Airframe structure of multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle

Abstract

The utility model relates to the technical field of unmanned aerial vehicles, and provides an airframe structure of a multi-rotor unmanned aerial vehicle and the multi-rotor unmanned aerial vehicle. The machine body framework comprises a machine body framework body prepared from a composite material, the skin is arranged on one side of the machine body framework body, and the machine body framework body and the skin are integrally formed through hand lay-up co-curing. Through the integrated arrangement of the airframe framework and the skin, the arrangement of connecting structural parts can be effectively reduced, and the effective control of the overall weight can be realized.

Description

TECHNICAL FIELD

[0001] The utility model relates to unmanned plane technical field especially relates to a kind of body structure of multi-rotor unmanned plane and multi-rotor unmanned plane. BACKGROUND

[0002] Multi-rotor unmanned plane is a kind of special unmanned rotary-wing aircraft with three and above rotary-wing shafts. With the development of unmanned plane technology, the requirement for body structure weight reduction and structure strength improvement is higher and higher, and if the body structure is too heavy, it will greatly reduce the flight performance and use environment of unmanned plane.

[0003] In related art, assembly is usually carried out by screw or assembly assembly, so as to form body framework, which has more parts, resulting in high assembly difficulty and low production efficiency, and this method is difficult to effectively control the weight of the whole. UTILITY MODEL CONTENT

[0004] The utility model provides a kind of body structure of multi-rotor unmanned plane and multi-rotor unmanned plane to solve the defect that too many structural members are connected between body and skin in prior art, resulting in high assembly difficulty and low assembly efficiency.

[0005] The utility model provides a kind of body structure of multi-rotor unmanned plane, comprising: body framework and skin;The body framework includes the body framework prepared by composite material, the skin is located at one side of the body framework, and the body framework and the skin are integrally formed by hand paste co-curing.

[0006] According to the body structure of multi-rotor unmanned plane provided by the utility model, the body framework is carbon fiber body framework, and the skin is carbon fiber skin.

[0007] According to the body structure of multi-rotor unmanned plane provided by the utility model, the body framework includes partition frame and rib plate, and the rib plate and the partition frame are arranged at intervals.

[0008] According to the body structure of multi-rotor unmanned plane provided by the utility model, the end of the partition frame and the rib plate is in contact with the skin.

[0009] According to the body structure of multi-rotor unmanned plane provided by the utility model, a strip structure is arranged on the edge of the partition frame, and the strip structure is in contact with the inner wall surface of the skin.

[0010] According to the body structure of multi-rotor unmanned plane provided by the utility model, through hole structures are arranged on the partition frame and the rib plate.

[0011] According to the body structure of multi-rotor unmanned plane provided by the utility model, the axis of the through hole on the partition frame and the through hole on the rib plate is on the same straight line.

[0012] According to the body structure of the multi-rotor unmanned plane, the inner wall surface of the skin is provided with a reinforcing rib.

[0013] The utility model provides a kind of multi-rotor unmanned plane, including unmanned plane main body, the unmanned plane main body includes the body structure of the multi-rotor unmanned plane of any one described above.

[0014] The body structure of the multi-rotor unmanned plane and the multi-rotor unmanned plane provided by the utility model can effectively reduce the setting of connecting structural members by integrally arranging the body framework and the skin, and effectively control the overall weight. BRIEF DESCRIPTION OF DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the utility model or the prior art, the following will briefly introduce the drawings needed to be used in the embodiment or the prior art description, and obviously, the drawings in the following description are some embodiments of the utility model, and for those skilled in the art, other drawings can also be obtained without creative labor.

[0016] Figure 1 It is the structure schematic view of another part in the body structure of the multi-rotor unmanned plane provided by the utility model.

[0017] Figure 2 It is the structure schematic view of another part in the body structure of the multi-rotor unmanned plane provided by the utility model. Figure 1 It is the structure schematic view of another part in the body structure of the multi-rotor unmanned plane provided by the utility model.

[0018] Figure 3 It is the structure schematic view of another part in the body structure of the multi-rotor unmanned plane provided by the utility model.

[0019] Reference signs:

[0020] 1, body framework;11, partition frame;111, edge strip structure;12, rib plate;2, through hole;3, skin;4, reinforcing rib. DETAILED DESCRIPTION

[0021] In order to make the purpose, technical scheme and advantages of the utility model more clear, the technical scheme in the utility model will be described clearly and completely in the following by combining with the drawings in the utility model, obviously, the described embodiment is a part of the embodiment of the utility model, rather than all the embodiments. Based on the embodiment in the utility model, all other embodiments obtained by those skilled in the art without creative labor belong to the protection scope of the utility model.

[0022] In the description of the embodiments of the present application, it should be explained that, the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the convenience of illustrating the embodiments of the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the embodiments of the present application. In addition, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance.

[0023] In the description of the embodiments of the present application, it should be explained that, unless otherwise explicitly specified and limited, the terms "connected", "connected" should be understood broadly, for example, it can be fixedly connected, or it can be detachably connected, or integrally connected; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0024] In the embodiments of the present application, unless otherwise explicitly specified and limited, the first feature is "on" or "under" the second feature, which can be direct contact between the first and second features, or indirect contact between the first and second features through an intermediate medium. Moreover, the first feature "above", "above" and "above" of the second feature can be directly above or obliquely above the first feature, or only indicate that the horizontal height of the first feature is higher than that of the second feature. The first feature "below", "below" and "below" of the second feature can be directly below or obliquely below the first feature, or only indicate that the horizontal height of the first feature is less than that of the second feature.

[0025] In the description of the present application, the description of the terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine the different embodiments or examples described in the present application and the features of the different embodiments or examples without contradiction.

[0026] Multirotor drones typically include quadcopters, hexacopter drones, and octocopters, which achieve larger payloads and provide higher flight stability through multiple rotors. In related technologies, the airframe of multirotor drones usually uses connecting structural components to link the skin to the airframe. This method makes it difficult to control the overall weight, resulting in excessive overall weight. Furthermore, this method involves more parts, leading to high assembly difficulty and low production efficiency.

[0027] Regarding the problems in related technologies, such as Figures 1-3 As shown, this embodiment provides a fuselage structure for a multi-rotor unmanned aerial vehicle (UAV), including a fuselage frame 1 and a skin 3. The fuselage frame 1 is made of composite material, and the skin 3 is disposed on one side of the fuselage frame 1. The fuselage frame 1 and the skin 3 are integrally molded by hand lay-up and co-curing. The skin 3 is the outer surface contour structure of the multi-rotor UAV. Typically, the skin 3 is connected to the fuselage frame 1 through structural components, thereby achieving the connection of the skin 3. This method makes it difficult to control the weight and has a high assembly difficulty. In this embodiment, by hand lay-up and co-curing the skin 3 and the fuselage frame 1 into an integral structure, the number of connecting structural components is greatly reduced, the assembly difficulty is lowered, and the production efficiency is improved.

[0028] Specifically, hand lay-up co-curing integral molding is a process in composite material manufacturing. Co-curing refers to the simultaneous curing of fibers and resin materials through heating or other means to ensure that the resin fully penetrates into the fibers, forming a composite material with consistent strength and structural integrity. This results in higher structural strength between the skin 3 and the body frame 1, and the integral molding method avoids excessive connecting parts, greatly reducing the number of components, thereby reducing assembly difficulty and improving production efficiency.

[0029] It is understood that the airframe 1 is the overall structure of the entire drone, and the airframe 1 can support the entire skin 3, thus making the skin 3 the outer contour surface of the entire drone. In this embodiment, the skin 3 and the airframe 1 are integrally molded by hand lay-up co-curing integral molding process, which simplifies the complexity of assembly and improves the structural strength of the connection between the skin 3 and the airframe 1, resulting in higher overall structural stability.

[0030] In the specific preparation process, the skin layer 3 is first laid up, and then the single-sided mold of the body frame 1 inside the skin layer 3 is assembled onto the skin layer 3 mold and locked with bolts. Then the layup of the body frame 1 is started. The overall assembly mold of the body frame 1 is used to ensure and support the outer contour shape of the skin layer 3. Then the skin layer 3 is pressed and cured in an oven to achieve an integrated molding and connection between the skin layer 3 and the body frame 1.

[0031] In specific experiments, the hand lay-up co-curing integral molding body structure showed that, compared with the body structure of ordinary drones, its tensile, compressive, and shear indices were increased by 30%, 17.8%, and 52.5% respectively, greatly improving the material strength index and making the structure stable and reliable.

[0032] In practical applications, the number of parts can be reduced from 29 to 5 by using integrated molding (i.e., hand lay-up co-curing integrated molding process), and the corresponding manufacturing cycle can be shortened from the original 74 hours to 26 hours, thereby significantly reducing the difficulty of preparation and significantly improving production efficiency.

[0033] Understandably, the use of composite materials allows for greater design flexibility in the body frame 1 and the skin 3, enabling the connection between the skin 3 and the body frame 1 through a hand lay-up co-curing integral molding process, thus allowing the skin 3 to be constructed on the outer surface of the body frame 1.

[0034] According to some embodiments provided by this utility model, the body frame 1 is a carbon fiber body frame 1, and the skin 3 is a carbon fiber skin 3. Both the body frame 1 and the skin 3 are made of carbon fiber, which facilitates the integrated connection of the two, and the limitation of carbon fiber can improve the overall structural strength and enhance the stability of the overall structure.

[0035] Specifically, carbon fiber has high strength and can withstand large tensile and compressive forces. In addition, carbon fiber has a low density and its weight is much lower than that of metal materials. Therefore, when used as the body frame 1, it can maintain high strength and light weight, thus achieving effective control of the overall weight.

[0036] According to some embodiments provided by this utility model, the airframe 1 includes a partition frame 11 and ribs 12, with the ribs 12 and the partition frame 11 spaced apart. The partition frame 11 divides the airframe 1 into multiple compartment areas, and the ribs 12 are alternately arranged with the partition frame 11. The arrangement of the ribs 12 results in higher overall structural strength and can improve the overall structural strength of the UAV.

[0037] It is understood that the body frame 1 in this embodiment is composed of partitions and ribs 12, and the partitions and ribs 12 are alternately arranged to make the overall structure more stable and to support the outer skin 3.

[0038] In some embodiments, the ends of both the partition frame 11 and the rib plate 12 are in contact with the skin 3. In this embodiment, both the partition frame 11 and the rib plate 12 are located on one side of the skin 3, and the skin 3 is connected to the partition frame 11 to form an integral body structure. This method can increase the connection area between the skin 3 and the body frame 1, thereby improving the overall stability.

[0039] It is understandable that the outer end faces of the partition frame 11 and the rib plate 12 are located on the same plane, which allows them to contact and connect with the skin 3 during integral co-curing molding, making the connection of the skin 3 more stable and improving the overall structural stability.

[0040] According to some embodiments provided by this utility model, a flange structure 111 is provided around the edge of the partition frame 11, and the flange structure 111 contacts the inner wall surface of the skin 3. The flange structure 111 at the edge of the partition frame 11 can effectively enhance the strength and rigidity of the edge, prevent local deformation or buckling when subjected to external loads or pressure, and improve the stability of the overall structure.

[0041] Specifically, during the integrated co-curing molding process, the edge strip structure 111 contacts the skin 3, thereby achieving integrated connection molding. This results in higher structural stability of the skin 3 connection and improves the overall structural strength. Furthermore, this method avoids collisions between the skin 3 and the frame 1, preventing noise and enhancing the overall structural stability.

[0042] In some specific embodiments, through holes 2 are provided on both the partition frame 11 and the rib plate 12. In the drone, in addition to the overall airframe structure, there are circuit boards and connecting wires inside. In this embodiment, the through holes 2 allow the wires to pass through, making the overall structure more compact.

[0043] It is understandable that in this embodiment, the partition frame 11 and the rib plate 12 are connected to the skin 3 by a hand lay-up co-curing integral molding process. After connection, it is difficult to disassemble for wire insertion. In this embodiment, the through hole 2 facilitates wire insertion and limits the wire position, preventing wire mess and ensuring that the wire is always within the through hole 2, which is beneficial for subsequent maintenance and replacement.

[0044] Specifically, wire clips are provided at the through holes 2 of the partition frame 11 and the rib plate 12. The wire clips can constrain multiple bundles of wires, so that multiple bundles of wires can be located in the through holes 2 and stably connected to the partition frame 11 and the rib plate 12.

[0045] In a specific configuration, the centerlines of the through holes 2 on the partition frame 11 and the through holes 2 on the rib plate 12 are on the same straight line. The through holes 2 are used for wires to pass through. By defining the positions of the through holes 2 on the partition frame 11 and the rib plate 12, it is easier to insert wires, facilitate overall assembly, and improve production efficiency.

[0046] According to some embodiments provided by this utility model, reinforcing ribs 4 are provided on the inner wall surface of the skin 3. As the outer surface contour of the entire body, the skin 3, through the setting of the reinforcing ribs 4, can have high structural strength and withstand a certain external impact.

[0047] The second aspect of this utility model provides a multi-rotor unmanned aerial vehicle (UAV), including a UAV body, which comprises the airframe structure of the multi-rotor UAV provided in any of the above-mentioned embodiments. The airframe structure enhances the overall stability and structural strength of the multi-rotor UAV.

[0048] Through the above description of the embodiments, those skilled in the art can clearly understand that by integrating the body frame 1 and the skin 3 into one unit, the number of connecting structural components can be effectively reduced, and the overall weight can be effectively controlled. Furthermore, the body frame 1 is made entirely of carbon fiber, which can improve the overall structural strength, effectively reduce the overall weight, and also facilitate the integral co-curing molding process.

[0049] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this utility model, and not to limit it. Although this utility model has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this utility model.

Claims

1. A fuselage structure for a multi-rotor unmanned aerial vehicle (UAV), characterized in that, include: The body frame and skin; The body frame includes a partition and ribs made of composite materials, with the ribs spaced apart from the partition; The skin is located on one side of the body frame, and the body frame and the skin are integrally formed by hand lay-up and co-curing; and the ends of the partition and the rib are in contact with the skin.

2. The airframe structure of the multi-rotor UAV according to claim 1, characterized in that, The body frame is a carbon fiber body frame, and the skin is a carbon fiber skin.

3. The airframe structure of the multi-rotor UAV according to claim 1, characterized in that, The frame has a rim strip around its edge, and the rim strip is in contact with the inner wall of the skin.

4. The airframe structure of the multi-rotor UAV according to claim 1, characterized in that, Both the partition frame and the rib plate are provided with through holes.

5. The airframe structure of the multi-rotor UAV according to claim 4, characterized in that, The axis of the through hole on the partition frame and the axis of the through hole on the rib plate are on the same straight line.

6. The airframe structure of the multi-rotor UAV according to claim 1, characterized in that, The inner wall surface of the skin is provided with reinforcing ribs.

7. A multi-rotor unmanned aerial vehicle, characterized in that, It includes the main body of the drone, which includes the airframe structure of the multi-rotor drone as described in any one of claims 1-6.

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