CN110667819A - Folding structure and rotor unmanned aerial vehicle thereof - Google Patents

Abstract

The invention discloses a folding structure and a rotor unmanned aerial vehicle thereof, wherein when a user needs to carry or store the unmanned aerial vehicle, a propeller assembly can be detached from a second wing, then a top cap clamped with a clamping groove is pressed, an elastic piece is further compressed, the elastic piece is contracted, then the second wing is pushed towards the direction of a machine body, the top cap is abutted against the inner top wall of a first wing, meanwhile, a sliding block slides on a sliding rail and stops when sliding is not enough, then the second wing slides to the inner part of the first wing, and only the propeller assembly is partially left outside the first wing, so that the folding storage of the unmanned aerial vehicle is realized, and the user can conveniently carry or store the unmanned aerial vehicle.

Description

Folding structure and rotor unmanned aerial vehicle thereof

Technical Field

The invention relates to the technical field of unmanned aerial vehicles, in particular to a folding structure and a rotor unmanned aerial vehicle thereof.

Background

Unmanned aerial vehicles are unmanned planes controlled by wireless remote control equipment and programs, are greatly developed in military and civil aspects, and are widely used in the aspects of aerial photography, detection, search and rescue, security, resource exploration, agriculture and the like. But unmanned aerial vehicle on the market usually exists wholly, and inconvenient carrying and accomodating research and development a folding unmanned aerial vehicle is needed a urgent need to solve.

Disclosure of Invention

The invention aims to provide a folding structure, and aims to solve the technical problem that an unmanned aerial vehicle on the market in the prior art is inconvenient to carry and store as a whole.

In order to achieve the above object, the folding structure adopted by the present invention includes a fuselage, a wing assembly and a propeller assembly, the wing assembly includes a first wing, a second wing, sliders, a support, an elastic member and a top cap, the first wing is fixedly connected with the fuselage and located on a side wall of the fuselage, the interior of the first wing is of a cavity structure, two side walls of the first wing are provided with parallel sliding rails, an upper wall end of the first wing is provided with a clamping groove, the sliders are fixedly connected with the second wing and located on two side walls of the second wing, each slider is slidably connected with the first wing and located inside the corresponding sliding rail, an outer bottom wall of the second wing is in clearance fit with an inner bottom wall of the first wing, the support is fixedly connected with the second wing and located at a wing root of an upper surface wall of the second wing, and is located the inside of first wing, the hood with support sliding connection, just the top of hood with the draw-in groove block, the screw hole has on the lateral wall of hood, the one end of elastic component with support fixed connection, the other end of elastic component with hood fixed connection, just the elastic component is located the inside of support, the screw subassembly with the second wing rotates to be connected, and is located the wing point department of second wing, the quantity of wing subassembly is two at least, and evenly distributed is in the lateral wall of fuselage.

The wing assembly further comprises a limiting part, one end of the limiting part penetrates through the threaded hole, and the limiting part is in threaded connection with the top cap.

The propeller component comprises a driving piece, a threaded rod and a propeller, the driving piece is fixedly connected with the second wing and is located at the wing tip of the second wing, the output end of the driving piece is in transmission connection with the threaded rod, the propeller is detachably connected with the threaded rod, and the shaft sleeve of the propeller is arranged outside the threaded rod.

The screw assembly further comprises a positioning piece and a locking cover, the positioning piece is fixedly connected with the threaded rod and is located at the lower end of the screw, the locking cover is in threaded connection with the threaded rod and sleeved outside the threaded rod, and the locking cover is clamped with the positioning piece to clamp the shaft sleeve of the screw.

The folding structure further comprises a floor stand assembly, the floor stand assembly is movably connected with the machine body and located at the bottom of the machine body, the number of the floor stand assemblies is two, and the two floor stand assemblies are arranged along the axial line of the machine body oppositely.

The fuselage, the first wing, the second wing and the landing frame assembly are all made of aluminum alloy materials.

The invention also provides a rotor unmanned aerial vehicle which comprises a folding structure and a sliding wheel, wherein the sliding wheel is rotatably connected with the landing frame assembly and is positioned at the bottom of the landing frame assembly.

According to the folding structure and the rotor unmanned aerial vehicle thereof, when a user needs to carry or store the unmanned aerial vehicle, the propeller assembly can be detached from the second wing, then the top cap clamped with the clamping groove is pressed, the elastic piece is compressed, the elastic piece is contracted, then the second wing is pushed towards the direction of the body, the top cap is abutted against the inner top wall of the first wing, meanwhile, the sliding block slides on the sliding rail and stops when sliding to the sliding block and cannot slide, then the second wing slides to the inner part of the first wing, and only the propeller assembly part is left outside the first wing, so that the wing can be folded and stored, and the user can conveniently carry or store the unmanned aerial vehicle.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

Figure 1 is a partial structural cross-sectional view of the folding structure of the present invention and its rotorcraft.

Fig. 2 is a schematic view of the folding structure and the structure of the unmanned rotorcraft without a limit stop according to the present invention.

Fig. 3 is a schematic structural view of the folding structure and the unmanned gyroplane thereof when a limiting member is installed.

Fig. 4 is a bottom view of the folding structure of the present invention and its rotorcraft.

Figure 5 is a side view of the folding structure of the present invention and its rotorcraft.

100-folding structure, 200-rotor unmanned aerial vehicle, 10-fuselage, 20-wing assembly, 30-propeller assembly, 40-landing frame assembly, 11-chute, 21-first wing, 211-slide rail, 212-clamping groove, 22-second wing, 23-slide block, 24-support, 25-elastic element, 26-top cap, 261-threaded hole, 27-limit piece, 31-driving piece, 32-threaded rod, 33-propeller, 34-locating piece, 35-locking cover, 41-connecting rod, 42-landing frame, 50-sliding sleeve and 60-sliding wheel.

Detailed Description

Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention.

In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

Referring to fig. 1 to 5, the present invention provides a folding structure 100, including a fuselage 10, a wing assembly 20, and a propeller assembly 30, where the wing assembly 20 includes a first wing 21, a second wing 22, sliders 23, a support 24, an elastic element 25, and a top cap 26, the first wing 21 is fixedly connected to the fuselage 10 and located on a side wall of the fuselage 10, the first wing 21 is of a cavity structure inside, two side walls of the first wing 21 are provided with parallel sliding rails 211, an upper wall end of the first wing 21 is provided with a locking groove 212, the sliders 23 are fixedly connected to the second wing 22 and located on two side walls of the second wing 22, each slider 23 is slidably connected to the first wing 21 and located inside the corresponding sliding rail 211, an outer bottom wall of the second wing 22 is in clearance fit with an inner bottom wall of the first wing 21, the support 24 with second wing 22 fixed connection to be located the wing root department of the last upper surface wall of second wing 22, and be located the inside of first wing 21, hood 26 with support 24 sliding connection, just the top of hood 26 with draw-in groove 212 block, screw hole 261 has on the lateral wall of hood 26, the one end of elastic component 25 with support 24 fixed connection, the other end of elastic component 25 with hood 26 fixed connection, just elastic component 25 is located the inside of support 24, screw subassembly 30 with second wing 22 rotates to be connected, and is located the wing tip department of second wing 22, the quantity of wing subassembly 20 is two at least, and evenly distributed in the lateral wall of fuselage 10.

In this embodiment, at least two wing assemblies 20 are disposed on a side wall of the fuselage 10, each wing assembly 20 is provided with the propeller assembly 30, the elastic member 25 is a compression spring, when the unmanned aerial vehicle needs to be used, the second wing 22 can be pulled towards one end far away from the fuselage 10, each slider 23 slides on the corresponding slide rail 211, and then the second wing 22 slides out of the first wing 21, when the second wing 22 is pulled to a certain position, that is, when the top cap 26 is pulled to a position where the clamping groove 212 coincides with the clamping groove 212, since the top cap 26 does not coincide with the clamping groove 212, the top cap 26 abuts against an inner top wall of the first wing 21, the elastic member 25 is in a compressed state, and when the top cap 26 coincides with the clamping groove 212, the top cap 26 is under a restoring force of the elastic member 25, moving towards one end far away from the support 24, then clamping the top cap 26 and the clamping groove 212 with each other, fixing the first wing 21 and the second wing 22 firmly at the moment, pulling the second wing 22 to a specified position, then assembling the propeller assembly 30 at the wing tip of the second wing 22, and then controlling the propeller assembly 30 to rotate so that the unmanned aerial vehicle takes off; when the unmanned aerial vehicle needs to be stored after finishing flying, the propeller assembly 30 can be detached from the second wing 22, then the top cap 26 clamped with the clamping groove 212 is pressed, the elastic piece 25 is further compressed, the elastic piece 25 contracts, then the second wing 22 is pushed towards the direction of the fuselage 10, the top cap 26 abuts against the inner top wall of the first wing 21, meanwhile, the sliding block 23 slides on the sliding rail 211 and stops when sliding to the sliding block 23 and cannot slide, then the second wing 22 slides to the inside of the first wing 21, and only the propeller assembly 30 is partially left outside the first wing 21, so that the unmanned aerial vehicle can be folded and stored, and a user can conveniently carry or store the unmanned aerial vehicle.

Further, the wing assembly 20 further includes a limiting member 27, one end of the limiting member 27 penetrates through the threaded hole 261, and the limiting member 27 is in threaded connection with the top cap 26.

In this embodiment, the limiting member 27 is a limiting bolt, and when the top cap 26 is engaged with the locking groove 212 under the restoring force of the elastic member 25, the positions of the first wing 21 and the second wing 22 are determined, so as to avoid that the engagement between the top cap 26 and the locking groove 212 is disengaged during the flight of the unmanned aerial vehicle, which results in the looseness of the second wing 22 on the first wing 21, the limiting member 27 penetrates through the threaded hole 261, which avoids the engagement between the top cap 26 and the locking groove 212, the looseness of the second wing 22 on the first wing 21 is avoided, and the unmanned aerial vehicle crashes during the flight.

Further, the screw propeller assembly 30 comprises a driving piece 31, a threaded rod 32 and a screw propeller 33, the driving piece 31 is fixedly connected with the second wing 22 and is located at the wing tip of the second wing 22, the output end of the driving piece 31 is in transmission connection with the threaded rod 32, the screw propeller 33 is detachably connected with the threaded rod 32, and the shaft sleeve of the screw propeller 33 is arranged outside the threaded rod 32. Screw subassembly 30 still includes setting element 34 and locking lid 35, setting element 34 with threaded rod 32 fixed connection, and be located the lower extreme of screw 33, locking lid 35 with threaded rod 32 threaded connection, and the cover is established the outside of threaded rod 32, locking lid 35 with setting element 34 centre gripping the axle sleeve of screw 33.

In this embodiment, the driving member 31 is a motor, the driving member 31 is installed at the wing tip of the second wing 22, the output end of the driving member 31 is in transmission connection with the threaded rod 32, the shaft sleeve of the propeller 33 is sleeved outside the threaded rod 32, the positioning member 34 is used for positioning the position of the screw 33 installed on the threaded rod 32, the locking cover 35 is sleeved outside the threaded rod 32, and then the locking cover 35 is rotated, so that the internal thread of the locking cover 35 is in threaded fit with the threaded rod 32, and then the shaft sleeve of the propeller 33 is clamped by the locking cover 35 and the positioning member 34, so that the propeller 33 is fixed firmly, when the unmanned aerial vehicle needs to be stored or carried, the locking cover 35 can be unscrewed, and the propeller 33 is taken down from the threaded rod 32, reduce unmanned aerial vehicle's volume with this to the user conveniently carries or accomodates unmanned aerial vehicle. It is also convenient to replace the propeller 33 when it is damaged.

Further, beta structure 100 still includes the frame subassembly of falling to the ground 40, fall to the ground the frame subassembly 40 with fuselage 10 swing joint, and be located the bottom of fuselage 10, just the quantity of frame subassembly 40 is two, two fall to the ground the frame subassembly 40 is followed the axial line of fuselage 10 sets up relatively. The assembly of landing stage 40 includes connecting rod 41 and landing stage 42, connecting rod 41 with fuselage 10 fixed connection, and be located the below of fuselage 10, the quantity of connecting rod 41 is two, two connecting rod 41 parallel arrangement, landing stage 42 is I-shaped structure, the both ends of the entablature that falls landing stage 42 run through two respectively connecting rod 41, just the both ends that fall landing stage 42 respectively with two connecting rod 41 is articulated.

In this embodiment, the two connecting rods 41 are used for supporting the ground falling frame 42, the ground falling frame 42 is composed of an upper cross beam, a longitudinal beam and a lower cross beam, the ground falling frame 42 is formed in an i-shaped structure, two ends of the upper cross beam penetrate through holes in the two connecting rods 41 which are arranged in parallel, the connecting rods 41 are hinged to the upper cross beam, limiting springs are arranged at the joints of the two ends of the upper cross beam and the connecting rods 41, the rotating angle of the upper cross beam on the connecting rods 41 can be limited, and further the rotating angle of the ground falling frame 42 is limited. Through two the assembly 40 edge of falling to the ground the axial line of fuselage 10 sets up relatively, makes two the frame 42 of falling to the ground can play the supporting role to unmanned aerial vehicle for unmanned aerial vehicle is subaerial more stable.

Folding structure 100 still includes sliding sleeve 50, the bottom of fuselage 10 has spout 11, sliding sleeve 50 with fuselage 10 sliding connection, and be located spout 11's inside, spout 11 sets up on the fuselage 10, and be located two between the frame 42 that falls, work as two the frame 42 that falls fold to with the fuselage 10 is parallel back, can with sliding sleeve 50 is in slide on the spout 11, and makes sliding sleeve 50 cover is established and is served at one of two entablature, with this will receive two after folding frame 42 that falls is fixed.

Further, the fuselage 10, the first wing 21, the second wing 22, and the landing gear assembly 40 are all made of aluminum alloy materials.

In this embodiment, the aluminum alloy material has low density, but has high strength, is close to or exceeds high-quality steel, has good plasticity, and can be processed into various profiles, and the fuselage 10, the first wing 21, the second wing 22 and the landing frame assembly 40 are all made of aluminum alloy materials, so that the unmanned aerial vehicle can be light in weight, and the structural strength of the unmanned aerial vehicle can be guaranteed.

The invention also provides a rotary wing unmanned aerial vehicle 200, which comprises a folding structure 100 and a sliding wheel 60, wherein the sliding wheel 60 is rotatably connected with the floor stand assembly 40 and is positioned at the bottom of the floor stand assembly 40.

In this embodiment, the glide wheel with the shelf 42 that falls is rotated and is connected, and is located on the bottom end rail of shelf, the setting of glide wheel 60, it is right to facilitate the user rotor unmanned aerial vehicle 200's removal, through set up on the rotor unmanned aerial vehicle 200 beta structure for unmanned aerial vehicle's wing can be folded, screw 33 can be followed dismantle on the second wing 22, the shelf 42 that falls can fold, and fold to the bottom of fuselage 10 reduces with this rotor unmanned aerial vehicle 200's volume, user can put into personal baggage or suitcase, and convenient to carry and accomodate, this unmanned aerial vehicle not only can be used to take photo by plane, still can be used to plant protection operation, homeland monitoring, electric power and patrol and examine, a plurality of fields such as public security anti-terrorism, uses and extensively.

While the invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.

Claims (7)

1. A folding structure is characterized in that a folding structure is provided,

the aircraft wing assembly comprises a first wing, a second wing, a sliding block, a support, an elastic part and a top cap, wherein the first wing is fixedly connected with the aircraft body and is positioned on the side wall of the aircraft body, the inside of the first wing is of a cavity structure, sliding rails which are arranged in parallel are arranged on the two side walls of the first wing, the upper wall end of the first wing is provided with a clamping groove, the sliding block is fixedly connected with the second wing and is positioned on the two side walls of the second wing, each sliding block is connected with the first wing in a sliding manner and is positioned inside the sliding rails in a matched manner, the outer bottom wall of the second wing is in clearance fit with the inner bottom wall of the first wing, the support is fixedly connected with the second wing and is positioned at the wing root of the upper surface wall of the second wing and is positioned inside the first wing, the hood with support sliding connection, just the top of hood with the draw-in groove block, the screw hole has on the lateral wall of hood, the one end of elastic component with support fixed connection, the other end of elastic component with hood fixed connection, just the elastic component is located the inside of support, the screw subassembly with the second wing rotates to be connected, and is located the wing tip department of second wing, the quantity of wing subassembly is two at least, and evenly distributed is in the lateral wall of fuselage.

2. The folding structure of claim 1,

the wing assembly further comprises a limiting part, one end of the limiting part penetrates through the threaded hole, and the limiting part is in threaded connection with the top cap.

3. The folding structure of claim 1,

the screw subassembly includes driving piece, threaded rod and screw, the driving piece with second wing fixed connection to be located the wing tip department of second wing, the output of driving piece with the threaded rod transmission is connected, the screw with the connection can be dismantled to the threaded rod, the axle sleeve cover of screw is established the outside of threaded rod.

4. The folding structure of claim 3,

the screw subassembly still includes setting element and locking lid, the setting element with threaded rod fixed connection, and be located the lower extreme of screw, the locking lid with threaded rod threaded connection, and the cover is established the outside of threaded rod, the locking lid with the setting element centre gripping the axle sleeve of screw.

5. The folding structure of claim 4,

the folding structure further comprises a floor stand assembly, wherein the floor stand assembly is movably connected with the machine body and located at the bottom of the machine body, the number of the floor stand assemblies is two, and the two floor stand assemblies are arranged along the axial line of the machine body oppositely.

6. The rotary-wing drone of claim 5,

the fuselage, the first wing, the second wing and the landing frame assembly are all made of aluminum alloy materials.

7. A rotor unmanned aerial vehicle comprises a folding structure and is characterized in that,

the sliding wheel is rotatably connected with the floor stand assembly and is positioned at the bottom of the floor stand assembly.

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