Trailing edge wedge for aircraft control surface structures and trailing edge wedge forming die

Abstract

The utility model provides a kind of aircraft control surface structure's trailing edge wedge and trailing edge wedge forming die, wherein, aircraft control surface structure's trailing edge wedge, comprising: preform, it is wedge-shaped, preform is woven from fiber material, and the fiber inside preform is angle interlocking interlaced structure;Matrix, resin material is integrally formed as trailing edge wedge with preform by closed mold process, and the resin part of trailing edge wedge forms matrix, and trailing edge wedge includes main body part connected with skin and the tip portion with tip end. The technical scheme of the utility model can effectively solve the problem that the conventional aircraft control surface structure in the prior art cannot simultaneously meet the good aerodynamic performance and light weight.

Description

Technical Field

[0001] This utility model relates to the field of aerospace technology, and more specifically, to a trailing edge wedge block and a mold for forming the trailing edge wedge block of an aircraft control surface structure. Background Technology

[0002] In the aviation field, aircraft control surfaces (such as flaps, ailerons, rudders, elevators, etc.) are important components of flight control. Their main function is to ensure that the aircraft can flexibly and stably adjust its flight attitude during flight by changing aerodynamics, meeting the needs of different flight phases. In order to achieve efficient aerodynamic performance, these control surfaces are usually designed with a convergent state at the trailing edge, that is, a wedge shape. Their geometric accuracy and structural stability directly affect the aircraft's control efficiency and aerodynamic noise level.

[0003] Traditional trailing edge wedge structures for aircraft control surfaces have numerous design and manufacturing drawbacks. From a structural design perspective, the common approach is to seal the trailing edge by gluing upper and lower panels together. In this configuration, the trailing edge height is approximately equal to the sum of the thicknesses of the upper and lower panels. However, in many aircraft wing structures, due to the aerodynamic requirements of the movable wing surfaces, the trailing edge wedge structure needs to have a relatively high height, while the upper and lower panels need to be designed to be thin, making traditional gluing sealing impractical. In such cases, using solid block sandwich structures for sealing not only increases the risk of delamination but also significantly increases the structural weight, thereby affecting the aircraft's fuel efficiency, range, and overall performance. Utility Model Content

[0004] The main objective of this invention is to provide a trailing edge wedge block and a mold for forming the trailing edge wedge block in an aircraft control surface structure, so as to solve the problem that traditional aircraft control surface structures in the prior art cannot simultaneously meet the requirements of good aerodynamic performance and light weight.

[0005] To achieve the above objectives, according to one aspect of the present invention, a trailing edge wedge block for an aircraft control surface structure is provided, comprising: a preform, wedge-shaped, the preform being woven from fiber material, and the internal fibers of the preform having an interlocking interwoven structure; a matrix, wherein resin material is integrally molded with the preform through a closed-mold process to form the trailing edge wedge block, the resin portion of the trailing edge wedge block forming the matrix, and the trailing edge wedge block including a main body portion connected to the skin and a tip portion having a pointed tip.

[0006] In one embodiment, the angle of the tip of the tip ranges from 10° to 15°.

[0007] In one embodiment, the fiber volume content in the preform is 50% to 60%, and the weaving angle of the internal fibers in the preform is within 28±3°.

[0008] In one embodiment, the porosity of the trailing edge wedge is less than or equal to 1.5%.

[0009] In one embodiment, a groove extending through the width of the main body is provided on each of the two opposite sides of the main body, and a connecting structure for connecting with the skin is provided in the groove.

[0010] According to another aspect of the present invention, a trailing edge wedge block forming mold is provided. The trailing edge wedge block forming mold is used to form the aforementioned trailing edge wedge block. The trailing edge wedge block forming mold includes: an upper mold; a lower mold, opposite to the upper mold, with a mold cavity for placing a preform of the trailing edge wedge block between the upper mold and the lower mold, the mold cavity being a wedge shape adapted to the shape of the preform, the mold cavity including a tip cavity and a main body cavity that are interconnected, the tip of the trailing edge wedge block being formed in the tip cavity, and the main body of the trailing edge wedge block being formed in the main body cavity; and an injection port, disposed on the upper mold or the lower mold and communicating with the mold cavity.

[0011] In one embodiment, a first guide net is provided on the wall of the tip cavity, and a second guide net is provided on the wall of the main cavity, wherein the permeability of the first guide net is greater than that of the second guide net.

[0012] In one embodiment, the first guide net has diamond-shaped mesh openings with a side length between 3 and 5 mm; and / or, the second guide net has square mesh openings with a side length between 1 and 2 mm.

[0013] In one embodiment, the upper or lower mold is provided with a main injection port that communicates with the main body cavity and a secondary injection port that communicates with the tip cavity, and the main injection port and the secondary injection port form an injection port.

[0014] In one embodiment, the main injection port is located in the middle of the upper or lower mold in the width direction of the rear edge wedge block forming mold, and there are two secondary injection ports located on both sides of the corresponding upper or lower mold in the width direction of the rear edge wedge block forming mold.

[0015] By applying the technical solution of this utility model, the trailing edge wedge block of the aircraft control surface structure is formed by an integrated closed-mold process using a preform woven from fiber material and resin material, achieving an angular interlocking interwoven structure of the fibers inside the trailing edge wedge block. This angular interlocking interwoven structure endows the preform with highly balanced mechanical properties, improving the weakness in the Z-direction and enhancing the structural stability and load-bearing capacity of the trailing edge wedge block. By injecting resin into the preform under preset temperature and pressure conditions, the resin achieves full impregnation and curing of the fiber material, ensuring structural integration between the main body and the tip of the trailing edge wedge block during the molding process. Furthermore, the tip angle of the trailing edge wedge block in the above structure can be designed to be smaller, thereby optimizing the aerodynamic performance of the aircraft control surface and reducing flight drag. Through this structure, this utility model effectively solves the problem that traditional aircraft control surface structures cannot simultaneously achieve good aerodynamic performance and light weight, improving the performance and flight safety of aircraft control surfaces.

[0016] In addition to the objectives, features, and advantages described above, this utility model has other objectives, features, and advantages. The present utility model will now be described in further detail with reference to the figures. Attached Figure Description

[0017] The accompanying drawings, which form part of this specification, are used to provide a further understanding of this utility model. The illustrative embodiments and descriptions of this utility model are used to explain this utility model and do not constitute an undue limitation thereof. In the drawings:

[0018] Figure 1 A three-dimensional structural schematic diagram of an embodiment of the trailing edge wedge block of the aircraft control surface structure according to the present invention is shown;

[0019] Figure 2 It shows Figure 1 A schematic diagram of the preform of the trailing edge wedge block during the weaving process;

[0020] Figure 3 It shows Figure 1 A three-dimensional structural diagram showing the rear edge wedge block installed behind the skin assembly; and

[0021] Figure 4 A three-dimensional structural schematic diagram of the trailing edge wedge block forming mold according to the present invention is shown.

[0022] The above figures include the following reference numerals:

[0023] 10. Rear edge wedge block; 11. Main body; 12. Tip; 13. Groove; 41. Upper mold; 42. Lower mold; 43. Mold cavity; 431. Tip cavity; 432. Main body cavity; 50. First guide net; 60. Second guide net; 70. Main injection port; 80. Secondary injection port. Detailed Implementation

[0024] It should be noted that, where there is no conflict, the embodiments and features in the embodiments of this utility model can be combined with each other. The present utility model will now be described in detail with reference to the accompanying drawings and embodiments.

[0025] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the protection scope of the present invention.

[0026] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this utility model are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such terms can be used interchangeably where appropriate for the embodiments of the utility model described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0027] It should be noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the exemplary embodiments according to this application. As used herein, the singular form is intended to include the plural form as well, unless the context clearly indicates otherwise. Furthermore, it should be understood that when the terms "comprising" and / or "including" are used in this specification, they indicate the presence of features, steps, operations, devices, components, and / or combinations thereof.

[0028] In the aviation field, the trailing edge of aircraft control surfaces is designed with a wedge-shaped structure to achieve efficient aerodynamic performance. However, traditional designs face many challenges, including: the contradiction between height and thickness in the method of sealing the trailing edge by bonding the upper and lower skins together, which cannot simultaneously meet the requirements of structural height and thin skin; and the use of solid block sandwich sealing increases the structural weight, increases the risk of delamination, and has an adverse effect on the aircraft's fuel efficiency, range, and overall performance.

[0029] After observing the limitations of the prior art, the inventors discovered that the main load-bearing parts of the aircraft control surface structure are the upper and lower skins, while the trailing edge wedge block has relatively lower load-bearing requirements. Based on this discovery, the inventors proposed designing a trailing edge wedge block made of woven material while maintaining the original structure of the upper and lower skins. This design can meet strict aerodynamic performance requirements while significantly reducing structural weight.

[0030] like Figures 1 to 3 As shown, this embodiment provides a trailing edge wedge block for an aircraft control surface structure, including a preform and a substrate. The preform is wedge-shaped and woven from fiber material, with the internal fibers forming an interlocking angular structure. Resin material is integrally molded with the preform using a closed-mold process to form the trailing edge wedge block 10. The resin portion of the trailing edge wedge block 10 forms the substrate. The trailing edge wedge block 10 includes a main body 11 connected to the skin and a tip 12 with a pointed end.

[0031] Applying the technical solution of this embodiment, the trailing edge wedge block 10 of the aircraft control surface structure is formed by an integrated closed-mold process using a preform woven from fiber material and resin material, achieving an angular interlocking interwoven structure of the internal fibers of the trailing edge wedge block 10 (i.e., an angular interlocking interwoven structure of X / Y / Z three-dimensional fiber bundles). This angular interlocking interwoven structure endows the preform with highly balanced mechanical properties, improving the weakness in the Z-direction and enhancing the structural stability and load-bearing capacity of the trailing edge wedge block 10. By injecting resin into the preform under preset temperature and pressure conditions, the resin achieves full impregnation and curing of the fiber material, ensuring structural integration of the main body 11 and the tip 12 of the trailing edge wedge block 10 during the molding process. Furthermore, the tip angle of the tip 12 of the trailing edge wedge block 10 can be designed to be smaller, thereby optimizing the aerodynamic performance of the aircraft control surface and reducing flight drag. Through the above structure, the technical solution of this embodiment effectively solves the problem that traditional aircraft control surface structures cannot simultaneously satisfy good aerodynamic performance and light weight, improving the performance and flight safety of the aircraft control surface.

[0032] Preferably, in this embodiment, the mold closing process is an RTM molding process.

[0033] In this embodiment, the angle of the tip of the tip 12 ranges from 10° to 15°. This structure optimizes the aerodynamic performance of the aircraft control surfaces, ensuring optimal aerodynamic effects under high-speed flight conditions while reducing drag. By controlling the tip angle within a specific range, the geometric accuracy requirements of the tip wedge block on the aircraft control surfaces are met.

[0034] Furthermore, in this embodiment, the fiber volume content in the preform is 50% to 60%, and the weaving angle of the internal fibers in the preform is within 28±3°. This structure ensures that the preform possesses highly balanced mechanical properties in the X, Y, and Z directions. Through the interlocking interwoven structure, the preform can achieve uniform load distribution and effective load transfer, thereby significantly enhancing the overall performance of the structure. Specifically, when the fiber volume content is less than 50%, the fiber content is low. Since the performance of the composite material is mainly provided by the fibers, while the resin plays a bonding and protective role, a lower fiber content will reduce the stiffness and strength of the composite material. Insufficient fiber content will lead to a decrease in the structural load-bearing capacity, increasing the risk of deformation and failure of the composite material under external forces. Secondly, excessive resin may cause significant shrinkage during curing, leading to pores or cracks inside the preform, which not only affects the mechanical properties of the material but may also reduce its corrosion resistance and fatigue life. In addition, excessive resin may also lead to increased weight. Conversely, if the fiber volume content is greater than 60%, problems such as uneven resin distribution and increased porosity may arise. The resin not only needs to fully penetrate between fibers to form a strong bond, but also needs to provide necessary mechanical properties during curing, such as impact toughness and interlaminar shear strength. Excessive fiber content restricts resin flow, making it difficult for the resin to completely fill the gaps between fibers, leading to increased porosity. The presence of pores becomes stress concentration points, reducing the damage tolerance and fatigue performance of the composite material. Furthermore, insufficient resin can affect fiber bundle fixation, reducing the stability of the preform during molding and potentially causing fiber bundle displacement or damage, ultimately affecting the geometric accuracy and appearance quality of the composite component. Therefore, proper control of fiber volume content is a key factor in ensuring excellent structural performance and production quality of composite preforms.

[0035] In this embodiment, the porosity of the trailing edge wedge 10 is less than or equal to 1.5%. This parameter is achieved through the high fiber volume ratio of the three-dimensional braided composite material and the control of the RTM molding process. Low porosity ensures structural density and good resin matrix filling, thereby improving the mechanical properties and fatigue resistance of the trailing edge wedge 10. During the molding process, the resin fully impregnates the braided fibers under high temperature and pressure. Combined with an optimized mold and resin flow path, this ensures that the resin can smoothly penetrate every corner of the fiber preform, thereby reducing pore formation and enhancing the overall structural integrity. Furthermore, low porosity effectively prevents the intrusion of moisture and oxygen, reducing the risk of material degradation due to environmental factors and ensuring the stability and reliability of the trailing edge wedge 10 during long-term use.

[0036] like Figure 1 and Figure 3 As shown, in this embodiment, grooves 13 extending along the width direction of the main body 11 are provided on both opposite sides of the main body 11. A connecting structure for connection with the skin is provided within the grooves 13. Specifically, the grooves 13 ensure that the outer surface of the tip 12 is flush with the outer surface of the skin assembly after the skin assembly is installed on the main body 11, achieving a continuous and smooth transition in aerodynamic shape. This structure effectively avoids turbulence and separation at the connection between the trailing edge wedge block 10 and the skin assembly, thereby reducing aerodynamic drag during flight and improving flight efficiency. Furthermore, during connection, the skin assembly is placed in the grooves 13 and connected via the connecting structure (high-strength bolts), making the overall structure more stable and reliable, reducing maintenance and repair work, and extending the service life of the aircraft control surfaces. In addition, the design of the grooves 13 also helps reduce resin accumulation and avoids the formation of excessive resin nodules at the connection, further improving the quality and appearance of the product. In summary, the groove design of this embodiment not only improves aerodynamic performance but also brings significant improvements in product quality.

[0037] It should be noted that, as Figure 1 As shown, the recessed area of ​​the dashed line forms the aforementioned groove 13, which is provided on the upper and lower sides of the main body 11.

[0038] It should also be noted that the connection between the main body 11 and the tip 12 is made of rounded corners, and the above structure can avoid stress concentration and resin accumulation.

[0039] like Figure 4As shown, this application also provides a trailing edge wedge forming mold. According to an embodiment of the trailing edge wedge forming mold of this application, the trailing edge wedge forming mold is used to form the aforementioned trailing edge wedge 10. The trailing edge wedge forming mold includes: an upper mold 41, a lower mold 42, and an injection port. The lower mold 42 is opposite to the upper mold 41, and a mold cavity 43 for placing a preform of the trailing edge wedge 10 is provided between the upper mold 41 and the lower mold 42. The mold cavity 43 is wedge-shaped and adapted to the shape of the preform. The mold cavity 43 includes a tip cavity 431 and a main body cavity 432 that are interconnected. The tip portion 12 of the trailing edge wedge 10 is formed in the tip cavity 431, and the main body portion 11 of the trailing edge wedge 10 is formed in the main body cavity 432. The injection port is disposed on the upper mold 41 and communicates with the mold cavity 43.

[0040] The trailing edge wedge block molding die of this embodiment complements the characteristics of the aforementioned trailing edge wedge block 10, providing crucial support for the manufacturing of high-performance aircraft control surface structures. The die employs a closed design of upper die 41 and lower die 42, jointly defining a wedge-shaped mold cavity 43 that perfectly matches the shape of the preform. This structure ensures the precise geometric dimensions of the trailing edge wedge block 10 during the molding process, meeting stringent requirements for aerodynamic shape and thus reducing aerodynamic drag during flight. The mold cavity 43 is internally divided into a tip cavity 431 and a main body cavity 432, corresponding to the tip portion 12 and the main body portion 11 of the preform, respectively. This gradient layout optimizes the flow and distribution of resin in different areas. The interconnected design of the tip cavity 431 and the main body cavity 432, combined with the injection port located on the upper die 41 or lower die 42, allows for controlled resin injection, ensuring the quality of the final product. Therefore, the trailing edge wedge block forming mold of this application can not only greatly improve the forming accuracy, but also ensure the lightweight of the trailing edge wedge block 10, effectively solving the problem that traditional aircraft control surface structures cannot simultaneously meet the requirements of good aerodynamic performance and light weight, thus improving the performance of aircraft control surfaces and flight safety.

[0041] Preferably, in other embodiments, the injection port is located on the lower mold 42.

[0042] like Figure 4As shown, in this embodiment, a first guide net 50 is provided on the cavity wall of the tip cavity 431, and a second guide net 60 is provided on the cavity wall of the main body cavity 432. The permeability of the first guide net 50 is greater than that of the second guide net 60. This structure achieves multi-gradient resin flow during the molding process of the trailing edge wedge block 10 through different permeability rates, ensuring uniform resin filling and structural integrity in the tip portion 12 and the main body portion 11. Specifically, the high permeability of the first guide net 50 facilitates rapid and deep resin penetration into the tip portion 12, overcoming the flow resistance caused by the geometric complexity of this area. The lower permeability of the second guide net 60 adapts to the high fiber density requirements of the main body portion 11, ensuring sufficient resin distribution in the main body area. Through this technical solution, not only is the problem of uneven resin distribution in complex structures solved, but porosity is also effectively controlled, ensuring the high performance and low weight characteristics of the trailing edge wedge block 10, thereby improving the overall aerodynamic performance and connection stability of the aircraft control surface structure.

[0043] In this embodiment, the first flow guide net 50 has diamond-shaped mesh openings with a side length between 3-5 mm, while the second flow guide net 60 has square mesh openings with a side length between 1-2 mm. Specifically, the above structure adopts a multi-gradient flow guide network layout strategy to optimize the resin flow characteristics in the RTM process. Specifically, the large size of the diamond-shaped mesh openings facilitates rapid resin penetration at the tip 12, solving the resin flow problem caused by the complex geometry of the tip region, ensuring uniform resin filling at the tip 12, and reducing the risk of insufficient resin at the tip. The main body 11 uses small-sized square mesh openings. This dense flow guide structure helps improve the accuracy of resin penetration, especially suitable for the high fiber volume content requirements of the main body 11, ensuring the structural strength and stability of the main body 11. Through the above structure, not only is uniform resin distribution promoted throughout the trailing edge wedge 10, but porosity is also effectively controlled, ensuring the high quality and high performance of the final product. In summary, the airflow guide net design in this embodiment, combining three-dimensional woven preform and RTM molding process, achieves both aerodynamic performance and lightweight design of the aircraft control surface structure, significantly improving the overall performance of the aircraft control surface.

[0044] like Figure 4As shown, in this embodiment, the upper mold 41 is provided with a main injection port 70 communicating with the main cavity 432 and a secondary injection port 80 communicating with the tip cavity 431. The main injection port 70 and the secondary injection port 80 form an injection port. Specifically, through the synergistic effect of the main injection port 70 and the secondary injection port 80, the resin can be more evenly distributed to various parts of the preform, especially the tip cavity 431, thereby ensuring the resin filling effect of the tip 12 and avoiding problems such as insufficient resin or uneven resin distribution in the tip 12. Therefore, the above structure not only improves the molding quality of the trailing edge wedge block 10, but also reduces defects in the curing process, such as pores and cracks, further enhancing the stability and reliability of the structure. In addition, by precisely controlling the resin injection path and speed, the mold making using the above structure can also effectively shorten the molding cycle, reduce production costs, and improve production efficiency. Preferably, in other embodiments, both the main injection port 70 and the secondary injection port 80 are provided on the lower mold 42.

[0045] like Figure 4 As shown, in this embodiment, the main injection port 70 is located in the middle of the upper mold 41 in the width direction of the trailing edge wedge block molding die. Two secondary injection ports 80 are located on either side of the upper mold 41 in the width direction of the trailing edge wedge block molding die. This arrangement of injection ports effectively promotes uniform resin flow and distribution during the RTM process, especially between the tip 12 and the main body 11 of the trailing edge wedge block 10. This ensures that the resin can quickly and completely fill the entire preform, thereby reducing the risk of insufficient resin at the tip and avoiding uneven resin distribution in the main body 11. This design achieves efficient molding of the trailing edge wedge block 10, ensuring its structural integrity and consistent mechanical properties, providing a high-quality base component for subsequent aircraft control surface assembly. In other embodiments not shown in the figure, the position and number of the main injection port 70 and secondary injection ports 80 can be adjusted to accommodate the molding requirements of trailing edge wedge blocks 10 with different geometries and sizes, further optimizing the resin flow path and improving molding accuracy and production efficiency.

[0046] In the fabrication process of the trailing edge wedge block of this application, firstly, a preform is woven using a three-dimensional weaving process. The preform is composed of fibrous material, with internal fibers arranged in an interlocking angular structure. The fiber volume content is controlled between 50% and 60%, and the weaving angle is set within the range of 28±3°. Next, the preform is precisely placed in a mold, which includes an upper mold and a lower mold, forming a mold cavity that matches the shape of the preform. The mold cavity is divided into a tip cavity and a main body cavity. The tip portion of the preform is placed in the tip cavity, while the main body portion is located in the main body cavity. Each cavity wall is equipped with a first and a second flow guide net with different permeability to optimize resin flow. Subsequently, low-viscosity epoxy resin is injected into the mold cavity through the main injection port and the secondary injection port, and RTM molding is performed under preset temperature and pressure conditions. The resin fully impregnates the fiber preform and cures. The tip angle of the tip portion is between 10° and 15°, ensuring good aerodynamic performance. After curing, the trailing edge wedge block undergoes post-processing, including sanding and trimming to remove excess resin and burrs, and machining holes at the connection points for mounting high-strength bolts to achieve a secure connection with the skin assembly. The entire manufacturing process precisely controls the fiber layout of the preform, resin penetration, and temperature and pressure conditions, effectively reducing porosity and ensuring the high performance, low weight, and excellent aerodynamic characteristics of the aircraft control surface structure with the trailing edge wedge block installed.

[0047] Unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps described in these embodiments do not limit the scope of this invention. It should also be understood that, for ease of description, the dimensions of the various parts shown in the drawings are not drawn to actual scale. Techniques, methods, and devices known to those skilled in the art may not be discussed in detail, but where appropriate, such techniques, methods, and devices should be considered part of the specification. In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters in the following drawings denote similar items; therefore, once an item is defined in one drawing, it need not be further discussed in subsequent drawings.

[0048] For ease of description, spatial relative terms such as "above," "on top of," "on the upper surface of," "above," etc., are used herein to describe the spatial positional relationship of a device or feature as shown in the figures to other devices or features. It should be understood that spatial relative terms are intended to encompass different orientations in use or operation beyond the orientation of the device as described in the figures. For example, if the device in the figures were inverted, a device described as "above" or "on top of" other devices or structures would subsequently be positioned as "below" or "under" other devices or structures. Thus, the exemplary term "above" can include both "above" and "below." The device may also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatial relative descriptions used herein will be interpreted accordingly.

[0049] In the description of this utility model, it should be understood that the directional terms such as "front, back, up, down, left, right", "horizontal, vertical, horizontal" and "top, bottom" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this utility model and simplifying the description. Unless otherwise stated, these directional terms do not indicate or imply that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on the scope of protection of this utility model. The directional terms "inner" and "outer" refer to the inner and outer contours of each component itself.

[0050] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A trailing edge wedge block for an aircraft control surface structure, characterized in that, include: The preform is wedge-shaped and is woven from fiber material, with the internal fibers of the preform having an interlocking angular interwoven structure. The matrix and resin material are integrally formed with the preform into a rear edge wedge block (10) through a closed-mold process. The resin part of the rear edge wedge block (10) forms the matrix. The rear edge wedge block (10) includes a main body (11) connected to the skin and a tip (12) with a pointed tip.

2. The trailing edge wedge block of the aircraft control surface structure according to claim 1, characterized in that, The angle of the tip of the tip (12) is between 10° and 15°.

3. The trailing edge wedge block of the aircraft control surface structure according to claim 1, characterized in that, The fiber volume content in the preform is 50% to 60%, and the weaving angle of the internal fibers in the preform is within 28±3°.

4. The trailing edge wedge block of the aircraft control surface structure according to claim 1, characterized in that, The porosity of the trailing edge wedge block (10) is less than or equal to 1.5%.

5. The trailing edge wedge block of the aircraft control surface structure according to claim 1, characterized in that, The main body (11) has grooves (13) extending through the width of the main body (11) on its two opposite sides, and a connecting structure for connecting to the skin is provided in the grooves (13).

6. A mold for forming a trailing edge wedge block, characterized in that, The trailing edge wedge forming mold is used to form the trailing edge wedge (10) according to any one of claims 1 to 5, the trailing edge wedge forming mold comprising: Upper mold(41); The lower mold (42) is opposite to the upper mold (41). Between the upper mold (41) and the lower mold (42) is a mold cavity (43) for placing the preform of the rear edge wedge block (10). The mold cavity (43) is wedge-shaped and adapted to the shape of the preform. The mold cavity (43) includes a tip cavity (431) and a main body cavity (432) that are interconnected. The tip (12) of the rear edge wedge block (10) is formed in the tip cavity (431), and the main body (11) of the rear edge wedge block (10) is formed in the main body cavity (432). The injection port is located on the upper mold (41) or the lower mold (42) and communicates with the mold cavity (43).

7. The trailing edge wedge block forming mold according to claim 6, characterized in that, The tip cavity (431) is provided with a first guide net (50) on its cavity wall, and the main cavity (432) is provided with a second guide net (60) on its cavity wall. The permeability of the first guide net (50) is greater than that of the second guide net (60).

8. The trailing edge wedge block forming mold according to claim 7, characterized in that, The first guide net (50) has diamond-shaped mesh holes with a side length between 3-5 mm; and / or, the second guide net (60) has square mesh holes with a side length between 1-2 mm.

9. The trailing edge wedge block forming mold according to claim 6, characterized in that, The upper mold (41) or lower mold (42) is provided with a main injection port (70) communicating with the main body cavity (432) and a secondary injection port (80) communicating with the tip cavity (431), and the main injection port (70) and the secondary injection port (80) form the injection port.

10. The trailing edge wedge block forming mold according to claim 9, characterized in that, The main injection port (70) is located in the middle of the upper mold (41) or the lower mold (42) in the width direction of the rear edge wedge block forming mold. The secondary injection ports (80) include two, and the two secondary injection ports (80) are located on both sides of the corresponding upper mold (41) or lower mold (42) in the width direction of the rear edge wedge block forming mold.

Images