A UAV aileron structure

Abstract

The utility model provides a kind of unmanned aerial vehicle aileron structure, comprising: composite skin, it is cylindrical structure, and at least one weight-reducing hole is set on it and passes through, both ends of weight-reducing hole and the both ends of cylindrical structure are through-penetrating;Two mounting plates are respectively installed in the opposite two sides position of composite skin, and the side surface of mounting plate close to composite skin is provided with the protruding part compatible with the weight-reducing hole of composite skin, the protruding part can be embedded in weight-reducing hole, so that the end of mounting plate and composite skin is fixed together.The utility model can realize once solidification forming by the cooperation of composite skin and mounting plate, and the forming manufacturing operation of aileron can be completed, through end insertion type connection, ensure the high coaxiality of left and right mounting plates, forming process is simple, forming efficiency is higher, and it is more stable and safe, solve the problem of the difference of coaxiality, assembly complex, weak overall rigidity of traditional multi-component assembly aileron.

Description

Technical Field

[0001] This utility model relates to the field of aileron equipment technology for unmanned aerial vehicles (UAVs), specifically to an aileron structure for a UAV. Background Technology

[0002] Ailerons are movable wing surfaces installed on the trailing edge of the wing. They are the main control surfaces of the aircraft. The rolling moment generated by the pilot's differential deflection of the left and right ailerons can enable the aircraft to perform roll maneuvers.

[0003] Traditional composite material drone aileron structures typically employ a foam sandwich structure and metal embedded parts. This usually requires the preparation of an upper skin, a lower skin, foam core material, multiple metal embedded parts, and a large amount of adhesive. Each part needs to be prepared, processed, and positioned separately, which greatly increases the complexity of production and the amount of preparation work. As a result, the production process must be divided into multiple highly dependent and time-consuming stages.

[0004] Meanwhile, embedded metal parts may shift or tilt due to adhesive flow or vacuum pressure. This directly makes it difficult to guarantee the coaxiality of the left and right aileron pivots, thus affecting the smoothness of aileron movement and control accuracy. To prevent shifting, complex positioning fixtures need to be designed, which need to be removed after curing, further increasing the process and cost. There is also the uncontrollability of precise positioning and large-area bonding quality.

[0005] Considering the above factors, traditional composite material drone ailerons, due to their inherent multi-component and multi-process characteristics, require multiple and multi-stage curing processes, which greatly prolongs the manufacturing time. Furthermore, the molding process is complex, the coaxiality is poor, and the assembly is complicated, resulting in low overall molding efficiency. Utility Model Content

[0006] In view of this, the present invention provides a drone aileron structure, which can be designed as a one-time solidified aileron structure, completing multiple components in one molding process, realizing the integration and lightweighting of the aileron body, and ensuring high coaxiality of the left and right mounting plates through end insertion connection, simplifying the assembly process and improving the overall molding efficiency.

[0007] To solve the above-mentioned technical problems, this utility model provides a drone aileron structure, including: a composite skin, which is a cylindrical structure, and at least one weight reduction hole is provided through it, the two ends of the weight reduction hole are connected to the two ends of the cylindrical structure; Two mounting plates are respectively installed on opposite sides of the composite skin. The mounting plates have protrusions on the side closest to the composite skin that mate with the weight-reducing holes in the composite skin. These protrusions can be inserted into the weight-reducing holes, fixing the mounting plates to the ends of the composite skin. This invention achieves the aileron molding process in a single step through the cooperation of the composite skin and the mounting plates. The end-insertion connection ensures high coaxiality of the left and right mounting plates. The molding process is simple, efficient, and more stable and safe, solving the problems of poor coaxiality, complex assembly, and weak overall rigidity inherent in traditional multi-part aileron assemblies.

[0008] Composite skin, from the outside in, includes: The outer skin is a multi-segment annular columnar structure, with each segment made of continuous fiber prepreg. The fiber is carbon fiber, and the matrix resin is epoxy resin. Adjacent annular columns are bonded together with structural adhesive film. The outer skin is in direct contact with the air and bears the aerodynamic loads during flight, such as lift, drag, and bending moment. The segmented design allows for flexible switching between straight wing and trapezoidal wing airfoils. When changing the airfoil, only the corresponding segment of the skin needs to be replaced, without the need for overall mold opening, making the operation more convenient. Several inner skins, each with a ring-shaped structure, have a hollow cavity inside that corresponds one-to-one with the weight-reduction holes. They are made of the same carbon fiber as the outer skin, and the matrix resin is epoxy resin prepreg. The inner skins are arranged linearly along the skin axis, and adjacent inner skins and outer skins enclose an "I"-shaped storage space. The cavities in the hollow parts of the inner skins can reduce the weight of the ailerons. At the same time, the inner diameter of the inner skins is precisely matched with the protrusions of the mounting plate, providing a positioning reference for the mounting plate.

[0009] The outer skin is composed of multiple segments.

[0010] Composite skin also includes: Several filler blocks are placed between the inner and outer skins to form a storage space. They are divided into two categories: First, the flange filler blocks are made of carbon fiber prepreg fabric stacked together and tightly bonded to the outer and inner skins to enhance the local strength of the flanges and prevent flange deformation during handling. Second, the gap filler blocks are made of weather-resistant structural adhesive film to fill the tiny gaps between the inner and outer skins. After curing, they form a rigid structure with a certain hardness to prevent moisture intrusion and improve the overall integrity of the skin.

[0011] Multiple inner skins are arranged linearly, and an I-shaped storage space is formed between every two adjacent inner skins.

[0012] The outer wall of the protrusion has at least one groove, which is filled with an adhesive to bond the protrusion to the inner wall of the weight reduction hole.

[0013] The grooves are annular and distributed circumferentially on the outer wall of the protrusions.

[0014] Each mounting plate is equipped with a hinge.

[0015] The mounting plate has a threaded through hole, one end of the shaft is machined with an external thread that matches the threaded through hole, and the other end of the shaft is machined with a keyway for cooperating with the drone control stick; the shaft and the mounting plate are fixed by a threaded connection.

[0016] A molding process for an aileron structure of a drone includes the following steps: S1. Inner skin fabrication: Continuous fiber prepreg is pre-laid on the inner skin on the core mold to form a closed ring structure with openings on both sides. The core mold is made of aluminum alloy and coated with a release agent. S2. Fabrication of the lower half of the outer skin shell and filling block: The lower contour of the outer skin is laid in the mold cavity under the molding process, and the remaining upper half of the outer skin is suspended without being laid. The pre-laid inner skin is placed in the lower mold cavity, and the inner skin is bonded to the lower half of the outer skin. The gap area between the upper and lower parts is filled with adhesive film to make the filling block, outer skin and inner skin bonded together. S3. Fabrication of the upper shell of the outer skin: The suspended outer skin continuous fiber prepreg is continued to be laid and covered to the upper surface of the inner skin and the filler block to form the upper shell of the composite skin. S4. Forming of composite skin: After the upper and lower molds are closed, they are molded and solidified by a press, demolded and core mold one and core mold two are extracted. S5. Installation of mounting plate and pivot: After molding, the composite skin is formed into an integral "I" shaped structure. After cutting out the predetermined size, apply adhesive to the annular groove on the boss part and the protrusion part of the mounting plate and the bonding area of ​​the inner skin. A stable connection is achieved through the bonding method. Then, the pivot is directly installed onto the side mounting plate through the threaded connection method.

[0017] In summary, compared with the prior art, this application includes at least one of the following beneficial technical effects: 1. High coaxiality and precise control response: This utility model uses the end insertion positioning of the mounting plate protrusion and the weight reduction hole, combined with the precise design of the mounting plate thread hole and the protrusion, to greatly improve the overall coaxiality of the rotating shaft compared with traditional ailerons. During flight, the frictional resistance of the aileron rotation is greatly reduced, and the control response delay is greatly shortened, solving the problems of poor coaxiality and sluggish control of traditional ailerons.

[0018] 2. One-time curing molding, superior efficiency and cost: The composite skin of this utility model is formed by one-time molding and curing, eliminating the need for secondary assembly, greatly shortening the overall time and significantly improving production efficiency; the qualification rate of single aileron assembly is greatly improved, while avoiding the procurement and bonding costs of foam core, greatly reducing the production cost of single aileron, and solving the problems of complex and inefficient assembly of traditional ailerons.

[0019] 3. Balance between weight reduction and rigidity, strong load resistance: This utility model can greatly reduce the weight of the aileron through the weight reduction hole design, and greatly extend the flight range of the drone; the "I" shaped storage space combined with the carbon fiber filling block design greatly improves the bending stiffness of the aileron compared with the traditional foam sandwich structure, and can withstand higher strong airflow loads, solving the problem of the contradiction between weight reduction and rigidity and weak load resistance of traditional ailerons.

[0020] 4. Multi-segment outer skin, flexible and low-cost changeover: This utility model can adopt a multi-segment design for the outer skin. When changing the airfoil, only the corresponding segment of the skin needs to be replaced, without the need for overall mold opening. The changeover cycle is greatly shortened and the changeover cost is greatly reduced. It is compatible with various types of UAVs such as straight wings and trapezoidal wings, solving the problems of high changeover cost and poor adaptability of traditional ailerons. Attached Figure Description

[0021] Figure 1 This is an exploded view of the aileron structure of the UAV of this utility model; Figure 2 This utility model Figure 1 Schematic diagram of the middle section; Figure 3 This is a schematic diagram of the skin structure in the aileron structure of the UAV of this utility model; Figure 4 This is a schematic diagram of the molding die and skin structure for the aileron structure of the UAV of this utility model.

[0022] Explanation of reference numerals in the attached drawings: 100, composite skin; 101, weight reduction hole; 102, outer skin; 103, inner skin; 200, mounting plate; 210, protrusion; 211, groove; 220, threaded through hole; 300, shaft. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the following will be described in conjunction with the appendices of the embodiments of this utility model. Figure 1-4 The technical solutions of the embodiments of this utility model are clearly and completely described herein. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the described embodiments of this utility model are within the protection scope of this utility model.

[0024] like Figure 1-4As shown, this embodiment provides a drone aileron structure, including: a composite skin 100, which is a cylindrical structure, with the cross-sectional area of ​​the end near the drone control stick being larger than the cross-sectional area of ​​the other end, and at least one weight reduction hole 101 is provided through it, with the two ends of the weight reduction hole 101 communicating with the two ends of the cylindrical structure. Two mounting plates 200, which can be formed by CNC milling of aluminum alloy, are respectively installed on opposite sides of the composite skin 100. On the side of the mounting plate 200 near the composite skin 100, there are protrusions 210 that fit into the weight-reducing holes 101 of the composite skin 100. The protrusions 210 can be inserted into the weight-reducing holes 101, fixing the ends of the mounting plate 200 and the composite skin 100 together. The protrusions 210 are cylindrical structures that fit into the weight-reducing holes 101, and their number matches that of the weight-reducing holes 101. The gap between the outer diameter and the inner diameter of the inner skin 103 is less than or equal to 0.1mm, allowing them to be inserted into the weight-reducing holes 101 to form an "end-insertion" positioning. The contact area is increased by 2-3 times compared to traditional planar bonding. This directly ensures the coaxiality of the mounting plates 200 on both sides. At least one groove 211 is provided on the outer wall of the protrusion 210. The groove 211 is filled with an adhesive, which bonds the protrusion 210 to the inner wall of the weight-reducing hole 101. The groove 211 has an annular structure and is distributed circumferentially on the outer wall of the protrusion 210. Specifically, one or two annular grooves 211 are machined circumferentially on the outer wall of the protrusion 210 to store weather-resistant structural adhesive. After the adhesive cures, it forms a mechanical interlock with the inner wall of the inner skin 103, greatly increasing the shear strength of the bonding surface between the mounting plate 200 and the composite skin 100 to 25 MPa, preventing connection peeling caused by flight vibration. According to one embodiment of the present invention, such as Figure 1-4 As shown, the composite skin 100 includes, from the outside in: The outer skin 102 is composed of multiple segments, specifically a multi-segment annular columnar structure. Each segment is formed by laying and molding continuous fiber prepreg. The fiber is carbon fiber, and the matrix resin is epoxy resin. Adjacent annular columns are bonded together with structural adhesive film. The outer skin 102 is in direct contact with the air and bears the aerodynamic loads during flight, such as lift, drag, and bending moment. The segmented design allows for flexible switching between straight wing and trapezoidal wing airfoil. When changing the airfoil, only the corresponding segment of the skin needs to be replaced, without the need for overall mold opening, making the operation more convenient. According to another embodiment of the present invention, such as Figure 1 and Figure 3As shown, there are several inner skins 103, each with a ring-shaped structure. The hollow part inside is a cavity, which corresponds one-to-one with the weight reduction holes 101. The inner skins 103 are made of the same carbon fiber as the outer skin 102, and the matrix resin is epoxy resin prepreg. The inner skins 103 are arranged linearly along the skin axis. Adjacent inner skins 103 and outer skins 102 enclose an "I"-shaped storage space. The cavity inside the hollow part of the inner skin 103 can reduce the weight of the aileron. At the same time, the inner diameter of the inner skin 103 is precisely matched with the protrusion 210 of the mounting plate 200, providing a positioning reference for the mounting plate 200.

[0025] According to another embodiment of the present invention, such as Figure 3 and Figure 4 As shown, the composite skin 100 also includes: Several filler blocks are placed in the storage space formed between the inner skin 103 and the outer skin 102. They are divided into two categories: First, flange filler blocks: made of stacked T700 carbon fiber prepreg fabric blocks, which are tightly attached to the outer skin 102 and the inner skin 103 to enhance the local strength of the flange and prevent flange deformation during operation; Second, gap filler blocks: made of weather-resistant structural adhesive film, which fills the tiny gaps between the inner skin 103 and the outer skin 102. After curing, they form a rigid structure with a certain hardness to prevent moisture intrusion and improve the overall integrity of the skin.

[0026] Multiple inner skins 103 are arranged linearly, and an I-shaped storage space is formed between every two adjacent inner skins 103.

[0027] According to another embodiment of the present invention, such as Figure 1 and Figure 2 As shown, each mounting plate 200 is equipped with a pivot 300.

[0028] The mounting plate 200 has a threaded through hole 220. One end of the rotating shaft 300 is machined with an external thread that matches the threaded through hole 220, and the other end of the rotating shaft 300 is machined with a keyway for mates with the drone control stick. The rotating shaft 300 and the mounting plate 200 are fixed together by a threaded connection. Specifically, the rotating shaft 300 is made of titanium alloy and is precision machined. The threaded section mates with the threaded through hole 220 of the mounting plate 200. Tightening is performed using a torque wrench and then using thread-locking adhesive to prevent loosening. The other end of the rotating shaft 300 is machined with a keyway for connecting with the drone control stick via a flat key to achieve torque transmission. The surface of the rotating shaft 300 is treated with hard anodizing to improve its wear resistance. The mounting plate 200 has an internal threaded hole machined in its center. The coaxiality of the axis of the threaded hole and the axis of the protrusion 210 is less than or equal to 0.05 mm. This facilitates the threaded connection with the rotating shaft 300, further ensuring the assembly accuracy of the rotating shaft 300 and avoiding coaxiality deviation. This invention enables the aileron to be formed in one step through the cooperation of the composite skin 100 and the mounting plate 200. The end insertion connection ensures high coaxiality of the left and right mounting plates 200. The forming process is simple, the forming efficiency is high, and it is more stable and safe. It solves the problems of poor coaxiality, complex assembly, and weak overall rigidity of traditional multi-part aileron assembly.

[0029] like Figure 3 As shown, the composite skin 100 includes an outer skin 102, an inner skin 103-1, an inner skin 103-2, a filler block 1, and a filler block 2. The outer skin 102 is divided into a lower shell and an upper shell, which combine to form the outer contour of the aileron. The inner skins 103-1 and 103-2 are annular structures, which, together with the outer skin 102, form an "I"-shaped cross-section. The filler block 1 is located on the inner edge of the aileron's outer contour, and the filler block 2 is located at the gap between the inner skins 103-1, 103-2, and the outer skin 102. The aileron structure also includes a core mold 1 and a core mold 2. The inner skin 103-1 forms an annular structure by applying molding material to the outside of the core mold 1, and the inner skin 103-2 forms an annular structure by applying molding material to the outside of the core mold 2. After molding, core mold one is taken out from the annular cavity of inner skin 103-1, and core mold two is taken out from the annular cavity of inner skin 103-2. The protruding shape is adapted to the inner contour of inner skin 103-1 and inner skin 103-2 at both ends of composite skin 100. The protrusion is embedded in the annular cavity of inner skin 103-1 and inner skin 103-2 to form a positioning fit. Outer skin 102, inner skin 103-1, and inner skin 103-2 are all made of continuous fiber prepreg. The fibers in the continuous fiber prepreg include at least one of carbon fiber, glass fiber, and aramid fiber, and the matrix resin includes at least one of epoxy resin, phenolic resin, and bismaleimide resin. Filler block one is formed by stacking continuous fiber prepreg cloth blocks, and filler block two is a flowable structural adhesive film.

[0030] Working principle and molding process of this utility model: First, it needs to be clarified that the aileron structure involved in this utility model is mainly used for the manufacture of ailerons for drones. It is compatible with the drone's control stick. It should be noted that this solution does not limit the specific structure, manufacturer, or model of each electronic control component. Any existing electronic control component capable of processing and shaping the aileron while ensuring the required processing precision is acceptable. The materials used to implement the aileron structure, as well as the adhesives used to increase its stability and robustness, such as the material of the skin and the adhesive itself, can also be materials from existing technologies. This utility model will elaborate on the working principle and molding process of a drone aileron structure as an example. The working principle is as follows: The principle of high coaxiality is as follows: the protrusion 210 of the mounting plate 200 is precisely matched with the weight reduction hole 101, and after being embedded, it forms a mechanical positioning, which directly constrains the radial displacement of the mounting plates 200 on both sides; the coaxiality between the threaded hole of the mounting plate 200 and the protrusion 210 is less than or equal to 0.05mm, and after the rotating shaft 300 is fixed by the threaded connection, the overall coaxiality is strictly controlled, avoiding the accumulation of deviations in traditional secondary assembly; Rigid load-bearing and lightweight principle: The outer skin 102, as a bending member, bears the aerodynamic bending moment of flight; the inner skin 103 bears the cross-sectional shear force through the ring structure, and the two form a "shell plus rib" collaborative load-bearing system; the weight reduction hole 101 achieves lightweight through hollow design, while the filling block in the "I" shaped storage space specifically reinforces the weak areas of the flange to avoid local deformation; Weather-resistant sealing principle: After the adhesive film of the gap filling block cures, it fills the tiny gaps between the inner skin 103 and the outer skin 102, forming a continuous sealing layer to prevent moisture and dust from entering the interior of the skin; the annular groove 211 of the protrusion 210 of the mounting plate 200 stores adhesive to form an interlocking structure of "adhesive plus metal plus composite material" to prevent the bonding surface from peeling due to temperature changes. Control and transmission principle: The UAV control stick drives the rotating shaft 300 to rotate via a flat key, and the rotating shaft 300 drives the mounting plate 200 to rotate synchronously; since the mounting plate 200 and the composite skin 100 form a rigid whole through "the protrusion 210 fitting and gluing", the composite skin 100 rotates synchronously with the mounting plate 200, and the UAV roll attitude is adjusted by changing the aerodynamic shape of the wing surface.

[0031] The forming process of the aileron structure of a drone includes the following steps: Figure 4 As shown, S1. Fabrication of inner skin 103-1 and inner skin 103-2: Continuous fiber prepreg is pre-laid on inner skin 103-1 and inner skin 103-2 respectively on core mold 1 and 2, so that inner skin 103-1 and inner skin 103-2 form closed ring structures with openings on both sides respectively. S2. Fabrication of the lower half of the outer skin 102 shell, filler block one, and filler block two: The lower contour of the outer skin 102 is laid in the mold cavity under molding, while the remaining upper half of the outer skin 102 is left unlaid. The pre-laid inner skin 103-1 and inner skin 103-2 are placed together in the lower mold cavity, adhering to the lower half of the outer skin 102. The gaps between the upper and lower parts are filled with adhesive film. Filler block one is formed by stacking prepreg strips to a predetermined width and thickness and placing them at the flange position. Filler block one is adhered to both the outer skin 102 and inner skin 103-1. Filler block two is formed by stacking prepreg strips to a predetermined width and thickness and placing them in the gap between inner skin 103-1 and inner skin 103-2. Filler block two is adhered to both the outer skin 102, inner skin 103-1, and inner skin 103-2. S3. Fabrication of the upper shell of the outer skin 102: The suspended outer skin 102 continuous fiber prepreg is continued to be laid and covered to the upper surface of the inner skin 103-1, inner skin 103-2 and filling block 1 and filling block 2 to form the upper shell of the composite skin 100. S4. Forming of composite skin 100: After the upper and lower molds are closed, the core mold and core mold 1 and core mold 2 are molded and solidified by a press. S5. Installation of mounting plate 200 and pivot 300: After molding, the composite skin 100 is formed into an integral "I" shaped structure. After cutting out the predetermined size, adhesive is applied to the boss part, the annular groove 211 on the protrusion 210 of the mounting plate 200 and the bonding area of ​​the inner skin 103. A stable connection is achieved through the bonding method. Then, the pivot 300 is directly installed onto the side mounting plate 200 through the threaded connection method.

[0032] This invention can complete multiple components in one molding process by designing a one-time solidified aileron structure, thereby achieving the integration and lightweighting of the aileron body. The end insertion connection ensures high coaxiality of the left and right mounting plates 200, simplifies the assembly process, and improves the overall molding efficiency.

[0033] Furthermore, it should be noted that, in the description of this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0034] The above description is the preferred embodiment of this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this utility model, and these improvements and modifications should also be considered within the protection scope of this utility model.

Claims

1. A drone aileron structure, characterized by, include: The composite skin (100) is a columnar structure and has at least one weight-reducing hole (101) through it, the two ends of which are connected to the two ends of the columnar structure. Two mounting plates (200) are respectively installed on opposite sides of the composite skin (100). On the side of the mounting plate (200) near the composite skin (100), there is a protrusion (210) that matches the weight reduction hole (101) of the composite skin (100). The protrusion (210) can be inserted into the weight reduction hole (101) to fix the end of the mounting plate (200) to the composite skin (100).

2. The drone aileron structure of claim 1, wherein, The composite skin (100) includes, from the outside in: The outer skin (102) is a ring-shaped columnar structure that is in direct contact with the air; Several inner skins (103) are also ring-shaped structures, and the hollow part inside is a cavity.

3. The drone aileron structure of claim 2, wherein, The outer skin (102) is composed of multiple segments.

4. The drone aileron structure of claim 2, wherein, Composite skin (100) also includes: Several filling blocks are placed in the storage space formed between the inner skin (103) and the outer skin (102).

5. The UAV flap structure of any of claims 2-4, wherein: Multiple inner skins (103) are arranged linearly, and an I-shaped storage space is formed between every two adjacent inner skins (103).

6. The UAV flap structure of any one of claims 1-4, wherein: The outer wall of the protrusion (210) is provided with at least one groove (211), and the groove (211) is used to fill the adhesive, so that the protrusion (210) is bonded to the inner wall surface of the weight reduction hole (101) by the adhesive.

7. The drone aileron structure of claim 6, wherein: The groove (211) is a ring structure and is distributed circumferentially on the outer wall surface of the protrusion (210).

8. The drone aileron structure of claim 1, wherein: Each of the mounting plates (200) is provided with a pivot (300).

9. The drone aileron structure of claim 8, wherein: The mounting plate (200) has a threaded through hole (220), one end of the rotating shaft (300) is machined with an external thread that matches the threaded through hole (220), and the other end of the rotating shaft (300) is machined with a keyway for cooperating with the drone control stick; the rotating shaft (300) and the mounting plate (200) are fixed by threaded connection.

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