, first rotor module and second rotor module formed, first rotor module, second rotor module can expand to be in the coplanar with the unmanned aerial vehicle main part.

Further, under the first rotor module and the second rotor module folded condition, the unmanned aerial vehicle main part is located the side of first rotor module and second rotor module.

Further, the rotor module includes the rotor and has the protective housing of cavity, the protective housing is the casing of fretwork, the rotor is installed in the cavity of protective housing.

Further, form sliding construction between rotor module and unmanned aerial vehicle main part through protruding and recess of matching between the side of first rotor module and second rotor module, push in or take out unmanned aerial vehicle main part through the mode of pull.

Further, be provided with the controller in the unmanned aerial vehicle main part, unmanned aerial vehicle operation in-process, the controller is connected or wireless connection with rotor module electricity, through the work of controller control rotor module.

Further, the first location structure is magnetic adsorption structure, and unmanned aerial vehicle main part passes through magnetic adsorption effect and first rotor module and second rotor module fixed connection.

Further, be provided with locking structure on the rotor portion for under the relative expansion of first rotor module and second rotor module is located the circumstances of coplanar, carry out the locking to the relative motion of first rotor module and second rotor module, keep both to be located the coplanar.

The invention also provides a realization method of the foldable unmanned aerial vehicle, which comprises the following steps: the unmanned aerial vehicle comprises an unmanned aerial vehicle main body and a rotor wing part, wherein the rotor wing part comprises at least a first rotor wing module and a second rotor wing module which are connected through flexible materials so as to be relatively folded or unfolded;

when the unmanned aerial vehicle is used, the first rotor wing module and the second rotor wing module are unfolded, and the unmanned aerial vehicle main body is adjusted to be located at the position of the flexible material and used as a rigid support between the first rotor wing module and the second rotor wing module.

Further, when the first rotor module and the second rotor module are relatively unfolded to be located on the same plane, the relative movement of the first rotor module and the second rotor module is locked through the locking structure arranged on the rotor part, and the first rotor module and the second rotor module are kept to be located on the same plane.

Compared with the prior art, the invention has the following advantages and positive effects by taking the technical scheme as an example: in the invention, the rotor wing modules are connected through the light flexible material, so that the rotor wing modules can be folded or unfolded through the flexible material; when the unmanned aerial vehicle is used for working, the unmanned aerial vehicle main body can be installed at the position of the flexible material to serve as a rigid support between the first rotor wing module and the second rotor wing module, and a complete unmanned aerial vehicle structure is formed after assembly, so that the unmanned aerial vehicle is simple and light in structure and convenient for a user to carry and use. Further, unmanned aerial vehicle can also charge the operation to the consumer.

Drawings

Fig. 1 is a schematic structural diagram of a foldable unmanned aerial vehicle according to an embodiment of the present invention when the foldable unmanned aerial vehicle is unfolded.

Fig. 2 to 5 are operation example diagrams for folding the foldable unmanned aerial vehicle in the foregoing embodiment.

Fig. 6 to 7 are schematic structural views of a foldable unmanned aerial vehicle having a charging function.

Fig. 8 to 11 are schematic diagrams illustrating assembly and disassembly operations of another foldable unmanned aerial vehicle according to an embodiment of the present invention.

Fig. 12 is a schematic structural view of a rotor section with a locking structure according to an embodiment of the present invention.

Reference numerals illustrate:

the unmanned plane 100; a first rotor module 110, a hollowed hole 111; the second rotor module 120, the hollow hole 121 and the locking structure 122; the unmanned aerial vehicle comprises an unmanned aerial vehicle main body 130, an elastic connecting piece 131 and a connecting belt 132; a flexible material 140; a first positioning structure 150; the first positioning structure matches the positioning structure 160; a third rotor module 170; a fourth rotor module 180; and a battery module 190.

Detailed Description

The foldable unmanned aerial vehicle and the implementation method thereof disclosed by the invention are further described in detail below with reference to the accompanying drawings and specific embodiments. It should be noted that the technical features or combinations of technical features described in the following embodiments should not be regarded as being isolated, and they may be combined with each other to achieve a better technical effect. In the drawings of the embodiments described below, like reference numerals appearing in the various drawings represent like features or components and are applicable to the various embodiments. Thus, once an item is defined in one drawing, no further discussion thereof is required in subsequent drawings.

It should be noted that the structures, proportions, sizes, etc. shown in the drawings are merely used in conjunction with the disclosure of the present specification, and are not intended to limit the applicable scope of the present invention, but rather to limit the scope of the present invention. The scope of the preferred embodiments of the present invention includes additional implementations in which functions may be performed out of the order described or discussed, including in a substantially simultaneous manner or in an order that is reverse, depending on the function involved, as would be understood by those of skill in the art to which embodiments of the present invention pertain.

Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values.

Examples

Fig. 1 shows a foldable unmanned aerial vehicle according to an embodiment of the present invention.

A foldable drone 100 includes a drone body 130 and a rotor section.

The rotor section includes at least a first rotor module 110 and a second rotor module 120, with the first rotor module 110 and the second rotor module 120 being connected therebetween by a flexible material 140 for relative folding or unfolding.

In the deployed state of the first rotor module 110 and the second rotor module 120, the drone body 130 is positioned at the location of the flexible material 140 as a rigid support between the first rotor module 110 and the second rotor module 120. So, assemble unmanned aerial vehicle main part 130 and first rotor module 110, second rotor module 120 into complete unmanned aerial vehicle structure, after starting unmanned aerial vehicle's switch, unmanned aerial vehicle gets into the operation.

Preferably, be provided with the controller in the unmanned aerial vehicle main part, corresponding, can set up shift knob on unmanned aerial vehicle main part shell, the user starts or closes unmanned aerial vehicle through triggering shift knob. In the unmanned aerial vehicle operation process, the controller is connected with rotor module electricity or wireless connection, through the work of controller control rotor module.

The first rotor module 110, the second rotor module 120 comprises at least one rotor, i.e. the inventive drone may comprise more than two rotors. In fig. 1, the first rotor module 110 and the second rotor module 120 are illustrated as having 2 rotors, respectively, that is, the unmanned aerial vehicle has a four-rotor structure.

In this embodiment, the flexible material may be one or a combination of a wire, a strip, and a sheet-shaped flexible structure, as shown in fig. 2.

In particular arrangements, the flexible material may be, by way of example and not limitation, a wire, a ribbon or a woven cloth made of high strength fibers; and can also be a chain, a flexible plastic sheet, a rubber sheet or a flexible metal sheet, etc.

Preferably, one end of the unmanned aerial vehicle body 130 is movably mounted between the first rotor module 110 and the second rotor module 120, and the other end thereof is rotatable relative to the end. In particular arrangements, by way of example and not limitation, the unmanned aerial vehicle body 130 may be mounted between the first rotor module 110 and the second rotor module 120 via the elastic connection 131.

The elastic connection 131 may be deformed to some extent when being stressed, thereby allowing the unmanned aerial vehicle body 130 to rotate around the end where the elastic connection 131 is located. When installed, the elastic connection 131 may be installed on the first rotor module 110 and the second rotor module 120, or may be installed on the flexible material 140.

Of course, the movable mounting may also be achieved by a hinge shaft, a connecting strap, etc., which should not be taken as a limitation of the movable mounting.

To facilitate assembly of the unmanned aerial vehicle body 130 with each rotor module, the unmanned aerial vehicle body 130 is provided with a first positioning structure 150, as shown in fig. 2. In a state where the first rotor module 110 and the second rotor module 120 are unfolded (as shown in fig. 1), the unmanned aerial vehicle body 130 is fixedly connected with the first rotor module 110 and the second rotor module 120 on both sides, respectively, through the first positioning structure 150.

The first positioning structure 150 may be a magnetic adsorption structure, and the unmanned aerial vehicle body 130 is fixedly connected with the first rotor module 110 and the second rotor module 120 through magnetic adsorption. When specifically setting up, the first location structure 150 can adopt the magnetite, and be in the side of first rotor module 110, second rotor module 120 sets up corresponding magnetism substrate and matches location structure 160 as first location structure, through the magnetism adsorption between magnetite and the magnetism substrate, is fixed in the both sides of unmanned aerial vehicle main part respectively with first rotor module and second rotor module. Of course, the matching of the first positioning structure with the positioning structure 160 is not an essential feature, and when the sides of the first rotor module 110 and the second rotor module 120 are made of metal materials, the first rotor module and the second rotor module can generate magnetic attraction with the magnets.

The first positioning structure 150 may also be a protrusion or a groove disposed on two sides of the main body of the unmanned aerial vehicle; at this time, opposite sides of the first rotor module 110 and the second rotor module 120 are provided with grooves or protrusions matching the aforementioned protrusions or grooves, which serve as first positioning structure matching positioning structures 160.

In this embodiment, the unmanned aerial vehicle body 130 may further be provided with a second positioning structure, where the second positioning structure is used to fix the unmanned aerial vehicle body 130 on the flexible material 140.

Through the second positioning structure, a user can conveniently position the unmanned aerial vehicle main body 130 on the flexible material 140 in the unmanned aerial vehicle assembling process; when folding unmanned aerial vehicle's rotor module, second location structure can also conveniently fix unmanned aerial vehicle main part 130 on flexible material 140, and the user of being convenient for accomodates. Preferably, the second positioning structure may be a magnetic adsorption structure or an adhesive sheet, and a magnetic substrate or an adhesive substrate is disposed at a corresponding position of the flexible material.

An operation example of folding the unmanned aerial vehicle of the present invention will be described with reference to fig. 2 to 5. Referring to fig. 2, when a user needs to fold the unmanned aerial vehicle 100 to carry after using the unmanned aerial vehicle 100, a certain external force may be applied to one end of the unmanned aerial vehicle body 130. Under the action of external force, the unmanned aerial vehicle main body 130 overcomes the friction resistance between the first positioning structure 150 and the first positioning structure matching positioning structure 160, and starts to rotate around the other end of the unmanned aerial vehicle main body.

Referring to fig. 3, the unmanned aerial vehicle body 130 is not located between the first rotor module 110 and the second rotor module 120 after being rotated 180 degrees by the elastic connection member 131.

Referring to fig. 4, the user may then fold the first rotor module 110 and the second rotor module 120 relative to each other until the first rotor module 110 and the second rotor module 120 are folded. Preferably, the first rotor module 110 and the second rotor module 120 are provided with matched fastening structures or magnetic adsorption structures, and after the first rotor module and the second rotor module are folded, the first rotor module and the second rotor module can be fixed by the fastening structures or the magnetic adsorption structures.

After the first rotor module 110 and the second rotor module 120 are folded, the unmanned aerial vehicle body 130 continues to rotate according to the previous rotation motion until the unmanned aerial vehicle body 130 is located on the side surfaces of the first rotor module 110 and the second rotor module 120 and is attached to the flexible material 140, as shown in fig. 5. Then, the unmanned aerial vehicle body 130 and the flexible material 140 may be fixedly connected through the second positioning structure.

Preferably, in the deployed state, the first rotor module 110 and the second rotor module 120 are located in a space formed by the flexible material 140, the first rotor module 110 and the second rotor module 120, and the first rotor module 110 and the second rotor module 120 can be deployed to be in the same plane with the unmanned aerial vehicle body 130. The first rotor module 110 and the second rotor module 120 are capable of being deployed to lie in a same plane as the bottom, top, and/or central axes of the main unmanned aerial vehicle 130. Referring to fig. 1, due to the design in size, after the unmanned aerial vehicle is deployed, the lower bottom surface of the unmanned aerial vehicle body 130 is tightly attached to the upper surface of the flexible material 140, and the upper top surfaces of the first rotor module 110, the second rotor module 120 and the unmanned aerial vehicle body 130 are located on the same plane. By the structure, the flatness of the unmanned aerial vehicle can be improved, and the flight resistance is reduced.

Further, the first rotor module 110 and the second rotor module 120 are in a folded state, the unmanned aerial vehicle body 130 is located on the side surfaces of the first rotor module 110 and the second rotor module 120, and the unmanned aerial vehicle body 130 is tightly attached to the lower surface of the flexible material 140, as shown in fig. 5. The structure is convenient for users to place, pack and carry.

Preferably, the rotor module comprises a rotor and a protective shell with a hollow cavity, wherein the protective shell is a hollowed shell, and the rotor is arranged in the hollow cavity of the protective shell. Referring to fig. 5, a hollow hole 111 is provided on the protective housing of the first rotor module 110, and a hollow hole 121 is provided on the protective housing of the second rotor module 120. By the structure, the influence of the outer shell on the running of the rotor wing structure is reduced, and meanwhile, the weight of the unmanned aerial vehicle is reduced.

Fig. 2 to 5 illustrate operations of folding the unmanned aerial vehicle, and operations of unfolding the unmanned aerial vehicle may be performed in reverse order, which will not be described herein.

The above-described folding and unfolding modes are exemplary and not limiting. Specifically, for example, when folding, the first rotor module 110 and the second rotor module 120 may be folded in opposite directions, and the unmanned aerial vehicle body 130 may be rotated in opposite directions. In the folded state, the unmanned aerial vehicle body 130 may be located on the long sides of the first rotor module 110 and the second rotor module 120, or on the short sides of the long sides of the first rotor module 110 and the second rotor module 120 (the long sides may be the same as or similar to the short sides in length).

Preferably, the width of the flexible material is adjustable according to the distance between the first rotor module and the second rotor module. By way of example and not limitation, a spooler may be provided within the first rotor module and/or the second rotor module, the flexible material being wound around a spool of the spooler, the flexible material extending from the spooler and the width of the flexible material increasing when a user applies a separating force to the first rotor module and the second rotor module. The reel is provided with a rotary button, and the user triggers the rotary button, so that the flexible material can be retracted into the reel.

In another embodiment of the present invention, referring to fig. 6 to 7, the unmanned aerial vehicle 100 further includes a battery module capable of performing a charging operation for the electric device.

Preferably, the drone 100 includes a drone body 130 and a rotor section that includes a first rotor module 110, a second rotor module 120, a third rotor module 170, and a fourth rotor module 180. Each rotor module may have one or more rotors.

The first, three rotor modules set up in the one side of unmanned aerial vehicle main part 130, and the second, four rotor modules set up in the opposite side of unmanned aerial vehicle main part 130.

The drone 100 also includes a battery module 190. The battery module 190 may be disposed between the first and third rotor modules and/or between the second and fourth rotor modules. Referring to fig. 6, battery module 190 is disposed between the first and third rotor modules and between the second and fourth rotor modules.

Preferably, referring to fig. 7, the first rotor module 110, the second rotor module 120, the third rotor module 170, and the fourth rotor module 180 are all connected by a flexible material 140. The battery module 190 may be secured between the first and third rotor modules and between the second and fourth rotor modules by a positioning structure. And the unmanned aerial vehicle body 130 is fixed between the first and third rotor modules and the second and fourth rotor modules by the first positioning structure. The drone body 130, battery module 190, form a rigid support between the rotor modules. So, unmanned aerial vehicle main part 130 assembles complete unmanned aerial vehicle structure with each rotor module, starts unmanned aerial vehicle's switch back, and unmanned aerial vehicle gets into the operation.

The battery module 190 is capable of performing a charging operation for a powered device. By way of example and not limitation, the battery module 190 may include an electrical storage structure. The electricity storage structure refers to a structure capable of storing electricity and supplying power, and is a common electricity storage structure such as various mobile power sources (charging devices). The electricity storage unit can be a liquid Lithium Ion Battery (Liquified Lithium-Ion Battery, abbreviated as LIB), a Polymer Lithium Ion Battery (Polymer Lithium-Ion Battery, abbreviated as PLB), a Plastic Lithium Ion Battery (PLB), a dry Battery, an alkaline Battery, an acid Battery, a fuel Battery and other chemical Batteries, a solar Battery, a nuclear Battery or other physical Batteries.

In this embodiment, the electric device may be a computing terminal device. Preferably, it is a mobile computing terminal such as various wireless car terminals, wireless hand-held terminals. By way of example and not limitation, such as a cell phone, tablet computer, portable laptop computer, drone, smart watch, and the like.

The battery module 190 may output electric energy to the electric device, which may be wireless charging or wired charging.

The wireless charging technology (Wireless charging technology) is derived from a wireless power transmission technology, and the currently mainstream wireless charging technology in the market mainly adopts the following three modes: electromagnetic induction, radio waves, resonance. For low-power wireless charging, electromagnetic induction is generally adopted; for high power wireless charging, a resonant device is typically employed that transfers energy from a power supply (charger) to a powered device that uses the received energy to charge a battery and at the same time to operate itself.

When the electric energy is output in a wireless manner, preferably, a charging induction structure for generating the electric energy in a wireless manner and charging the electric equipment is arranged on the battery module 190. The charging induction structure can output electric energy in a wireless mode to charge electric equipment, such as a magnetic induction mode, a microwave induction mode and the like.

When the wired charging is adopted, preferably, an external charging interface and an interface docking structure are arranged on the electricity storage structure, and the interface docking structure can be used for connecting the external charging interface with a charging connector of electric equipment after the unmanned aerial vehicle is at a fixed position relative to the electric equipment, and the circuit is connected for carrying out charging operation.

In another embodiment of the present invention, another foldable drone is provided.

Referring to fig. 8, a sliding structure is formed between the rotor module and the main body of the unmanned aerial vehicle through the matched protrusions and recesses, and the main body of the unmanned aerial vehicle is pushed in or pulled out through a drawing manner between the sides of the first rotor module and the second rotor module. In specific implementation, by way of example and not limitation, the unmanned aerial vehicle main body 130 is provided with a first positioning structure 150, and the first positioning structure 150 is a protrusion disposed on two sides of the unmanned aerial vehicle main body; meanwhile, opposite sides of the first rotor module 110 and the second rotor module 120 are provided with grooves matched with the aforementioned protrusions, and the grooves may be used as first positioning structures to match the positioning structures 160.

In the unfolded state of the first rotor module 110 and the second rotor module 120, the unmanned aerial vehicle body 130 can be pushed in by means of drawing between the sides of the first rotor module 110 and the second rotor module 120, and the unmanned aerial vehicle body 130 is used as a rigid support for the first rotor module 110 and the second rotor module 120, and an operation example is shown in fig. 8, 9 and 10. In this manner, the first rotor module 110, the second rotor module 120, and the unmanned aerial vehicle body 130 may be fixedly connected. After the power switch of the unmanned aerial vehicle is started, the unmanned aerial vehicle can enter into operation.

The unmanned aerial vehicle main part can be provided with the controller in, corresponds, can set up shift knob on unmanned aerial vehicle main part shell, and the user starts or closes unmanned aerial vehicle through triggering shift knob. In the unmanned aerial vehicle operation process, the controller is connected with rotor module electricity or wireless connection, through the work of controller control rotor module.

Preferably, the unmanned aerial vehicle main body 130 and the rotor wing part of the unmanned aerial vehicle are connected through a connecting belt 132. The connecting belt 132 is used for connecting the unmanned aerial vehicle main body and the rotor wing part, and the length of the connecting belt can be adjusted according to the requirement.

Specifically, a reel may be provided on the rotor portion, and the ribbon of the connection strap 132 may be wound around the reel. The reel swivel may be controlled to retract the connection strap 132 without requiring the connection strap 132 to perform a connection function, such as where the drone body 130 is already installed between the first rotor module 110 and the second rotor module 120, as shown in fig. 10.

After the use of the unmanned aerial vehicle, when the user needs to store the unmanned aerial vehicle, the unmanned aerial vehicle main body 130 can be pulled out from the side surfaces of the first rotor module 110 and the second rotor module 120, and at this time, the connecting belt 132 also extends from the reel, as shown in fig. 11.

After the main drone body 130 is completely withdrawn, the user may fold the first rotor module 110 and the second rotor module 120 until the first rotor module 110 and the second rotor module 120 are folded.

Preferably, in order to facilitate the user to install the unmanned aerial vehicle body 130 in the unfolded state of the first rotor module 110 and the second rotor module 120, a locking structure may be further provided on the rotor part.

The locking structure is configured to lock the relative movement of the first rotor module 110 and the second rotor module 120 when the first rotor module 110 and the second rotor module 120 are relatively unfolded and located on the same plane, so as to keep the first rotor module 110 and the second rotor module 120 on the same plane, thereby facilitating the installation of the unmanned aerial vehicle body 130 by a user.

The locking structure plays a role of rotation limitation, and can limit the rotation angle of the first rotor module 110 and the second rotor module 120. Referring to fig. 12, by way of example and not limitation, the locking structure 122 may be a stop block or stop bar or stop plate secured to the second rotor module 120. The locking structure 122 may be extended or retracted relative to the housing of the second rotor module 120 (extension or retraction may be accomplished by rotation or folding).

Before the folded first rotor module 110 and the folded second rotor module 120 are unfolded, the locking structure 122 can be extended relative to the second rotor module 120, and the length of the extended locking structure 122 is longer than the width of the flexible material and extends to the position where the first rotor module 110 is located.

Then, the first rotor module 110 and the second rotor module 120 are unfolded, and when the first rotor module 110 and the second rotor module 120 are unfolded 180 degrees to be located on the same plane due to the blocking of the locking structure 122, the first rotor module 110 and the second rotor module 120 cannot continue to rotate, so that they can be kept on the same plane.

It should be noted that the above locking structure is by way of example and not limitation, and the locking structure may be any structure capable of performing rotation limitation. For example, the locking structure may be a self-locking hinge installed between the first rotor module 110 and the second rotor module 120, and the locking may be performed when the hinge is unfolded to a certain angle.

The invention further provides a realization method of the foldable unmanned aerial vehicle. The unmanned aerial vehicle comprises an unmanned aerial vehicle main body and a rotor wing part, wherein the rotor wing part comprises at least a first rotor wing module and a second rotor wing module which are connected through flexible materials so as to be relatively folded or unfolded; when the unmanned aerial vehicle is used, the first rotor wing module and the second rotor wing module are unfolded, and the unmanned aerial vehicle main body is adjusted to be located at the position of the flexible material and used as a rigid support between the first rotor wing module and the second rotor wing module. So, assemble unmanned aerial vehicle main part and first rotor module, second rotor module into complete unmanned aerial vehicle structure, after starting unmanned aerial vehicle's switch, unmanned aerial vehicle gets into the operation.

The first rotor module, the second rotor module comprise at least one rotor, i.e. the inventive unmanned aerial vehicle may comprise more than two rotors. In fig. 1, a manner in which the first rotor module and the second rotor module each have 2 rotors, that is, the unmanned aerial vehicle has a four-rotor structure, is illustrated.

In this embodiment, the flexible material may be one or a combination of a wire, a strip, and a sheet-like flexible structure. In particular arrangements, the flexible material may be, by way of example and not limitation, a wire, a ribbon or a woven cloth made of high strength fibers; and can also be a chain, a flexible plastic sheet, a rubber sheet or a flexible metal sheet, etc. Preferably, the width of the flexible material is adjustable according to the distance between the first rotor module and the second rotor module.

Preferably, when the first rotor module and the second rotor module are relatively unfolded to be located on the same plane, the relative movement of the first rotor module and the second rotor module is locked by a locking structure arranged on the rotor part, so that the first rotor module and the second rotor module are kept to be located on the same plane.

In this embodiment, the rotor module may include the rotor and have the protective housing of cavity, the protective housing is the casing of fretwork, the rotor is installed in the cavity of protective housing.

In this embodiment, the unmanned aerial vehicle further includes a battery module that can perform charging operation for the electric equipment. Preferably, the unmanned aerial vehicle comprises a third rotor wing module and a fourth rotor wing module, wherein the first rotor wing module and the third rotor wing module are arranged on one side of the unmanned aerial vehicle body, and the second rotor wing module and the fourth rotor wing module are arranged on the other side of the unmanned aerial vehicle body; the battery module is arranged between the first rotor module and the third rotor module and/or between the second rotor module and the fourth rotor module.

The battery module can charge electric equipment. By way of example and not limitation, the battery module may include an electrical storage structure. The electricity storage structure refers to a structure capable of storing electricity and supplying power, and is a common electricity storage structure such as various mobile power sources. The electricity storage unit can be a liquid lithium ion battery, a polymer lithium ion battery and a plastic lithium ion battery, can be other chemical batteries such as a dry battery, an alkaline battery, an acid battery and a fuel battery, and can also be a physical battery such as a solar battery or a nuclear battery.

The mode of the battery module outputting the electric energy to the electric equipment can be wireless charging or wired charging.

In the above description, the components may be selectively and operatively combined in any number, and each of these components may itself be implemented as hardware, within the scope of the present disclosure. In addition, terms like "comprising," "including," and "having" should be construed by default as inclusive or open-ended, rather than exclusive or closed-ended, unless expressly defined to the contrary. All technical, scientific, or other terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. Common terms found in dictionaries should not be too idealized or too unrealistically interpreted in the context of the relevant technical document unless the present disclosure explicitly defines them as such.

Although the exemplary aspects of the present disclosure have been described for illustrative purposes, those skilled in the art will appreciate that the foregoing description is merely illustrative of preferred embodiments of the invention and is not intended to limit the scope of the invention in any way, including additional implementations in which functions may be performed out of the order of presentation or discussion. Any alterations and modifications of the present invention, which are made by those of ordinary skill in the art based on the above disclosure, are intended to be within the scope of the appended claims.

Claims

1. The utility model provides a folding unmanned aerial vehicle, includes unmanned aerial vehicle main part and rotor portion, its characterized in that:

the rotor part comprises at least a first rotor module and a second rotor module which are connected by flexible materials to be folded or unfolded relatively;

in the deployed state of the first rotor module and the second rotor module, the drone body is positioned at a flexible material location as a rigid support between the first rotor module and the second rotor module;

wherein, be provided with first location structure on the unmanned aerial vehicle main part, the one end movable mounting of unmanned aerial vehicle main part is between first rotor module and second rotor module, and the other end can rotate for the aforesaid end, under the state that first rotor module and second rotor module were expanded, unmanned aerial vehicle main part passes through first location structure respectively with the first rotor module and the second rotor module fixed connection of both sides;

the unmanned aerial vehicle main body is provided with a second positioning structure which is used for fixing the unmanned aerial vehicle main body on a flexible material;

the rotor wing part is provided with a locking structure for locking the relative movement of the first rotor wing module and the second rotor wing module under the condition that the first rotor wing module and the second rotor wing module are unfolded relatively.

2. The foldable drone of claim 1, wherein: the flexible material is one or a combination of a wire, a strip and a sheet flexible structure.

3. The foldable drone of claim 1, wherein: the first positioning structure is a protrusion or a groove arranged on two side surfaces of the unmanned aerial vehicle main body, and grooves or protrusions matched with the protrusions or the grooves are arranged on the opposite side surfaces of the first rotor wing module and the second rotor wing module; the second positioning structure is a magnetic adsorption structure or an adhesive sheet, and a magnetic base material or an adhesive base material is arranged at the corresponding position of the flexible material.

4. The foldable drone of claim 1, wherein: the width of the flexible material can be adjusted according to the distance between the first rotor module and the second rotor module.

5. The foldable drone of claim 1, wherein: the unmanned aerial vehicle further comprises a battery module capable of conducting charging operation for the electric equipment.

6. The foldable drone of claim 5, wherein: the unmanned aerial vehicle further comprises a third rotor wing module and a fourth rotor wing module, wherein the first rotor wing module and the third rotor wing module are arranged on one side of the unmanned aerial vehicle main body, and the second rotor wing module and the fourth rotor wing module are arranged on the other side of the unmanned aerial vehicle main body; the battery module is arranged between the first rotor module and the third rotor module and/or between the second rotor module and the fourth rotor module.

7. The foldable drone of claim 1 or 6, wherein: each rotor module has a plurality of rotors.

8. The foldable drone of claim 1, wherein: under first rotor module and the second rotor module expansion state, unmanned aerial vehicle main part is arranged in the space that flexible material, first rotor module and second rotor module formed, first rotor module, second rotor module can expand to be in the coplanar with the unmanned aerial vehicle main part.

9. The foldable drone of claim 1, wherein: under first rotor module and the second rotor module folded condition, unmanned aerial vehicle main part is located the side of first rotor module and second rotor module.

10. The foldable drone of claim 1, wherein: the rotor module comprises a rotor and a protective shell with a hollow cavity, wherein the protective shell is a hollowed shell, and the rotor is arranged in the hollow cavity of the protective shell.

11. The foldable drone of claim 1, wherein: form sliding construction between rotor module and unmanned aerial vehicle main part through protruding and the recess of matching between the side of first rotor module and second rotor module, push in or take out unmanned aerial vehicle main part through the mode of pull.

12. The foldable drone of claim 1, wherein: be provided with the controller in the unmanned aerial vehicle main part, unmanned aerial vehicle operation in-process, the controller is connected or wireless connection with rotor module electricity, through the work of controller control rotor module.

13. The foldable drone of claim 1, wherein: the first positioning structure is a magnetic adsorption structure, and the unmanned aerial vehicle body is fixedly connected with the first rotor wing module and the second rotor wing module through magnetic adsorption.

14. The implementation method of the foldable unmanned aerial vehicle is characterized by comprising the following steps of: the unmanned aerial vehicle comprises an unmanned aerial vehicle main body and a rotor wing part, wherein the rotor wing part comprises at least a first rotor wing module and a second rotor wing module which are connected through flexible materials so as to be relatively folded or unfolded;

when the unmanned aerial vehicle is used, the first rotor wing module and the second rotor wing module are unfolded, and the unmanned aerial vehicle main body is adjusted to be located at the position of the flexible material and used as a rigid support between the first rotor wing module and the second rotor wing module;

wherein, be provided with first location structure on the unmanned aerial vehicle main part, the one end movable mounting of unmanned aerial vehicle main part is between first rotor module and second rotor module, and the other end can rotate for the aforesaid end, under the state that first rotor module and second rotor module were expanded, unmanned aerial vehicle main part passes through first location structure respectively with the first rotor module and the second rotor module fixed connection of both sides; the unmanned aerial vehicle main body is provided with a second positioning structure which is used for fixing the unmanned aerial vehicle main body on a flexible material;

when the first rotor module and the second rotor module are relatively unfolded, the relative movement of the first rotor module and the second rotor module is locked by a locking structure arranged on the rotor part.

15. The method according to claim 14, wherein: the rotor module comprises a rotor and a protective shell with a hollow cavity, wherein the protective shell is a hollowed shell, and the rotor is arranged in the hollow cavity of the protective shell.

16. The method according to claim 14, wherein: the unmanned aerial vehicle further comprises a battery module capable of conducting charging operation for the electric equipment.

17. The method according to claim 16, wherein: the unmanned aerial vehicle further comprises a third rotor wing module and a fourth rotor wing module, wherein the first rotor wing module and the third rotor wing module are arranged on one side of the unmanned aerial vehicle main body, and the second rotor wing module and the fourth rotor wing module are arranged on the other side of the unmanned aerial vehicle main body; the battery module is arranged between the first rotor module and the third rotor module and/or between the second rotor module and the fourth rotor module.

18. The method according to claim 14, wherein: the width of the flexible material can be adjusted according to the distance between the first rotor module and the second rotor module.