CN110193957A - A kind of small drone composite aileron moulding technique - Google Patents

Abstract

The invention relates to a small UAV composite material aileron forming process, which sequentially includes the manufacture of a special airbag forming mold, the manufacture of an airbag mandrel, the preparation of the overall product forming mold, the laying of prepregs to obtain layers, and then each The molds are combined to form a closed assembly, which can be solidified and demoulded; the invention solves the problem of the limitation of vacuum introduction of liquid resin for step-by-step curing and molding, improves product quality and uniformity of thickness, and improves the problems of low foam molding pressure and large structural weight , to provide a light-weight, high-performance, and good dimensional stability integral molding process for small UAV composite ailerons, and improve the structural performance and scope of application of small UAV composite ailerons.

Description

A small unmanned aerial vehicle composite material aileron forming process

technical field

The invention belongs to the technical field of UAV composite material molding technology, and relates to a small UAV composite material aileron molding technology method.

Background technique

The aileron of the aircraft refers to the movable wing surface installed outside the trailing edge of the wing tip. It is the main control surface of the aircraft. The traditional non-metal material UAV aileron mainly adopts wet hand lay-up FRP or liquid molding process, which is usually composed of skin, light wood ribs or stringers and beams; compared with the traditional aileron molding method, The composite material aileron formed by prepreg has the advantages of uniform glue content, light weight, excellent comprehensive mechanical properties and high environmental adaptability, and is more and more widely used in the body structure of high-performance UAVs.

The Chinese invention patent with the notification number CN 107160709 A announced "a method and rudder surface of composite material liquid forming ultra-light aircraft rudder surface", and proposed the method of using vacuum to introduce liquid resin and the method of step-by-step curing molding to realize the rudder surface. manufacture. This method requires step-by-step solidification and molding to assemble the beam structure, and then fills the gaps with fine sand to form the upper and lower skins of the rudder surface on the beam structure. The production cost of this method is high and the cycle is long, the weight of the realized product is large, the glue content and thickness are uneven, and the molding surface is filled with fine sand or air during the molding process, the process is complicated, and the product quality is not easy to control; it is suitable for The step-by-step curing molding of larger composite ailerons is not suitable for the overall molding and lightweight requirements of small UAV composite ailerons.

The Chinese invention patent with the notification number CN 106182801 A has announced "A Method for Forming the Aircraft Foam Sandwich Composite Steering Surface", which proposes to realize the integral molding of the rudder surface by utilizing the thermal expansion of the foam itself. The weight of the full-height foam core contained in this method is relatively large, and compared with silicone rubber thermal expansion molding and vacuum-assisted molding, the thermal expansion pressure of the foam itself is relatively small, so this method is suitable for the integral molding of non-load-bearing structures and low-performance ailerons , is not suitable for the integral molding of high-performance small UAV composite ailerons.

Contents of the invention

technical problem to be solved

In order to avoid the deficiencies of the prior art, the present invention proposes a small UAV composite material aileron molding process method and equipment, which are used to solve the limited problem of step-by-step solidification of vacuum-introduced liquid resin and improve product quality and thickness. The uniformity of the foam can be improved, and the problem of low foam molding pressure and large structural weight can be solved, and an overall molding process method with light weight, high performance, and good dimensional stability can be provided for the composite aileron of small UAVs, and the compounding of small UAVs can be improved. Structural performance and scope of application of material ailerons.

Technical solutions

A small UAV composite material vertical tail molding process, characterized in that the steps are as follows:

Step 1: Manufacture of dedicated airbag molding mold

Use CATIA software for three-dimensional modeling and optimal design of the special airbag forming mold, and process the optimized digital model; the special airbag forming mold is divided into two parts, the lower female mold and the upper female mold. The molds are connected by positioning pins and bolts, and a cavity is formed in the middle after combination, and the cavity is consistent with the inner cavity of the unmanned aerial vehicle composite aileron part to be processed; the left and right ends of the special airbag forming mold are provided with the second A left baffle plate and a first right baffle plate are positioned and connected to the end faces of the lower female mold and the upper female mold through bolts respectively, and are used to seal the above-mentioned cavity; the middle area of the right baffle plate is provided with a central hole, which is used to fix the airbag forming Mandrel filling and deflation joints;

Step 2: Manufacture of Airbag Mandrel

Step 2a: Unseal the lower female mold, the upper female mold, the first left baffle and the first right baffle respectively, apply sealing agent and water-soluble mold release agent to the inner surfaces of each of them, and let them dry for 15 minutes; The inner surface of the upper female mold is paved with silicon rubber sheets layer by layer to form a silicon rubber layer; then the lower female mold and the upper female mold containing the silicon rubber layer are molded together; on the first left baffle plate and the first right baffle plate The inner surface is also paved layer by layer with silicone rubber sheets to form a silicone rubber layer, in which the inflation and deflation joints are pre-embedded in the silicone rubber layer on the inner surface of the right baffle, and embedded in the center hole; The first left baffle plate and the first right baffle plate are respectively installed on both sides of the lower female mold and the upper female mold to form a closed assembly with a cavity; nitrogen is filled into the cavity through the charging and deflation joints, and the pressure is maintained at 0.4 MPa, to test the air tightness in the cavity, when the leakage pressure within 5 minutes does not exceed 0.017MPa, put the assembly into a vacuum curing furnace for vulcanization: first, heat up at a heating rate of 1-3°C/min, Until it reaches a constant temperature of 180°C, keep it warm for 2 hours; then cool down at a cooling rate of 3°C/min until it is out of the oven when it is below 55°C;

Step 2b: Disassemble the first left baffle and the first right baffle, and after separating the upper female mold, separate the airbag mandrel with the inflation and deflation joints from the inner surface of the lower female mold, and trim the remaining edge of the silicone rubber Obtain the airbag core mold; when the airbag core mold does not meet the requirements for use, it can be remanufactured with a special airbag forming mold;

Step 3: Prepare the overall product molding mold

CATIA software is used for 3D modeling and optimal design of the overall product forming mold, and the optimized digital model is used for mold processing; the overall product forming mold is divided into blocks after the front edge is designed along the process separation surface There are two parts, the female mold and the upper mold for forming; the lower mold for forming includes the entire trailing edge surface, which is used in conjunction with the upper mold for forming, and forms an integral combined mold through positioning pins and bolt connections for the overall molding of the product; here On the basis, the second left baffle and the second right baffle of the molding mold are also set at both ends of the overall molding mold of the product, which is convenient for positioning and fixing the inflation and deflation joints of the airbag mandrel, and is connected with the overall molding mold of the product to form an airtight combination body;

Step 4: Unseal the overall product molding mold, the second left baffle and the second right baffle respectively, apply sealing agent and water-soluble mold release agent to each inner surface in turn, and dry for 15 minutes; Two layers of 0°/90° carbon fiber fabric prepreg are laid on each layer, and the excess prepreg is reserved at the front edge on the non-forming working surface on the left side of the lower forming female mold, and separated by a non-porous isolation film to obtain Lower skin pre-laying layer; Lay 2 layers of 0°/90° carbon fiber fabric prepreg layer by layer on the surface of the forming upper female mold to obtain the upper skin pre-laying layer; fill the airbag mandrel with nitrogen to 0.4MPa, wait After constant pressure, a layer of 0°/90° carbon fiber fabric prepreg is laid on the rear edge to obtain the pre-lay of the beam; the prepreg is stored in a low-temperature refrigeration environment at -18°C and packaged before unsealing No condensed water is formed on the bag; the above-mentioned paving is carried out in a clean room, and the temperature in the clean room is kept at 22±4°C, and the relative humidity is not more than 65%;

Step 5: Install the second left baffle and the second right baffle at both ends of the lower female mold containing prepreg, and put the airbag mandrel containing prepreg into it, and fix the inflation and deflation joints At the center hole of the right baffle of the forming mold; place the balsa parts close to the pre-laying layer of the beam; roll the 50mm wide 0° unidirectional carbon tape prepreg into a cylindrical solid strip and fill it in the balsa The gap between the part and the lower female mold is formed into a strip-shaped pre-lay layer; the 2 layers of excess prepreg reserved on the left non-forming working surface are respectively turned over and pressed on the airbag layer by layer after removing the non-porous isolation film The upper surface of the mandrel; then combine the forming upper female mold containing prepreg and the lower forming female mold to form a closed assembly;

Step 6: Place the above airtight assembly in a vacuum curing furnace for curing: first heat up at a heating rate of 1-3°C/min until it reaches a constant temperature of 120°C, and keep it warm for 1 hour; then cool down at a rate of 3°C/min Cool down at a lower rate until it is out of the oven when it is below 55°C;

Step 7: Disassemble the second left baffle and the second right baffle at both ends of the assembly, separate the forming upper female mold upwards as a whole, sand the burrs at both ends of the product body, and release nitrogen to the airbag mandrel (6) After treatment, it is extracted from the solidified product body, and then the product body is separated from the lower mold for forming, the remaining edge of the product is processed, and the incision is sanded for smoothing to obtain a small UAV composite Material Aileron Products.

Beneficial effect

A kind of small UAV composite material aileron molding process method proposed by the present invention has the following beneficial effects:

(1) Solve the limited problem of step-by-step curing of liquid resin introduced by vacuum and improve the uniformity of product quality and thickness, avoiding environmental pollution and quality risks during the preparation and use of chemicals; effectively improving the pressure of foam molding The problem of small size and large structural weight improves the structural performance and scope of application of small UAV composite ailerons;

(2) The molding process and tooling are effectively simplified, the difficulty of the process is reduced, the production cycle is shortened, and the large loss of materials is avoided. It not only realizes the overall molding of the composite aileron, but also greatly exerts the advantages of the overall molding of the composite material , and the obtained product structure is light in weight and high in performance;

(3) It is suitable for the overall molding of a variety of small UAV composite ailerons, avoiding the difficulty of vacuum-assisted molding due to narrow cavity, or the difficulty of demolding various products;

(4) Through the airbag mandrel molding, the molding pressure can be effectively and evenly transmitted, which ensures the stable size of the integrally formed product, improves the quality of the inner and outer surfaces of the product, and avoids the thermal hysteresis effect inside the product, making the product performance reliable.

Description of drawings

Fig. 1 is the schematic diagram of the composite aileron structure of the embodiment of the present invention;

Fig. 2 is a schematic side view of the composite aileron structure in the embodiment

Fig. 3 is a schematic side view of the special airbag forming mold and the airbag mandrel in the embodiment;

Fig. 4 is a schematic diagram of the structure on the left side of the special airbag forming mold in the embodiment;

Fig. 5 is a schematic diagram of the structure on the right side of the special airbag forming mold in the embodiment;

Fig. 6 is the structural representation of airbag mandrel in the embodiment;

Fig. 7 is a schematic view of the lay-up structure in the embodiment;

Fig. 8 is a schematic side view of the equipment position in the embodiment;

Fig. 9 is a schematic diagram of forming the lower skin in the embodiment;

Fig. 10 is a schematic diagram of upper skin molding in the embodiment;

Fig. 11 is a schematic diagram of the state before curing in the embodiment.

Among them, 1-lower female mold, 2-upper female mold, 3-first left baffle, 4-first right baffle, 5-center hole, 6-airbag mandrel, 7-forming lower female mold, 8-forming Upper female mold, 9-lower skin pre-laying, 10-beam pre-laying, 11-balsa wood parts, 12-strip pre-laying, 13-upper skin pre-laying, 14-non-formed working surface , 15-forming mold left baffle plate, 16-forming mold right baffle plate.

Detailed ways

Now in conjunction with embodiment, accompanying drawing, the present invention will be further described:

The first step is the design of the special airbag forming mold.

Referring to Figure 1, the product of this embodiment is a typical small UAV composite material aileron structure special-shaped part, about 600mm long, the chord lengths at both ends are about 80mm and 75mm respectively, the radius of the front edge is about 6mm, and the thickness of the rear edge is about 1.5mm, the overall thickness of the product skin is about 0.4mm. The product has a complex structure and light weight; both ends are open, and one end is large and the other end is small; there are 5 recessed grooves on the front edge, which not only provides excellent rigidity for the front edge of the product, but also can be compared with other products. The connectors are pinned and fixed to realize the function of the aileron; the trailing edge is equipped with balsa wood embedded parts and strip-shaped pre-laid layers, which not only effectively improves the rigid support of the product after the overall molding and the co-glue between the skins, but also It effectively improves the conformability of the trailing edge of the product and avoids the generation of more defects at the rounded corners of the trailing edge.

Referring to Figure 2, according to the three-dimensional digital model of the product, CATIA software is used for tooling design, and mold processing is carried out according to the digital model to obtain a special airbag forming mold for the manufacture of airbag core molds.

Referring to Figure 3, the special airbag forming mold is mainly composed of a lower female mold 1 and an upper female mold 2, and the lower female mold 1 and the upper female mold 2 are connected by positioning pins and bolts to form an integral combined mold with a cavity, which is connected with the cavity to be The inner cavities of processed UAV composite aileron parts are consistent. Simultaneously, a sunken groove is arranged at the abutment of the front and rear edges, which is convenient for the abutment molding of the airbag mandrel 6, sealing of the cavity and trimming of the remaining edges.

Referring to Figures 4 and 5, on this basis, a first left baffle 3 and a first right baffle 4 are provided at both ends of the combined special airbag forming mold to facilitate airtight cavity. The baffle plate is a metal plate of the same material as the mold, and its surface contains bolt holes, which are respectively connected with the end faces of the lower female mold 1 and the upper female mold 2 through bolts, and the middle area of the right baffle plate 4 is provided with a central hole 5. It can be used to fix the inflation and deflation joints of the mandrel 6 of the airbag, and the joint adopts a quick-release connection method.

The special airbag forming mold is divided into simple and reasonable blocks, which can effectively avoid problems such as poor air tightness caused by too many block designs. The detachable baffles at both ends ensure good airtightness in the cavity and the reliability of the baffles. Detachability is also conducive to the positioning and demoulding of the airbag core mold; through the sinking design of the joint, it can effectively ensure the process convenience of silicone rubber sheet laying and the overall sealing of the airbag after vulcanization.

The second step is to manufacture the airbag core mold 6 .

Referring to Figure 6, unseal the lower female mold 1, the upper female mold 2, the left baffle 3, and the right baffle 4, apply a sealing agent and a water-soluble mold release agent on each forming working surface in sequence, and let it dry for 15 minutes. Lay silicone rubber sheets on each forming work surface to form a silicone rubber layer. When laying and laying, the airbag should have a certain rigidity and collapse rate when forming the product, which can not only play a good role in supporting and positioning the prepreg laid, but also ensure that the thickness of the airbag material can be adjusted during the vulcanization process. Good air tightness and mold release, the specific method is to lay a thicker silicone rubber layer on each corner and left and right baffles, which can effectively form a certain rigidity and form an effective supporting surface; on the right baffle 4. Pre-embed the joint into the silicone rubber layer to ensure the sealing performance between the joint and the silicone rubber after vulcanization. After the silicone rubber sheet is laid, the shape of the silicone rubber layer is trimmed, and a 5mm silicone rubber lap strip is reserved for the joint to improve the sealing and quality reliability of the airbag mandrel at the joint.

On this basis, the lower female mold 1 and the upper female mold 2 containing the silicone rubber layer are mold-closed, and then the left baffle 3 and the right baffle 4 are respectively installed at both ends of the combined mould, finally forming a closed assembly.

Inflate nitrogen gas into the cavity of the airtight assembly through the inflation and deflation joints until a pressure of 0.4MPa is formed in the cavity; perform an air tightness test on the cavity, and when the pressure leaked within 5 minutes does not exceed 0.017MPa, the combination Put the body into a vacuum curing furnace for vulcanization. The main content is to heat up at a heating rate of 1-3°C/min until it reaches a constant temperature of 180°C and keep it for 2 hours; then cool down at a cooling rate of 3°C/min. , until it is below 55°C, out of the oven, and demolded. Finally, use a paper cutting blade to trim the flaky remaining edge of the airbag mandrel blank to obtain the airbag mandrel 6 .

The third step is the overall molding mold design of the product.

Referring to Figure 7, according to the 3D digital model of the product, the CATIA software is used to carry out the 3D modeling and optimization design of the overall product forming mold, and the optimized digital model is processed to obtain the overall product forming mold, which is used for the overall aileron of the composite material forming.

Referring to Fig. 8, the overall molding mold of the product is divided into two parts, the lower molding die 7 and the upper molding die 8, after the front edge is divided into blocks along the process separation surface; the lower female die 7 includes the entire trailing edge The surface is used in conjunction with the upper female mold 8 to form an integral combined mold through positioning pins and bolt connections, which is used for the overall molding of the product. On this basis, the left baffle plate 15 and the right baffle plate 16 of the molding mold are also arranged at both ends of the overall molding mold of the product to facilitate the positioning and fixing of the inflation and deflation joints of the airbag mandrel 6, and are connected with the overall molding mold of the product through threads. Join to form a closed assembly.

Through the combined use of the overall product molding mold and the airbag core mold 6, it can fully and effectively solve the overall quality state of the product before and after curing, the uniformity of the molding pressure transmission, and improve the releaseability of the product and the reliability of internal and external quality. sex.

The fourth step is the preparation process.

Unpack the molding lower female mold 7, the upper molding female mold 8, the left baffle 15 of the molding mold, and the right baffle 16 of the molding mold, apply sealing agent and water-soluble mold release agent on each molding working surface in turn, and dry for 15 minutes.

Referring to Fig. 7, prepreg and balsa wood parts 11 for integral molding are prepared; the prepreg used in this embodiment is MTM28/CF0300-42% RW carbon fiber fabric prepreg with single layer thickness δ0.2mm and single layer thickness δ0.125mm MTM28-1/T700SC-125-33%RW unidirectional carbon tape prepreg.

The fifth step is the cutting of prepreg.

Through the three-dimensional digital model of the product, the sample opening and process optimization of the prepreg are carried out. AutoCAD is used to optimize the layout design of the prepreg to improve material utilization and reduce costs; The prepregs are marked and placed in layers. When prepreg is cut, the direction deviation of the piece is allowed to be ±1°, and the size deviation is ±1mm.

The sixth step is prepreg layup.

Referring to Figures 7 and 9, two layers (0°/90°) of carbon cloth fabric prepreg are laid layer by layer on the lower forming female mold 7, and the excess prepreg is reserved on the left side of the lower forming female mold 7 at the front edge. On the non-forming working surface 14 of the side, and use non-porous isolation film to separate, obtain the lower skin pre-lay layer 9.

Referring to FIG. 10 , two layers (0°/90°) of carbon cloth fabric prepreg are laid layer by layer on the surface of the forming upper female mold 8 , and the upper skin pre-lay layer 13 is obtained after a step transition is formed between the layers.

Fill the airbag mandrel 6 with nitrogen to 0.4 MPa, and after it is under constant pressure, lay a layer (0°/90°) of carbon fiber fabric prepreg on the trailing edge to obtain the pre-laminated layer 10 of the beam.

Referring to Fig. 11, the left baffle plate 15 and the right baffle plate 16 of the molding mold are installed at both ends of the molding lower mold 7 containing the prepreg, and the airbag mandrel 6 containing the prepreg is inserted thereinto, and filled, The air release joint is fixed at the center hole of the right baffle plate 16 of the forming mold; the balsa wood part 11 is placed close to the pre-lay layer 10 of the beam; the 50mm wide 0° unidirectional carbon tape prepreg is rolled into a cylindrical solid The strip fills the gap between the balsa wood part 11 and the lower female mold 7 to form a strip pre-lay 12 . After removing the non-porous isolation film, the 2 layers of excess prepreg reserved at 14 on the left non-forming working surface were turned over and pressed layer by layer on the upper surface of the airbag mandrel 6 to form a stepped transition; The molding upper female mold 8 and the lower molding female mold 7 are combined to form a closed assembly.

The requirements of the whole layup process are as follows: In order to eliminate the air wrapped between the layups as much as possible, the prepreg layup should be vacuum pre-compacted and help the parts to form. Vacuum pre-compaction should be carried out for the first layer of prepreg laying, before and after laying the sandwich material, and for each 1 to 3 layers of prepreg laying. The method of vacuum pre-compaction is on the pre-laying layer The commonly used porous isolation film, air felt, and temporary vacuum bag are laid in sequence, and the vacuum sealing system is formed by the adhesion of the sealing tape at the edge of the non-working surface of the mold, and then the vacuum degree in the system is kept at least 0.08MPa by continuous vacuuming. 10 minutes; After each vacuum pre-compacting, the temporary vacuum bag with the sealing tape on it is uncovered and put together, so that the entire working surface of the mold is fully exposed, and then the porous isolation film and the air felt Remove and keep it clean for next time use. The carbon fiber fabric prepreg should be lapped when laying. The lap width is about 25mm, and the lap joints between adjacent layers should be staggered by about 25mm.

The seventh step is curing.

Place the above airtight assembly in a vacuum curing furnace for curing: first heat up at a heating rate of 1-3°C/min until it reaches a constant temperature of 120°C, and keep it warm for 1 hour; then cool at a cooling rate of 3°C/min Cool down until it is below 55°C.

The eighth step, demoulding and shape processing.

Disassemble the metal baffles at both ends of the assembly, separate the forming upper female mold 8 upwards as a whole, sand the burrs at both ends of the product body, and release nitrogen gas from the airbag mandrel 6 and remove it from the solidified product body. Pull out, and then the product blank is separated from the forming lower female mold 7, the remaining edge of the product is processed, and the sanding cut is carried out for finishing treatment.

So far, the overall molding of the small UAV composite aileron product has been completed.

Claims (1)

1. A small unmanned aerial vehicle composite material aileron molding process, is characterized in that the steps are as follows: Step 1: Manufacture of dedicated airbag molding mold Use CATIA software to carry out three-dimensional modeling and optimal design of the special airbag forming mold, and carry out mold processing on the optimized digital model; the special airbag forming mold is divided into two parts, a lower female mold (1) and an upper female mold (2), The lower female mold (1) and the upper female mold (2) are connected by positioning pins and bolts, and a cavity is formed in the middle after the combination, and the cavity is consistent with the inner cavity of the unmanned aerial vehicle composite aileron part to be processed; The left and right ends of the special airbag forming mold are provided with a first left baffle (3) and a first right baffle (4), which are respectively positioned and connected to the end surfaces of the lower female mold (1) and the upper female mold (2) by bolts , for sealing the above-mentioned cavity; the middle area of the right baffle (4) is provided with a central hole (5), which is used to fix the inflation and deflation joints of the airbag forming mandrel (6); Step 2: Manufacture of airbag mandrel (6) Step 2a: Unseal the lower female mold (1), upper female mold (2), first left baffle (3) and first right baffle (4) respectively, and apply sealing agent and water-soluble release agent and dry for 15 minutes; pave and paste silicone rubber sheets layer by layer on the inner surfaces of the lower female mold (1) and the upper female mold (2) to form a silicone rubber layer; then place the lower female mold (1) containing the silicone rubber layer ) and the upper female mold (2) are mold-closed; on the inner surfaces of the first left baffle (3) and the first right baffle (4), the same layer-by-layer silicon rubber sheet is laid to form a silicone rubber layer, wherein the right baffle (4) Embed the inflation and deflation joints into the silicone rubber layer on the inner surface, and embed them in the center hole (5); then place the first left baffle (3) and the first right baffle on the upper The plates (4) are respectively installed on both sides of the lower female mold (1) and the upper female mold (2) to form a closed assembly with a cavity; nitrogen is filled into the cavity through the charging and deflation joints, and the pressure is maintained at 0.4MPa. Carry out an air tightness test in the cavity, and when the leakage pressure within 5 minutes does not exceed 0.017MPa, put the assembly into a vacuum curing furnace for vulcanization: first, heat up at a heating rate of 1-3°C/min until it reaches Keep the temperature at 180°C for 2 hours; then cool down at a cooling rate of 3°C/min until it comes out of the oven when it is below 55°C; Step 2b: Disassemble the first left baffle (3) and the first right baffle (4), separate the upper female mold (2), and remove the airbag mandrel (6) with the inflation and deflation joints from the lower female mold (1) The inner surface is separated, and the airbag core mold (6) is obtained after trimming the remaining edges of the silicone rubber; when the airbag core mold (6) does not meet the requirements for use, it can be repeatedly manufactured by using a special airbag forming mold; Step 3: Prepare the overall product molding mold CATIA software is used for 3D modeling and optimal design of the overall product forming mold, and the optimized digital model is used for mold processing; the overall product forming mold is divided into blocks after the front edge is designed along the process separation surface The female mold (7) and the forming upper female mold (8) are two parts; the forming lower female mold (7) includes the entire trailing edge surface, used in conjunction with the forming upper female mold (8), and is connected as a whole by positioning pins and bolts The combined mold is used for the overall molding of the product; on this basis, the second left baffle (15) and the second right baffle (16) of the molding mold are also arranged at both ends of the overall molding mold of the product, so as to facilitate the positioning and fixing of the airbag mandrel (6) The inflation and deflation joints of the product are connected with the overall molding mold of the product to form a closed assembly by threading; Step 4: Unseal the overall product molding mold, the second left baffle and the second right baffle respectively, apply a sealing agent and a water-soluble mold release agent to each inner surface in turn, and dry for 15 minutes; the female mold under the forming (7 ) on top of 2 layers of 0°/90° carbon fiber fabric prepreg layer by layer, reserve excess prepreg at the front edge on the non-forming working surface (14) on the left side of the lower forming female mold (7), and Use a non-porous isolation film to separate to obtain the lower skin pre-lay layer (9); pave and paste 2 layers of 0°/90° carbon fiber fabric prepreg on the surface of the forming upper female mold (8) layer by layer to obtain the upper skin pre-preg. Layup (13); fill the airbag mandrel (6) with nitrogen to 0.4MPa, and lay a layer of 0°/90° carbon fiber fabric prepreg at the trailing edge after the constant pressure to obtain the pre-lay of the beam (10); the prepreg is stored in a low-temperature refrigeration environment at -18°C, and no condensation is formed on the packaging bag before unsealing; the laying is carried out in a clean room, and the temperature in the clean room is kept at 22±4°C , the relative humidity is not more than 65%; Step 5: Install the second left baffle (15) and the second right baffle (16) at both ends of the molding lower die (7) containing the prepreg, and simultaneously place the airbag mandrel (6) containing the prepreg ) into it, and the inflation and deflation joints are fixed at the center hole of the right baffle of the forming mold; the balsa parts (11) are placed close to the pre-laying layer (10) of the beam; the 50mm wide 0° unidirectional The carbon tape prepreg roll is made into a cylindrical solid strip and filled in the gap between the balsa wood part (11) and the lower mold (7) to form a strip pre-layer (12); The 2 layers of excess prepreg reserved at the forming working surface (14) are respectively turned over and pressed layer by layer on the upper surface of the airbag mandrel (6) after removing the non-porous isolation film; 8) combined with the forming lower female mold (7) to form a closed assembly; Step 6: Place the above airtight assembly in a vacuum curing furnace for curing: first heat up at a heating rate of 1-3°C/min until it reaches a constant temperature of 120°C, and keep it warm for 1 hour; then cool down at a rate of 3°C/min Cool down at a lower rate until it is out of the oven when it is below 55°C; Step 7: Disassemble the second left baffle plate (15) and the second right baffle plate (16) at both ends of the assembly, separate the forming upper female mold (8) upwards as a whole, sand clean the burrs at both ends of the product body, and After the airbag mandrel (6) is treated with nitrogen release, it is extracted from the solidified product body, and then the product body is separated from the lower mold (7), and the remaining edge of the product is processed and sanded The incision is smoothed to obtain a small UAV composite material aileron product.