Wing structure of unmanned aerial vehicle
By using PMI foam and carbon fiber woven fabric to manufacture drone wings, the problems of complex and high cost of traditional wing structures have been solved, achieving the effects of simplified manufacturing and improved performance.
Patent Information
- Application Number
- CN202423259189.4
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-27
- Publication Date
- 2025-11-04
- Estimated Expiration
- 2034-12-27
AI Technical Summary
Traditional drones suffer from numerous wing structure components, complex manufacturing processes, high costs, and stringent assembly requirements.
Using PMI foam as the core material for the wing, combined with carbon fiber woven fabric skin and unidirectional belts, the drone wing is manufactured through composite material compression molding process, which simplifies the parts and enhances the structural strength.
It reduced manufacturing complexity and costs, improved production efficiency, simplified the assembly process, and enhanced the mechanical performance of the wings.
Smart Images
Figure CN223508512U_ABST
Abstract
Description
TECHNICAL FIELD
[0001] The utility model relates to unmanned plane technical field, concretely is a kind of unmanned plane wing structure. BACKGROUND
[0002] In the development of modern unmanned plane technology, the design and manufacturing technology of wing is one of the key factors to determine its performance. The unmanned plane wing not only needs to have sufficient mechanical properties to withstand the load in various flight environments, but also should ensure lightweight and high efficiency to improve the flight time and flexibility of the machine. The traditional wing structure is mainly divided into skin, wing rib, spar, joint and other parts. At the same time, the spar is divided into front beam and rear beam, and the wing rib is different from ordinary wing rib and reinforced wing rib. Many wing ribs are arranged in a wing, and the parts are more, the structure is complex, the manufacturing is more complex, and the economic cost is high.
[0003] The traditional wing structure has the following problems:
[0004] 1. The parts constituting the wing are more, and the structure is complex;
[0005] 2. The manufacturing process is more complex: because there are more parts, the manufacturing process and material of each part are different, which makes the manufacturing difficulty larger;
[0006] 3. The manufacturing cost is higher: from metal wing structure to composite material wing structure, because the number of parts is large, the manufacturing cost is increased. For metal structure, the material and process need to be distinguished, and the processing and manufacturing of different materials are different, which increases the economic cost. For composite material wing structure, mold is needed for processing and manufacturing, and even a wing rib also needs mold for processing and manufacturing, which increases the number of molds and further increases the economic cost;
[0007] 4. The assembly process requires higher precision: the assembly of most parts requires higher precision, and sometimes needs tooling to assist assembly. INVENTION CONTENTS
[0008] Therefore, the utility model provides a kind of unmanned plane wing structure, including: wing skin, wing body, unidirectional tape, wing reinforcement area and wing body connecting piece;The outer part of the wing body is attached with the wing skin;The upper surface and the lower surface of the wing body are provided with unidirectional tape laid along the wing span direction, and the unidirectional tape is located in the wing skin, and the middle part of the wing body is provided with wing reinforcement area attached with wing reinforcement layer, and the middle part of the wing reinforcement area is provided with wing body connecting piece.
[0009] Further, the wing body is made of polymethyl methacrylate foam material.
[0010] Further, the wing skin is made of integrated carbon fiber woven cloth material, or a combination of carbon fiber woven cloth and glass fiber cloth.
[0011] Further, the wing body includes a plurality of glue joints, and the plurality of glue joints are formed by gluing along the wing span direction.
[0012] Further, the unidirectional belt includes a front unidirectional belt and a rear unidirectional belt, the front unidirectional belt is arranged at 20-25% of the chord in the wing root to wing tip direction, and the rear unidirectional belt is arranged at 70-75% of the chord in the wing root to wing tip direction.
[0013] Further, the unidirectional belt is a pre-impregnated unidirectional belt, and the unidirectional belt is prepared by impregnating resin into continuous fibers or unidirectional fabric parallel to each other.
[0014] Further, the wing reinforcing layer is made of carbon fiber woven cloth.
[0015] Further, the wing reinforcing area of the wing machine is provided with a circular mounting hole, and the wing machine body connector is fixed in the mounting hole.
[0016] Further, the wing machine body connector is a cylindrical structure, and a plurality of connection holes are arranged on the end face in the circumferential direction, and the connection holes are used to connect the wing and the machine body by screws.
[0017] Further, the wing body is a round tail shape, and the thickness gradually increases from the leading edge to the trailing edge and then gradually decreases.
[0018] The beneficial effects of the unmanned aerial vehicle wing structure are as follows: the unmanned aerial vehicle wing structure solves the problems of the traditional wing by simplifying the parts and using advanced materials. It uses PMI foam with convenient processing and excellent mechanical properties as the core material, which can more conveniently process the airfoil shape to fit the wing mold and maintain the wing shape. The outer part is covered with a wing skin, which reduces the number of parts and the manufacturing complexity. In addition, the unidirectional belt arranged along the wing span direction enhances the mechanical properties of the structure. The design of the wing reinforcing area is used to transfer the torque at the wing root, improve the strength and stiffness of the wing, further reduce the cost and production difficulty, and design the mounting hole for mounting the wing machine body connector, so that the wing machine body connector can be pre-buried in the PMI foam during manufacturing, simplifying the processing flow and assembly process. Overall, this structure reduces the number of parts and uses advanced materials, effectively reducing the manufacturing cost, simplifying the assembly process, and improving the production efficiency. BRIEF DESCRIPTION OF DRAWINGS
[0019] Fig. 1 It is a schematic diagram of the overall structure of the unmanned aerial vehicle wing structure.
[0020] Fig. 2 It is a sectional view of a wing structure of a UAV according to an embodiment of the present application.
[0021] Fig. 3 It is a perspective view of a wing-body connecting piece of a wing structure of a UAV according to an embodiment of the present application.
[0022] In the above figure: 1, wing skin; 2, PMI foam; 3, unidirectional tape; 4, wing reinforcing area; 5, wing-body connecting piece, 51- connecting hole. DETAILED DESCRIPTION
[0023] In order to make the purpose, technical scheme and advantages of the present application more clear, the following will further describe the embodiments of the present application in combination with the drawings.
[0024] Please refer to Figs. 1 to 3 A wing structure of a UAV is provided according to the present embodiment, which mainly comprises the following parts: wing skin 1, wing body, unidirectional tape 3, wing reinforcing layer and wing-body connecting piece 5. The wing body is PMI foam 2.
[0025] The wing skin 1 is the outer covering of the wing, which directly contacts the external environment, provides the external form of the wing and plays a role of protecting the internal structure. The PMI foam 2 is the core filling material of the wing, which is located inside the wing skin 1. This foam material is not only light in quality, easy to process and low in cost, but also has good mechanical properties. The unidirectional tape 3 is arranged on the upper surface and the lower surface of the PMI foam 2 in the spanwise direction, which further enhances the structural strength of the wing. In addition, the wing reinforcing layer is attached to the middle part of the PMI foam 2, so as to form a wing reinforcing area 4 in the middle part of the PMI foam 2. The wing reinforcing area 4 is designed to enhance the structural stability of the central part of the wing and to transfer the moment at the wing root, so as to improve the strength and rigidity of the wing. The middle part of the wing reinforcing area 4 is also provided with a circular mounting hole, and the wing-body connecting piece 5 is installed in the mounting hole. The wing-body connecting piece 5 can be used for connecting the wing and the fuselage, and can realize quick replacement or maintenance of the wing and the fuselage (see Fig. 3 ).
[0026] In the above embodiment, the wing of the UAV not only can exhibit more excellent performance in flight, but also is easy to manufacture, which effectively reduces the cost of production, transportation and maintenance.
[0027] In the preferred embodiment, the wing skin 1 is composed of a whole piece of carbon fiber woven cloth or carbon fiber woven cloth and glass fiber cloth. The wing skin 1 needs to be cut according to the size of the wing surface area, and is a whole piece. The size of the cut area needs to be able to wrap the whole wing.
[0028] In the preferred embodiment, the PMI foam 2 is a polymethacrylic foam, which is a high-performance foam plastic material with good mechanical properties, high tensile strength, compressive strength and elastic modulus, and needs to be machined into a wing-shaped shape for fitting the wing mold and maintaining the wing shape. The PMI foam 2 includes a plurality of glued parts, which can be segmented and machined into a segmented shape, and finally connected together by gluing, for example, a plurality of glued parts are prepared first, and then glued along the wing span to form a PMI foam with a wing-shaped shape.
[0029] Notably, the middle section of the PMI foam 2 needs to be machined into a circular mounting hole for embedding the wing-body connector 5, and the mounting hole needs to be fitted with the wing-body connector.
[0030] In the preferred embodiment, the unidirectional tape 3 is a pre-impregnated unidirectional tape, which is a strip-shaped prepreg made of continuous fibers or unidirectional fabric impregnated with resin. The unidirectional tape 3 has better performance than the braided material, with good strength and toughness. In this embodiment, the unidirectional tape 3 mainly plays a traditional spar role, and needs to be arranged at 20-25% of the wing chord and 70-75% of the wing chord, and on both the upper and lower surfaces of the wing chord. It can be understood that the unidirectional tape 3 is divided into front and rear unidirectional tapes, the front unidirectional tape is arranged at 20-25% of the wing chord in the wing root to wing tip direction, and the rear unidirectional tape is arranged at 70-75% of the wing chord in the wing root to wing tip direction. The thickness of the unidirectional tape 3 needs to be calculated according to the aerodynamic force to obtain the required thickness of the unidirectional tape 3.
[0031] In the preferred embodiment, the wing reinforcing layer is a carbon fiber woven cloth, and the specific length and thickness can be determined according to the wing-body condition.
[0032] As shown in Fig. 3 In the preferred embodiment, the wing-body connector 5 is a cylindrical structure, and a plurality of connection holes are formed in the circumferential direction of the end face, which are used to connect the wing and the fuselage by screws. The wing-body connector 5 is a metal piece or a 3D printed piece, and the structure can be designed in advance according to the specific installation form and embedded in the PMI foam 2.
[0033] In the preferred embodiment, the wing shape of the unmanned aerial vehicle wing structure is a round head and tail shape, and the thickness gradually increases from the leading edge to the trailing edge and then gradually decreases.
[0034] The utility model also provides a manufacturing process for unmanned aerial vehicle wing structure, which can manufacture the above-mentioned unmanned aerial vehicle wing structure. The manufacturing process adopts a composite material mold pressing forming process, which simplifies the manufacturing process and reduces the production cost by one-time forming.
[0035] Preparation before manufacturing: Cut the required carbon fiber cloth according to the design size and shape of the wing. According to the needs of the internal structure of the wing, cut and process PMI foam 2 to match the geometry of the wing. Pre-cut unidirectional tape for use in the molding process. Pre-process the structure connecting the wing to the UAV fuselage. According to the electrical design requirements, prepare the cables that need to be embedded. Ensure that the mold is clean and free of foreign matter, and apply release agent to prevent the wing from sticking to the mold after molding.
[0036] The manufacturing process includes the following steps:
[0037] S1, mold preparation: Prepare the mold coated with release agent to ensure that the inner surface of the mold is smooth and flawless.
[0038] S2, lay the wing reinforcement area 4: Lay the wing reinforcement layer on the mold, and brush glue after each layer.
[0039] S3, lay the wing skin 1: First, the lower surface of the wing skin is attached to the mold, and the upper surface is first turned to the outside of the mold.
[0040] S4, lay the unidirectional tape 3: Lay the unidirectional tape of the prepreg along the front and rear lower surfaces of the wing.
[0041] S5, place the PMI foam 2: Place the PMI foam in the wing structure in the order and position according to the design.
[0042] S6, place the wing fuselage connecting piece 5: Place the wing fuselage connecting piece at the designed position.
[0043] S7, lay the unidirectional tape 3 on the upper surface: Lay the unidirectional tape on the upper surface of the wing.
[0044] S8, mold closing: Finally, fold the upper surface of the wing skin to the upper surface and close the mold. Glue should be applied at each step to ensure that the layers of material can be effectively bonded.
[0045] S9, molding: After the entire structure is completed, the mold is sent to the hot press tank for heating and pressure molding to ensure that all materials can be cured into a whole, forming the final wing structure. This method greatly simplifies the manufacturing process, reduces production costs, and ensures the quality and performance of the wing.
[0046] In this article, the front, rear, upper, lower, and other orientation words are defined by the position of the parts in the drawing and the position of the parts relative to each other in the drawing, only to express the technical solution clearly and conveniently. It should be understood that the use of orientation words should not limit the scope of the application claimed.
[0047] In the case of no conflict, the above-mentioned embodiments and features in the embodiments can be combined with each other.
[0048] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims
1. An unmanned aerial vehicle wing structure, characterized by, The wing skin, the wing body, the unidirectional tape, the wing reinforcing area and the wing body connecting piece are included; the wing body is PMI foam, the outer part of the wing body is attached with the wing skin; the upper surface and the lower surface of the wing body are provided with the unidirectional tape laid along the wingspan direction, the unidirectional tape is located in the wing skin, the middle part of the wing body is provided with the wing reinforcing area attached with the wing reinforcing layer, and the middle part of the wing reinforcing area is provided with the wing body connecting piece.
2. The wing structure of claim 1, wherein, The PMI foam is poly-methyl-methacrylate isocyan foam material.
3. The wing structure of claim 1, wherein, The wing skin is integrated carbon fiber woven cloth material or the combination material of carbon fiber woven cloth and glass fiber cloth.
4. The wing structure of claim 1, wherein, The wing body includes a plurality of glue parts, and the plurality of glue parts form the wing body by gluing along the wingspan direction.
5. The wing structure of claim 1, wherein, The unidirectional tape includes a front unidirectional tape and a rear unidirectional tape, the front unidirectional tape is arranged at 20%-25% of the chord in the wing root to wing tip direction, and the rear unidirectional tape is arranged at 70%-75% of the chord in the wing root to wing tip direction.
6. The wing structure of claim 5, wherein, The unidirectional tape is a prepreg unidirectional tape prepared by impregnating resin into continuous fibers or unidirectional fabric parallel to each other.
7. The wing structure of claim 1, wherein, The wing reinforcing layer is made of carbon fiber woven cloth.
8. The wing structure of claim 1, wherein, The wing reinforcing area is provided with a circular mounting hole, and the wing body connecting piece is fixed in the mounting hole.
9. The wing structure of claim 8, wherein, The wing body connecting piece is a cylindrical structure, and a plurality of connecting holes are arranged on the end face in the circumferential direction, and the connecting holes are used to connect the wing and the body by screws.
10. The wing structure of claim 1, wherein, The wing body is a round head and tail shape, and the thickness gradually increases from the leading edge to the trailing edge and then gradually decreases.