Folding structure and rotor unmanned aerial vehicle thereof
阅读说明:本技术 一种折叠结构及其旋翼无人机 (Folding structure and rotor unmanned aerial vehicle thereof ) 是由 周渝曦 高超 陈赟飞 于 2019-10-18 设计创作,主要内容包括:本发明公开了一种折叠结构及其旋翼无人机,通过在用户需要携带或者收纳无人机时,可将所述螺旋桨组件从所述第二机翼上拆下,然后按压与所述卡槽卡合的顶帽,进而压缩所述弹性件,所述弹性件收缩,然后将第二机翼朝向所述机身方向推动,所述顶帽与所述第一机翼的内顶壁抵持,同时所述滑块在所述滑轨上滑动,并滑动至所述滑块与不能够滑动时停止,进而所述第二机翼滑动至所述第一机翼的内部,且只将所述螺旋桨组件部分留在所述第一机翼的外部,以此实现无人机的可折叠收纳,方便用户携带或者收纳。(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.)
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.
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
In this embodiment, at least two
Further, the
In this embodiment, the
Further, the
In this embodiment, the
Further,
In this embodiment, the two connecting
Further, the
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
The invention also provides a rotary wing unmanned
In this embodiment, the glide wheel with the
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.
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