Unmanned aerial vehicle empennage leading edge
By designing composite skins as foam sandwich structures and suitable for VARI process molding, the high manufacturing cost problem of traditional composite laminated structures or honeycomb sandwich structures in the manufacturing of the leading edge of the drone tail wing is solved, and the manufacturing cost is reduced and the effect of improving bird collision resistance.
Patent Information
- Application Number
- CN202421439267.6
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-06-21
- Publication Date
- 2025-02-14
- Estimated Expiration
- 2034-06-21
AI Technical Summary
Traditional composite laminated structures or honeycomb sandwich structures have high manufacturing cost problems in the manufacturing of the leading edge of the drone tail wing, and the honeycomb sandwich structure cannot be suitable for low-cost VARI processes.
The composite skin is designed as a foam sandwich structure, adopts a V-shaped cross-section and a foam core is set at the V-shaped end. It combines ordinary partitions and docking partitions, and is connected through adhesive connections and removable connections, which are suitable for VARI process molding.
It reduces the manufacturing cost of composite materials, simplifies the forming process, improves the advanced structure and bird collision resistance, and solves the problem of grid deformation of traditional honeycomb sandwich structures during the manufacturing process.
Smart Images
Figure CN222474494U_ABST
Abstract
Description
Technical Field
[0001] The utility model belongs to the field of unmanned aerial vehicle manufacturing and relates to a leading edge of a tail wing of a unmanned aerial vehicle. Background Art
[0002] At present, composite materials have become the main structural materials in the field of UAVs. The application of composite materials has played a vital role in the lightweight, miniaturization and high performance of UAV structures. Accelerating the development of high-performance, low-cost composite materials for UAV fuselage and their manufacturing processes is a major challenge faced by the aviation field. Traditional typical structural parts of aviation composite materials are mostly formed by autoclave molding, which has high energy consumption, long manufacturing cycle and relatively poor economic efficiency. Therefore, low cost and high integrity have become the development direction of the new generation of composite materials. At present, the typical leading edge structures of domestic and foreign aircraft are basically divided into two categories: skin-rib structure and sandwich structure. In the skin-rib structure, the skin is mostly a metal structure, and the ribs can be a metal structure or a composite laminate structure. In the sandwich structure, the skin is mostly a composite honeycomb sandwich structure. Traditional composite laminate structures or composite honeycomb sandwich structures are mostly formed by autoclave molding, which has high manufacturing costs, and the prepreg used needs to be stored and transported at low temperatures, which limits its further expansion in other fields.
[0003] The VARI (Vacuum Assistant Resin Infusion) process is a low-cost manufacturing technology for composite materials. The process cost is lower than the autoclave molding process, but the honeycomb sandwich structure is not suitable for the VARI process at present. Utility Model Content
[0004] The purpose of the utility model is to overcome the shortcomings of the above-mentioned prior art and provide a leading edge of a UAV tail wing, which can be formed by VARI process while keeping the weight and structure basically unchanged, thereby reducing the manufacturing cost.
[0005] In order to achieve the above purpose, the utility model adopts the following technical solutions:
[0006] A leading edge of a UAV tail wing, including a composite skin;
[0007] The composite material skin is bent along the center line in the length direction to form a V-shaped cross-section structure, with the V-shaped end being an arc, and a foam core is arranged inside the V-shaped structure of the composite material skin.
[0008] Preferably, the thickness of the foam core gradually decreases from the V-shaped end to the V-shaped side regions.
[0009] Preferably, a plurality of common partitions are arranged on the inner side of the composite material skin.
[0010] Furthermore, if there are multiple common partitions, the multiple common partitions are arranged at equal intervals.
[0011] Furthermore, the common partition is a composite laminate structure.
[0012] Furthermore, the composite skin and the common bulkhead are connected by adhesive bonding.
[0013] Furthermore, the common partition is a V-shaped structure, and its size is the same as the inner size of the composite material skin, and the common partition fits the inner shape of the composite material skin.
[0014] Preferably, butt-jointing partitions are provided at both ends of the composite material skin.
[0015] Furthermore, the composite skin and the butt bulkhead are detachably connected via support plate nuts and bolts.
[0016] Furthermore, the butt-joint bulkhead is a V-shaped structure, and its dimensions are the same as the dimensions of the inner side of the composite material skin, and the butt-joint bulkhead fits the inner shape of the composite material skin.
[0017] Compared with the prior art, the utility model has the following beneficial effects:
[0018] The utility model designs the composite skin as a foam sandwich structure, thereby making the composite sandwich structure suitable for VARI process molding, simplifying the mold structure in the molding process, improving the structural advancement, and reducing the manufacturing cost of the composite material while meeting the design requirements, overcoming the high manufacturing cost problem of traditional autoclave molding. In addition, the processing performance and bird strike resistance of the foam core are better than those of the honeycomb core, and it is more suitable for the manufacturing of UAV structures with a small leading edge arc top area, solving the problem that the R angle of the leading edge arc top area is small, the honeycomb core grid is deformed during the manufacturing process, and the honeycomb sandwich structure bird strike resistance design cannot be used in the leading edge arc top area of the small wing type tail.
[0019] Furthermore, the V-shaped end is the front end of the leading edge facing the wind, and the foam core thickness is relatively thick, which can improve the bird strike resistance of the leading edge structure. The thickness of the foam core in the remaining area gradually decreases, which can not only meet the skin stability and process processing requirements, but also reduce the structure weight.
[0020] Furthermore, the common partition is a composite laminate structure, thereby achieving adaptation to VARI process molding and further reducing manufacturing costs.
[0021] Furthermore, the composite skin and the ordinary partition are connected by adhesive bonding, which not only improves the structural integrity and structural surface performance, simplifies the assembly process, but also reduces the structural weight. BRIEF DESCRIPTION OF THE DRAWINGS
[0022] Figure 1 This is a schematic structural diagram of the leading edge of the UAV tail wing of the utility model;
[0023] Figure 2 This is a schematic diagram of the composite material skin structure of the utility model;
[0024] Figure 3 It is a cross-sectional view of the composite material skin of the utility model;
[0025] Figure 4 This is a schematic diagram of a common partition structure of the utility model;
[0026] Figure 5 It is a schematic diagram of the docking partition structure of the utility model.
[0027] Among them: 1-composite material skin; 2-ordinary partition; 3-butt partition. DETAILED DESCRIPTION
[0028] The embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.
[0029] In the description of the present utility model, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present utility model and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present utility model. In addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present utility model, the meaning of "multiple" is two or more, unless otherwise clearly and specifically defined.
[0030] In the description of the present utility model, it should be noted that, unless otherwise clearly specified and limited, the terms "installation", "connection" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, or mutual communication; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present utility model can be understood according to specific circumstances.
[0031] In the present utility model, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include that the first and second features are in direct contact, or may include that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes that the first feature is directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes that the first feature is directly below and obliquely below the second feature, or simply indicates that the first feature is lower in level than the second feature.
[0032] The disclosure below provides many different embodiments or examples for realizing different structures of the utility model. In order to simplify the disclosure of the utility model, the components and settings of specific examples are described below. Of course, they are merely examples, and the purpose is not to limit the utility model. In addition, the utility model may repeat reference numbers and / or reference letters in different examples, and such repetition is for the purpose of simplification and clarity, and does not itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the utility model provides various specific examples of processes and materials, but those of ordinary skill in the art may be aware of the application of other processes and / or the use of other materials.
[0033] like Figure 1 and Figure 2 As shown, the leading edge of the tail wing of the UAV described in the utility model includes a composite material skin 1, a common partition 2 and a docking partition 3.
[0034] The composite material skin 1 is bent along the center line in the length direction to form a V-shaped cross-section structure, and the V-shaped end is an arc line, which is the leading edge arc top area.
[0035] The composite material skin 1 is a foam sandwich structure. A foam core is arranged inside the V-shaped composite material skin 1. The processing performance and bird strike resistance of the foam core are better than those of the honeycomb core, and it is more suitable for the manufacture of UAV structures with a smaller leading edge arc top area.
[0036] like Figure 3As shown, the foam core of the sandwich structure of the composite material skin 1 adopts a variable cross-section structure design. The front end of the leading edge facing the wind, that is, the foam core thickness of the V-shaped end is relatively thick, which can improve the bird strike resistance of the leading edge structure. The thickness of the foam core in the remaining areas on both sides, that is, the areas on both sides of the V-shaped area, is uniformly thinned, which can not only meet the skin stability and process processing requirements, but also reduce the structural weight.
[0037] One or a plurality of common partitions 2 are arranged at equal intervals inside the composite skin 1. The composite skin 1 and the common partitions 2 are connected by adhesive bonding, which not only improves the structural integrity and structural surface performance, but also reduces the structural weight.
[0038] like Figure 4 As shown, the common partition 2 is a V-shaped structure, and its size is the same as the inner size of the composite material skin 1 , and the common partition 2 fits the inner shape of the composite material skin 1 .
[0039] Both ends of the composite material skin 1 are provided with butt-joint bulkheads 3. The composite material skin 1 and the butt-joint bulkheads 3 are detachably connected through support plate nuts and bolts, which can improve the structural maintenance performance and reduce the maintenance cost.
[0040] like Figure 5 As shown, the butt-joint bulkhead 3 is a V-shaped structure, and its size is the same as the inner size of the composite material skin 1 , and the butt-joint bulkhead 3 fits the inner shape of the composite material skin 1 .
[0041] The composite material skin 1 is a foam sandwich structure, and the common partition 2 is a composite material laminate structure, both of which are formed by VARI process.
[0042] The preparation process of the composite skin 1 foam sandwich structure is as follows: firstly, the carbon fiber cloth and the foam core are laid on a single-sided mold, the gas of the fiber reinforcement is removed under a vacuum state, and then the fiber reinforcement is impregnated through the flow and penetration of the resin, and then heated and cured in an oven.
[0043] The composite material skin 1 and the common partition 2 are connected by adhesive bonding, which not only improves the structural integrity and structural surface performance, simplifies the assembly process, but also reduces the structural weight.
[0044] The composite material skin 1 and the docking bulkhead 3 are detachably connected via support plate nuts and bolts, ensuring that the connection between the leading edge of the tail wing and the surrounding structure is detachable, thereby improving the maintenance and interchangeability of the leading edge structure of the tail wing.
[0045] The utility model designs the composite material skin as a foam sandwich structure, thereby making the composite material sandwich structure suitable for VARI process molding, simplifying the mold structure in the molding process, and improving the structural advancement. The skin is a composite material sandwich structure, and the core material is a lightweight foam. It is molded by the VARI process. On the premise of meeting the design requirements, the manufacturing cost of the composite material is reduced, and the high manufacturing cost problem of traditional autoclave molding is overcome. In addition, the processing performance and bird strike resistance of the foam core are better than those of the honeycomb core, which is more suitable for the manufacturing of UAV structures with smaller leading edge arc top areas, solving the problems of small R angles in the leading edge arc top area, deformation of the honeycomb core grid during the manufacturing process, and the inability to use the honeycomb sandwich structure bird strike resistance design in the leading edge arc top area of the small wing-shaped tail. At the same time, the skin is connected to the ordinary partition by adhesive bonding, which improves the integrity of the structure.
[0046] The composite skin 1 and the common partition 2 of the present application are both formed by the VARI process. This process only requires a single-sided mold that does not leak under vacuum and a simple vacuum bag. The gas of the fiber reinforcement is removed under vacuum, and the fiber reinforcement is impregnated through the flow and penetration of the resin, and then heated and cured in an oven. This process simplifies the mold structure, improves the structural advancement, reduces the structural weight and reduces the manufacturing cost of the composite material while meeting the design requirements, and overcomes the high manufacturing cost problem of traditional autoclave molding.
[0047] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.
[0048] It should be understood that the above description is for illustration and not for limitation. Many embodiments and many applications beyond the examples provided will be apparent to those skilled in the art upon reading the above description. Therefore, the scope of the present teachings should not be determined with reference to the above description, but rather with reference to the foregoing claims and the full scope of equivalents to which such claims are entitled. For the purpose of comprehensiveness, all articles and references, including disclosures of patent applications and publications, are incorporated herein by reference. The omission of any aspect of the subject matter disclosed herein in the foregoing claims is not intended to be a waiver of the subject matter, nor should it be considered that the applicant has not considered the subject matter as part of the disclosed utility model subject matter.
Claims
1. A leading edge of a UAV tail wing, characterized in that: It comprises a composite material skin (1); The composite material skin (1) is bent along the center line in the length direction to form a V-shaped cross-section structure, the V-shaped end is an arc, and a foam core is arranged inside the V-shaped structure of the composite material skin (1).
2. The UAV tail wing leading edge according to claim 1, characterized in that: The thickness of the foam core gradually decreases from the V-shaped end to the V-shaped two side areas.
3. The leading edge of the UAV tail wing according to claim 1, characterized in that: A plurality of common partitions (2) are arranged on the inner side of the composite material skin (1).
4. The leading edge of the UAV tail wing according to claim 3, characterized in that: If there are multiple common partitions (2), the multiple common partitions (2) are arranged at equal intervals.
5. The leading edge of the UAV tail wing according to claim 3, characterized in that: The common partition (2) is a composite material laminate structure.
6. The leading edge of the UAV tail wing according to claim 3, characterized in that: The composite material skin (1) and the common partition (2) are connected by gluing.
7. The leading edge of the UAV tail wing according to claim 3, characterized in that: The common partition (2) is a V-shaped structure, and its size is the same as the inner size of the composite material skin (1). The common partition (2) fits the inner shape of the composite material skin (1).
8. The UAV tail wing leading edge according to claim 1, characterized in that: Butt clapboards (3) are provided at both ends of the composite material skin (1).
9. The leading edge of the UAV tail wing according to claim 8, characterized in that: The composite material skin (1) and the butt bulkhead (3) are detachably connected via support plate nuts and bolts.
10. The leading edge of the UAV tail wing according to claim 8, characterized in that: The butt-joint bulkhead (3) is a V-shaped structure, and its dimensions are the same as the dimensions of the inner side of the composite material skin (1), and the butt-joint bulkhead (3) fits the inner shape of the composite material skin (1).