Structurally functional integrated composite airfoil and method of forming

Abstract

The application relates to a structure-function integrated composite airfoil and a forming method thereof. The structure-function integrated composite airfoil comprises a wing joint, a composite airfoil, an antenna, an antenna cable channel, a wave-transparent reinforcing beam and an antenna upper and lower protective cover; the wing joint is fixedly connected with the composite airfoil; the antenna is embedded in the leading edge of the composite airfoil; the antenna cable channel is located in the interior of the composite airfoil and is laid to the wing root part of the trailing edge; an outlet hole is arranged on the wing joint, and the antenna cable channel is led out from the outlet hole; the wave-transparent reinforcing beam is embedded in the position close to the leading edge of the airfoil in front of the antenna; the composite airfoil, the wave-transparent reinforcing beam and the antenna upper and lower protective cover are integrally formed through co-curing. The antenna is embedded in the leading edge of the airfoil, the antenna protective cover, the wave-transparent reinforcing beam in front of the antenna and the composite airfoil are integrally formed through co-curing, and the overall structure and reliability are improved.

Description

Technical Field

[0001] This invention relates to a structurally and functionally integrated composite material airfoil and its molding method, belonging to the field of composite material design and molding technology. Background Technology

[0002] Composite material wings possess excellent mechanical properties such as high specific stiffness and specific strength, good fatigue resistance, and corrosion resistance, and have been widely used in aerospace structures. Installing antennas on the composite material wings of airborne early warning vehicles offers advantages such as high orbital range, wide field of view, and minimal obstruction from terrain, enabling wide-area surveillance and continuous coverage. These antennas can remain airborne for extended periods, collecting large amounts of stable and reliable intelligence information. They also offer a downward-diving detection advantage against stealth aircraft, making it easier to detect stealth targets and effectively addressing the defense and early warning vulnerabilities caused by the shortcomings of ground / sea-based early warning systems.

[0003] Designing composite material wings and antennas as an integrated structure not only increases the antenna area but also reduces the impact of antenna installation on the aircraft's aerodynamic performance. Therefore, achieving a structurally and functionally integrated structure for composite material wings and antennas is of great significance, and existing technologies do not provide a satisfactory solution. Summary of the Invention

[0004] The purpose of this invention is to provide a structurally and functionally integrated composite material wing and its molding method. The wing embeds an antenna in the front edge of the wing, and the wave-transparent antenna protective cover, the forward wave-transparent beam of the antenna, and the composite material wing are co-cured and integrally molded, thereby improving the integrity and reliability of the structure.

[0005] The technical solution adopted in this invention is as follows:

[0006] A structurally and functionally integrated composite material wing includes a wing joint, a composite material wing, an antenna, an antenna cable channel, a wave-transparent reinforcing beam, and upper and lower antenna protective covers. The wing joint is fixedly connected to the composite material wing. The antenna is embedded in the leading edge of the composite material wing. The antenna cable channel is located inside the composite material wing and extends to the wing root at the trailing edge. A cable outlet hole is provided on the wing joint, and the antenna cable channel is led out from the cable outlet hole. The wave-transparent reinforcing beam is embedded in the forward-facing part of the antenna near the leading edge of the wing. The composite material wing, the wave-transparent reinforcing beam, and the upper and lower antenna protective covers are co-cured and formed.

[0007] Furthermore, based on the design load required for the airfoil, as well as the material properties, weight, and simulation calculation results, the fibers of the composite airfoil are carbon fiber, quartz fiber, or glass fiber, and the resin is epoxy resin, cyanate ester resin, or polyether ether ketone resin.

[0008] Furthermore, the wave-transparent material reinforced beam is made of composite material, wherein the fibers are wave-transparent material fibers, and the resin is epoxy resin, cyanate ester resin, or polyether ether ketone resin. The resin curing conditions are the same as those for the composite material airfoil. The dielectric constant of the composite material used in the wave-transparent material reinforced beam is not greater than 4.0.

[0009] Furthermore, the upper and lower protective covers of the antenna are made of composite materials, wherein the fibers are made of wave-transparent materials, and the resin is made of epoxy resin, cyanate ester resin, or polyether ether ketone resin. The resin curing conditions are the same as those of the composite material wing surface. The dielectric constant of the composite material used in the upper and lower protective covers of the antenna is not greater than 4.0.

[0010] Furthermore, the upper and lower protective covers of the antenna are provided with flanges at the edges, and are co-cured with the composite material wing surface using adhesives with the same curing conditions. The flanges increase the bonding area between the upper and lower protective covers of the antenna and the composite material wing surface.

[0011] Furthermore, the antenna and the antenna cable channel are made of aluminum alloy, and the antenna cable channel is a circular or square thin-walled hollow structure with a wall thickness of 1-2 mm.

[0012] Furthermore, the wing joint and the composite material wing surface are fixedly connected by a plug-in method; the wing joint is provided with a shaft hole and a lug hole, wherein the shaft hole is used to install the joint positioning shaft, and the lug hole is used to install the lug positioning pin, so as to assist in the curing and molding of the wing surface.

[0013] Furthermore, the wing joint is made of a metal material, which is one of the following: stainless steel, titanium alloy, or aluminum alloy.

[0014] A method for forming a structurally and functionally integrated composite material airfoil includes the following steps:

[0015] Perform lower wing surface layup of composite material wing surfaces;

[0016] Place the wing connector and antenna cable channel in the reserved groove. The antenna cable channel runs from the front edge of the wing to the rear edge and exits through the cable outlet hole of the wing connector.

[0017] Perform upper surface layup of composite material wing surfaces;

[0018] Lay up the wave-transmitting enhancement beam and the upper and lower protective covers of the antenna;

[0019] The laid composite material wing surface, wave-transparent reinforcing beam, and upper and lower antenna protective covers are co-cured and molded, and then demolded to obtain a structurally and functionally integrated composite material wing surface.

[0020] Furthermore, the wing joint is made of metal, and the insertion part is sandblasted to improve the connection strength between the metal joint and the composite material wing surface.

[0021] The beneficial effects of this invention are as follows:

[0022] This invention embeds the antenna into the leading edge of the wing. The upper and lower protective covers, the forward reinforcing beam, and the composite material wing surface are all made of the same resin and co-cured under the same curing conditions, improving the overall integrity and reliability of the structure, reducing the impact of the environment on the antenna, and effectively extending the antenna's lifespan. The upper and lower protective covers and the forward reinforcing beam are made of quartz fiber or glass fiber, while the composite material wing surface is made of carbon fiber, ensuring the load-bearing capacity of the main load-bearing surface while achieving the antenna function. The forward reinforcing beam increases the stiffness and strength of the leading edge, suppressing torsional deformation at the antenna notch area. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the overall structure of a structurally functional composite material airfoil according to an embodiment of the present invention.

[0024] Figure 2 This is a schematic diagram of the structure of a wing joint according to an embodiment of the present invention.

[0025] Figure 3 This is a schematic diagram of the upper and lower protective covers of an antenna according to an embodiment of the present invention.

[0026] Figure 4 This is a flowchart illustrating the steps of a method for forming a structurally and functionally integrated composite airfoil according to an embodiment of the present invention.

[0027] In the diagram: 10-wing connector, 11-plug-in part, 12-outlet hole, 13-shaft hole, 14-support lug hole; 20-composite material wing surface; 30-antenna; 40-antenna cable channel; 50-wave-transparent reinforcement beam; 60-antenna upper and lower protective covers, 61-flanged edge; 70-leading edge; 80-tailing edge. Detailed Implementation

[0028] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to specific embodiments and accompanying drawings.

[0029] This invention utilizes the co-curing properties and designability of composite materials to pre-embed the antenna at the leading edge of the wing and lay the antenna cable channel inside the wing surface to the wing root at the trailing edge (leeward side). A wave-transmitting reinforcement beam is pre-embedded near the leading edge of the wing, which can improve the rigidity of the leading edge of the composite material wing. The wave-transmitting reinforcement beam, the upper and lower protective covers of the antenna, and the composite material of the wing body are all made of resin with the same curing conditions and are co-cured with the wing body.

[0030] Figure 1 This is a schematic diagram of a structurally and functionally integrated composite material wing surface according to an embodiment of the present invention. The structurally and functionally integrated composite material wing surface includes a wing joint 10, a composite material wing surface 20, an antenna 30, an antenna cable channel 40, a wave-transmitting reinforcement beam 50, and upper and lower antenna protective covers 60. Figure 1 The diagram also illustrates the leading edge 70 and trailing edge 80 of the integrated composite material airfoil.

[0031] The wing joint 10 is made of stainless steel, titanium alloy, or aluminum alloy, etc., according to the design load required by the wing surface and the comprehensive requirements of material properties, weight and simulation calculation results.

[0032] The composite material airfoil 20 is made of fiber materials such as carbon fiber, quartz fiber, or glass fiber, selected according to the design load required by the airfoil and the comprehensive requirements of material properties, weight, and simulation calculation results. The resin is selected as epoxy resin, cyanate ester resin, or polyether ether ketone resin.

[0033] The antenna 30 and antenna cable channel 40 are preferably made of aluminum alloy, wherein the antenna cable channel is a circular or square thin-walled hollow structure with a channel wall thickness of 1-2 mm.

[0034] The aforementioned wave-transparent reinforcing beam 50 is pre-embedded in the forward direction of the antenna, i.e., near the leading edge of the wing, to improve the stiffness and strength of the composite material wing surface at the antenna opening location. The fibers of this wave-transparent reinforcing beam are made of wave-transparent materials such as quartz fiber or glass fiber, and the resin is selected from epoxy resin, cyanate ester resin, or polyetheretherketone resin. The resin curing conditions are the same as those for the composite material wing surface 20. Preferably, the dielectric constant of the composite material used for the wave-transparent reinforcing beam pre-embedded in the forward direction of the antenna is not greater than 4.0.

[0035] The antenna upper and lower protective covers 60 are made of composite materials, in which the fibers are made of wave-transparent materials such as quartz fiber or glass fiber, and the resin is made of epoxy resin, cyanate ester resin or polyether ether ketone resin. The resin curing conditions are the same as those of the composite material wing 20. The dielectric constant of the composite material used for the antenna upper and lower protective covers is preferably not greater than 4.0.

[0036] The wing joint 10 and the composite material wing surface 20 are plug-in structures, such as... Figure 2As shown, the wing connector 10 is connected to the composite material wing surface 20 via the insertion part 11. The wing connector 10 is a metal connector and requires a hole in the trailing edge region, i.e., a cable exit hole 12, through which the antenna cable channel 40 is led out. The wing connector 10 also has a shaft hole 13 and a lug hole 14, where the shaft hole 13 is used to install the connector positioning shaft, and the lug hole 14 is used to install the lug positioning pin, assisting in the curing and molding of the wing surface.

[0037] The antenna upper and lower protective covers 60, such as Figure 3 As shown, a flange 61 with a certain area is required at the edges (left, right, or rear), which is co-cured with the wing surface 20 using an adhesive with the same curing conditions. The flange 61 can increase the bonding area between the protective cover and the composite material wing surface.

[0038] In one embodiment of the present invention, a method for forming a structurally and functionally integrated composite material airfoil is provided, the process of which is as follows: Figure 4 As shown, it includes the following steps:

[0039] Perform lower wing surface layup of composite material wing surfaces;

[0040] Place the wing connector and antenna cable channel in the reserved groove. The antenna cable channel runs from the front edge of the wing to the rear edge and exits through the cable outlet hole of the wing connector.

[0041] Perform upper surface layup of composite material wing surfaces;

[0042] Lay up the wave-transmitting enhancement beam and the upper and lower protective covers of the antenna;

[0043] The laid composite material wing surface, wave-transparent reinforcing beam, and upper and lower antenna protective covers are co-cured and molded, and then demolded to obtain a structurally and functionally integrated composite material wing surface.

[0044] In one embodiment of the present invention, before the lower wing surface layup of the composite material airfoil, pretreatment is performed, including sandblasting of the wing joint, fabric bonding, pre-adhesive absorption, and fabric cutting, to obtain a pre-cut non-woven fabric for subsequent layup operations. Quartz sand is preferably used for sandblasting, which increases the surface roughness of the joint insertion area and improves the bonding strength between the metal joint and the composite material. Then, resin prepreg is used for fabric bonding, and layup is performed according to the process document requirements to form a non-woven fabric layup assembly. The bonded non-woven fabric layup assembly is then pre-adhesive absorbed. Finally, a CNC fabric cutting machine is used to cut the pre-adhesive-absorbed non-woven fabric to obtain the pre-cut non-woven fabric.

[0045] In one embodiment of the present invention, the sandblasting preferably uses 20-40 mesh quartz sand and an air pressure of 0.4 MPa-0.7 MPa.

[0046] In one embodiment of the present invention, the layup method used when combining the fabric is [45 / -45 / 0 / 0], [0 / 0 / -45 / 45], [45 / 0 / 0 / -45], [0 / 0 / 0 / 45] [0 / 0 / -45 / 90] [90 / -45 / 0 / 0] [45 / 0 / 0 / 0] [-45 / 0 / 0 / 45], forming a non-woven fabric layup group.

[0047] In one embodiment of the present invention, the pre-adhesive absorption includes: during pre-adhesive absorption, placing one layer of PTFE cloth, one layer of adhesive-absorbing paper, one layer of PTFE cloth, and one layer of vacuum bag film on the upper and lower surfaces of the assembled non-woven fabric in sequence, respectively. The non-woven fabric needs to be sealed during adhesive absorption. The prepreg assembly after adhesive absorption also needs to be kept in a sealed bag. Then, the press is started to pressurize the fabric. After the pressurization is completed, the fabric is kept warm for a certain period of time. Then, the pre-pressed non-woven fabric layer assembly is removed from the press and allowed to cool naturally for later use.

[0048] In one embodiment of the present invention, the cut non-woven fabric is laid on the bottom mold according to the layup sequence of the process documents and tracking card. The layup is carried out according to the numbering sequence of the template. After the lower wing surface layup is completed, a layer of adhesive film (such as AD-36 adhesive film) is evenly pasted on the surface of the insertion part of the wing connector. The wing connector and the aluminum antenna cable channel are placed in the groove reserved in the template. The cable channel goes from the front edge of the wing to the rear edge, and then passes out from the cable outlet hole at the rear edge of the wing connector. Finally, the upper wing surface layup is completed according to the layup sequence.

[0049] In one embodiment of the present invention, the layup of the wave-transmitting reinforcement beam and the upper and lower protective covers of the antenna specifically includes: completing the layup of the wave-transmitting reinforcement beam according to the layup sequence of the process documents and the tracking card; placing the antenna into the reserved limit in the bottom mold; embedding the laid wave-transmitting reinforcement beam into the reserved limit in the antenna and the leading edge of the wing; and then laying up the upper and lower protective covers of the antenna at the leading edge. The protective cover layup method is to cover multiple layers of prepreg (e.g., QW100 / 9368 prepreg) as a whole. The layup sequence is carried out according to the cutting template number of the fabric, and the layup reference is the reserved flange position at the leading edge.

[0050] In one embodiment of the present invention, the co-curing and molding of the laid composite material wing surface, the wave-transmitting reinforcing beam, and the upper and lower antenna protective covers includes: placing the laid wing surface into a molding die, installing the wing joint positioning shaft and the lug positioning pin, lifting the upper die with a crane and placing it into the lower die cavity, and placing shims at the four corners of the mating surfaces of the upper and lower dies; then, checking that the hot press and temperature probe are working properly, lifting the die onto the press table with a crane, and contacting the upper die with the press's upper panel; inserting a thermocouple into the temperature measuring holes of the upper and lower dies respectively, setting the press temperature (e.g., to 90°C), heating the die, and removing the limiting shims after the die reaches the set temperature, applying pressure to make the upper and lower dies close tightly; setting the press temperature again (e.g., to 130°C), and holding the die at the set temperature for a certain period of time.

[0051] In one embodiment of the present invention, the demolding includes: removing the thermocouple from the mold, then using a crane to unload the mold from the press and place it on a mold cart for natural or fan cooling; then removing the fastening screws on the upper mold, removing each edge strip of the airfoil portion, then using a crane to remove the upper mold, tapping the lower connector positioning shaft from the front of the mold until the positioning shaft is removed from the bottom mold and the part, then pulling out the support lug positioning pin, and lightly tapping each part of the connector area to remove the part from the mold.

[0052] In one embodiment of the present invention, molding a structurally and functionally integrated wing surface product includes the following steps:

[0053] The first step is sandblasting the wing joints.

[0054] The wing joint uses a metal connector. The mating area of ​​the metal connector is sandblasted, and the non-sandblasted areas are protected to prevent quartz sand from splashing during sandblasting. Sandblasting uses 20-40 mesh quartz sand at an air pressure of 0.4MPa-0.7MPa. The sandblasting direction is kept as consistent as possible with the normal direction of the sandblasted surface and the sandblasting is even, avoiding prolonged lingering in one spot. The purpose of sandblasting is to increase the surface roughness of the joint mating area, improving the adhesion strength between the metal connector and the composite material.

[0055] The second step is to combine the fabric.

[0056] The fabric is laid up using GW700S / 9368 medium-temperature epoxy resin prepreg. According to the process documents, the layup method is [45 / -45 / 0 / 0], [0 / 0 / -45 / 45], [45 / 0 / 0 / -45], [0 / 0 / 0 / 45], [0 / 0 / -45 / 90], [90 / -45 / 0 / 0], [45 / 0 / 0 / 0], [-45 / 0 / 0 / 45], forming a non-woven fabric layup group.

[0057] The third step is pre-absorption of adhesive.

[0058] Pre-absorb the adhesive onto the assembled non-woven fabric layers. During pre-absorption, place one layer of PTFE fabric, one layer of adhesive-absorbing paper, one layer of PTFE fabric, and one layer of vacuum bag film on the top and bottom surfaces of the assembled non-woven fabric in that order. The non-woven fabric needs to be sealed during adhesive absorption by using double-sided tape to bond the top and bottom vacuum bag films together into a single sealed bag. The prepreg assembly after adhesive absorption must also be kept in the sealed bag and not opened until the fabric is cut.

[0059] Start the press, lift the upper template, place the prepreg on the steel pad, seal tightly, and press at a pressure of 1.0MPa to 1.5MPa. Start timing from the end of pressurization, and maintain the temperature for 1 to 2 minutes. After the maintenance time is up, remove the pre-pressed nonwoven fabric layer from the press and allow it to cool naturally before use.

[0060] The fourth step is to cut the fabric.

[0061] Based on the electronic file of the blanking template used by the wing surface cutting machine, the non-woven fabric after the third step of glue absorption was cut using a CNC cutting machine. At the same time, the QW100 / 9368 prepreg used for the antenna forward reinforcing beam and the upper and lower antenna protective covers was also cut. The 0° direction is the spanwise direction of the wing surface.

[0062] Step 5: Wing-body plying.

[0063] Install each side strip and wingtip block in the corresponding position on the bottom mold. First, install the positioning pins on each side strip, and then fix it with screws; tighten the top screws of the wingtip block.

[0064] Following the layup sequence in the process documents and tracking card, lay the non-woven fabric cut in step four on the bottom mold. Lay the fabric according to the numbering sequence of the template. After completing the lower wing surface layup, evenly apply a layer of AD-36 adhesive film to the surface of the wing connector insertion part. Place the wing connector and aluminum antenna cable channel in the groove reserved in the template. The cable channel goes from the front edge of the wing to the rear edge, and then passes out from the cable exit hole at the rear edge of the wing connector. Finally, complete the upper wing surface layup according to the layup sequence.

[0065] Step 6: Lay out the wave-transmitting enhancement beam and the upper and lower protective covers of the antenna.

[0066] Complete the layup of the wave-transmitting reinforcement beam according to the layup sequence of the process documents and tracking card. Place the antenna into the reserved limit in the bottom mold. Embed the laid wave-transmitting reinforcement beam into the reserved limit in the antenna and the leading edge of the wing. Then lay up the upper and lower protective covers of the antenna at the leading edge. The protective cover layup method is to cover the whole with 10 layers of QW100 / 9368 prepreg. The layup sequence is to lay up according to the cutting template number of the fourth step of fabric cutting. The layup reference is the reserved flange position at the leading edge.

[0067] Step 7: Curing and shaping of the wing surface.

[0068] The laid-out wing surface is placed into the molding die, the wing joint positioning shaft and the support lug positioning pin are installed, the upper die is lifted by a crane and placed into the lower die cavity, and 2mm shims are placed at the four corners of the mating surfaces of the upper and lower dies.

[0069] The hot press and temperature probe should be functioning correctly. Use a crane to lift the mold onto the press platform, ensuring the press's upper panel contacts the upper mold. Insert a thermocouple into the temperature measurement holes of both the upper and lower molds, with an insertion depth of at least 150mm. Set the press temperature to 90℃ and heat the mold. Once the mold reaches 90℃, remove the 2mm limiting gasket and apply pressure (3-5) MPa to ensure the upper and lower molds close tightly. Then set the press temperature to 130℃ and maintain this temperature for 120 minutes.

[0070] Step 8: Demolding.

[0071] Remove the thermocouple from the mold, then use a 5t crane (equipped with slings capable of supporting over 5t) to unload the mold from the press and place it on a mold cart. Allow it to cool naturally or with a fan to below 40℃.

[0072] Use a pneumatic hammer to remove the fastening screws on the upper mold. Use a hex wrench to remove each edge strip of the airfoil section. Then, use a 5-ton crane (equipped with a lifting sling with a capacity of 5 tons or more) to move the upper mold away. Use a copper rod to tap the lower joint positioning shaft from the front of the mold until the positioning shaft is removed from the bottom mold and the workpiece. Use a pin puller to pull out the support lug positioning pins. Gently tap various parts of the joint area with a rubber mallet. Meanwhile, have two additional people stand at the wingtip and center of the wing respectively to remove the workpiece from the mold.

[0073] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and are not intended to limit them. Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in each embodiment, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A structurally and functionally integrated composite material airfoil, characterized in that, The system includes a wing connector, a composite material wing surface, an antenna, an antenna cable channel, a wave-transmitting reinforcement beam, and upper and lower antenna protective covers. The wing connector is fixedly connected to the composite material wing surface. The antenna is embedded in the leading edge of the composite material wing surface. The antenna cable channel is located inside the composite material wing surface and extends to the wing root at the trailing edge. A cable outlet hole is provided on the wing connector, and the antenna cable channel is led out from the cable outlet hole. The wave-transmitting reinforcement beam is embedded in the forward direction of the antenna near the leading edge of the wing surface. The composite material wing surface, the wave-transmitting reinforcement beam, and the upper and lower antenna protective covers are made of the same resin and are co-cured under the same curing conditions.

2. The structurally and functionally integrated composite material wing surface according to claim 1, characterized in that, Based on the design load required for the wing surface, as well as the material properties, weight, and simulation calculation results, the fibers of the composite material wing surface are carbon fiber, quartz fiber, or glass fiber, and the resin is epoxy resin, cyanate ester resin, or polyether ether ketone resin.

3. The structurally and functionally integrated composite material wing surface according to claim 1, characterized in that, The wave-transparent reinforcing beam is made of composite material, wherein the fibers are wave-transparent material fibers, and the resin is epoxy resin, cyanate ester resin, or polyether ether ketone resin. The resin curing conditions are the same as those for the composite material airfoil. The dielectric constant of the composite material used in the wave-transparent reinforcing beam is not greater than 4.

0.

4. The structurally and functionally integrated composite material wing surface according to claim 1, characterized in that, The upper and lower protective covers of the antenna are made of composite materials, in which the fibers are made of wave-transparent materials and the resin is made of epoxy resin, cyanate ester resin or polyether ether ketone resin. The resin curing conditions are the same as those of the composite material wing surface. The dielectric constant of the composite material used in the upper and lower protective covers of the antenna is not greater than 4.

0.

5. The structurally and functionally integrated composite material wing surface according to claim 1, characterized in that, The upper and lower protective covers of the antenna have flanges at their edges, which are co-cured with the composite material wing surface using adhesives with the same curing conditions. The flanges increase the bonding area between the upper and lower protective covers of the antenna and the composite material wing surface.

6. The structurally and functionally integrated composite material wing surface according to claim 1, characterized in that, The antenna and the antenna cable channel are made of aluminum alloy. The antenna cable channel is a circular or square thin-walled hollow structure with a wall thickness of 1~2mm.

7. The structurally and functionally integrated composite material wing surface according to claim 1, characterized in that, The wing joint and the composite material wing surface are fixedly connected by a plug-in method; the wing joint is provided with a shaft hole and a lug hole, wherein the shaft hole is used to install the joint positioning shaft, and the lug hole is used to install the lug positioning pin, so as to assist in the curing and molding of the wing surface.

8. The structurally and functionally integrated composite material wing surface according to claim 1, characterized in that, The wing joint is made of a metal material, which is one of the following: stainless steel, titanium alloy, or aluminum alloy.

9. A method for molding the structurally and functionally integrated composite material airfoil as described in claim 1, characterized in that, Includes the following steps: Perform lower wing surface layup of composite material wing surfaces; Place the wing connector and antenna cable channel in the reserved groove. The antenna cable channel runs from the front edge of the wing to the rear edge and exits through the cable outlet hole of the wing connector. Perform upper surface layup of composite material wing surfaces; Lay up the wave-transmitting enhancement beam and the upper and lower protective covers of the antenna; The laid composite material wing surface, wave-transparent reinforcing beam, and upper and lower antenna protective covers are co-cured and molded, and then demolded to obtain a structurally and functionally integrated composite material wing surface.

10. The molding method according to claim 9, characterized in that, The wing joint is made of metal, and the insertion part is sandblasted to improve the connection strength between the metal joint and the composite material wing surface.

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