A wing forming tooling and method for a box section structure

Abstract

A forming tooling and method for a wing of a box-section structure, belonging to the field of aviation composite material forming. A frame is fixedly connected to a template to form a tooling base. Two side molds are placed on the left and right sides of the cavity of the template. The two side molds are positioned and detachably fixedly connected to the template. A cover plate is positioned and detachably fixedly connected to the top surfaces of the two side molds. A plurality of stoppers are placed on the left and right sides and the front and rear ends of the two side molds on the template. The plurality of stoppers abut against the two side molds and are positioned and detachably fixedly connected to the template. Two drill jigs are positioned and detachably fixedly connected to the template. The two drill jigs are located at the front and rear ends of the cover plate. A rib locator assembly straddles the outside of the two side molds and is positioned and detachably fixedly connected to the template. The method steps are: assembling the tooling base; pasting the skin and the wing beam; assembling the stoppers and the two side molds; positioning the wing ribs; encapsulating all the components above the template in a vacuum bag and evacuating, heat-insulating, pressure-holding, and curing. The present invention is used for forming the wing of a box-section structure.

Description

Technical Field

[0001] The present invention belongs to the field of aviation composite material forming, and particularly relates to a forming tooling and method for a wing with a box-section structure. Background Art

[0002] Composite materials are made of two or more materials with different properties through physical or chemical methods, and form materials with new properties macroscopically or microscopically. The development of modern high-tech cannot do without composite materials, and composite materials are more and more widely used in the fields of aerospace. The usage amount of advanced composite materials has become an important indicator of the advancement of aircraft.

[0003] Since the composite material wing with a box-section structure is large and has a complex shape, when using the existing split forming process for forming, each composite material part needs to be manufactured separately and then riveted. The number of parts used is large, increasing the weight of the fuselage. When assembling the structure, assembly tooling needs to be equipped. The amount of tooling used is large, the weight is heavy, the cost is high, and the assembly time is long. Summary of the Invention

[0004] The purpose of the present invention is to solve the problems in the background art and provide a forming tooling and method for a wing with a box-section structure.

[0005] By adopting the integral curing forming process, the present invention can accelerate the application of the forming technology for the wing with a box-section structure, further optimize the aviation composite material forming process, solve the problems such as the cumbersome assembly process of the wing with a box-section structure, reduce the number of riveting times of the wing, greatly improve the processing and manufacturing efficiency, greatly improve the time-consuming and laborious processing, significantly shorten the manufacturing cycle, greatly reduce the cost, be more lightweight, and can meet the customer requirements.

[0006] To achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0007] A forming tooling for a wing with a box-section structure includes a mold plate, a frame, a cover plate, two side molds, two drill jigs, a plurality of stoppers and a rib locator assembly;

[0008] The top of the frame is fixedly connected to the mold plate to form a tooling base; the two side molds are placed on the mold plate and located on the left and right sides of the mold cavity of the mold plate. The mold surfaces of the two side molds are arranged oppositely. The two side molds are positioned and detachably fixedly connected to the mold plate. A cover plate is placed on the top surfaces of the two side molds. The cover plate is positioned and detachably fixedly connected to the top surfaces of the two side molds; a plurality of stoppers are placed on the mold plate on the left and right sides and the front and rear ends of the two side molds. The plurality of stoppers abut against the two side molds. The plurality of stoppers are positioned and detachably fixedly connected to the mold plate; the two drill jigs are placed on the mold plate and located at the front and rear ends of the cover plate. The drill jigs are positioned and detachably fixedly connected to the mold plate; the rib locator assembly straddles the outside of the two side molds. The rib locator assembly is positioned and detachably fixedly connected to the mold plate.

[0009] Furthermore, four corner wheel assemblies are symmetrically and fixedly arranged on both the left and right sides of the frame.

[0010] Furthermore, four lifting rings are symmetrically and fixedly arranged on both the left and right sides of the frame.

[0011] Furthermore, a plurality of circular positioning balls are arranged on the top surface of the side mold, and a plurality of circular grooves are arranged at positions corresponding to the plurality of circular positioning balls on the bottom surface of the cover plate. The plurality of circular positioning balls are in positioning connection with the plurality of circular grooves.

[0012] Furthermore, the rib locator assembly includes a plurality of rib locators. Each rib locator includes a U-shaped frame, a connecting plate, a positioning plate and two bottom plates. The U-shaped frame is formed by square steel pipes. The upper and lower end faces of the cross beam of the U-shaped frame are both flat. A connecting plate is fixedly arranged in the middle of one side surface of the cross beam of the U-shaped frame. The positioning plate is detachably and fixedly connected to the outer plate surface of the connecting plate. The outer plate surface of the positioning plate is an inclined surface. One bottom plate is fixedly arranged at each end of the U-shaped frame.

[0013] Furthermore, an inclined surface is arranged on one side of the top surface of the stop block. Two bushings are fixedly arranged in the stop block. A positioning pin is fixedly arranged in each bushing. The stop block and the template are positioned by two positioning pins and are detachably and fixedly connected to the template by two screws.

[0014] A method for forming a wing of a box-section structure, characterized in that the method comprises the following steps:

[0015] Step 1: Assemble the tooling base; first move the frame to the working position, and then fixedly connect the template and the upper end of the frame to form the tooling base;

[0016] Step 2: Paste one side skin of the wing on the template; specifically: lay the composite material on the surface of the cavity of the template. For every two layers laid, paste a vacuum bag to evacuate the air. After pre-compaction treatment, remove the vacuum bag until the required thickness of the skin is laid;

[0017] Paste part of the wing beam on the two side molds; specifically: first lay the composite material on the surfaces of the two side molds. For every two layers laid, paste a vacuum bag to evacuate the air. After pre-compaction treatment, remove the vacuum bag until the required thickness of part of the wing beam is laid;

[0018] Step 3: Place a plurality of stop blocks on the template and on the outer side of the periphery of the cavity of the template. The plurality of stop blocks are positioned and detachably and fixedly connected to the template. Finally, place the two side molds on the left and right sides of the cavity of the template. The surfaces of the two side molds are arranged oppositely. The two side molds are positioned and detachably and fixedly connected to the template. The plurality of stop blocks abut against the two side molds. The space formed between the cavity of the template and the two side molds constitutes the tooling cavity;

[0019] Step 4: Place the preformed other part of the wing beam in the tooling cavity. The other part of the wing beam and the part of the wing beam on the two side molds are positioned to form a wing beam assembly. Lay composite materials on the upper surface of the wing beam assembly to the required thickness and compact them to form an integral wing beam. Then place the preformed wing rib in the middle of the integral wing beam. After placement, place the rib locator assembly across the outside of the two side molds. The rib locator assembly is positioned and detachably fixed to the formwork. Use the rib locator assembly to inspect the wing rib, and finally adjust and position the wing rib to the appropriate position.

[0020] Step 5: After the wing rib is positioned, disassemble the rib locator assembly. Then position and detachably fix the cover plate to the top surfaces of the two side molds. Enclose all the components above the formwork in a cured vacuum bag, evacuate the air, and send the tooling into the autoclave for heat preservation, pressure holding, and curing to form a wing blank with a box section structure.

[0021] Step 6: After curing is completed, transfer the tooling to the indoor area and ventilate and cool it to room temperature. Then, remove the vacuum bag, place the two drill jigs on the formwork and at the front and rear ends of the cover plate. The drill jigs are positioned and detachably fixed to the formwork. Use the drill jigs to drill positioning holes at the specified positions on the wing blank with a box section structure. After the positioning holes are drilled, disassemble the drill jigs.

[0022] Step 7: Demold. First, disassemble the cover plate, multiple stop blocks, and the two side molds in sequence, and then take out the wing blank with a box section structure.

[0023] Step 8: After demolding is completed, trim and polish the boundary of the wing blank with a box section structure to form a wing with a box section structure.

[0024] Step 9: Perform moisture-proof and anti-corrosion treatments on the surface of the wing with a box section structure, and pass the inspection.

[0025] Furthermore, in Step 5, during the evacuation process, a complete vacuum leakage inspection shall be carried out, and the minimum complete vacuum shall be 0.08 MPa.

[0026] Furthermore, in Step 5, the curing temperature is 120 °C, the curing pressure is 0.6 Mpa, heat preservation and pressure holding are carried out for 120 - 180 minutes, and the negative pressure reading of the detected vacuum degree does not decrease by more than 0.017 MPa.

[0027] Compared with the prior art, the beneficial effects of the present invention are:

[0028] 1. This tooling uses stop blocks to position the side molds (metal parts) to achieve integrated molding, reduce parts, and correspondingly reduce the number of rivets and the use of tooling, saving costs and reducing assembly time.

[0029] 2. This tooling uses a rib locator assembly to position the wing rib (composite part) to achieve integrated molding, reduce weight, and improve the overall performance.

[0030] 3. This tooling adopts a segmented structure, which is convenient for the demolding of the wing with a complex shape.

[0031] 4. This forming method is easy to operate. Using this forming method, the wing with a box-section structure can be formed in one step, avoiding multiple assemblies of beams and ribs. The process is simple and can ensure the forming quality and accuracy. Description of the Drawings

[0032] Figure 1 is an isometric view of a forming tooling for a wing with a box-section structure according to the present invention;

[0033] Figure 2 is a front view of a forming tooling for a wing with a box-section structure according to the present invention;

[0034] Figure 3 is a top view of a forming tooling for a wing with a box-section structure according to the present invention;

[0035] Figure 4 is a left view of a forming tooling for a wing with a box-section structure according to the present invention;

[0036] Figure 5 is a top view of the template;

[0037] Figure 6 is a top view of the frame;

[0038] Figure 7 is a top view of the cover plate;

[0039] Figure 8 is a top view of the combination of two side molds;

[0040] Figure 9 is a front view of the drill jig;

[0041] Figure 10 is Figure 9 left view;

[0042] Figure 11 is Figure 9 top view;

[0043] Figure 12 is a front view of the stop block;

[0044] Figure 13 is Figure 12 left view;

[0045] Figure 14 is Figure 12 top view;

[0046] Figure 15 is a front view of the angle wheel assembly;

[0047] Figure 16 is Figure 15Left view;

[0048] Figure 17 is the top view of the rib locator assembly;

[0049] Figure 18 is Figure 17 Left view;

[0050] Figure 19 is the front view of the lifting ring;

[0051] Figure 20 is Figure 19 Left view.

[0052] The names and reference numerals of the components involved in the above drawings are as follows:

[0053] Mold plate 1, frame 2, cover plate 3, side mold 4, drill jig 5, stop block 6, inclined surface 6-1, corner wheel assembly 7, rib locator assembly 8, U-shaped frame 8-1, connecting plate 8-2, positioning plate 8-3, bottom plate 8-4, inclined surface 8-5, lifting ring 9. Specific embodiments

[0054] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the scope of protection of the present invention.

[0055] Specific embodiment 1: As Figures 1 - 20 shown; this embodiment discloses a wing forming tooling for a box-section structure, including a mold plate 1, a frame 2, a cover plate 3, two side molds 4, two drill jigs 5 (which are prior art), a plurality of stop blocks 6 and a rib locator assembly 8;

[0056] The top of the frame 2 (which is the base of the entire forming tooling) is fixedly connected to the mold plate 1 (by welding) to form the tooling base (the welding shall use argon arc welding to ensure airtightness, clean the oxides, welding spatter, cutting slag, etc. of the welding joint, ensure that the weld is smooth and all show metallic luster; the surface of the mold plate 1 is machined according to the bottom surface of the box-section structure wing, and notch grooves are provided at the three corners of the upper end surface of the mold plate 1. The bottom surface of the notch groove is used as the reference surface, and the smooth reference surface is used as the clamping reference for tooling alignment and machining to ensure that the flatness does not exceed 0.2 mm. The rough and finish machining are carried out according to the aircraft digital model surface according to the numerical control machining program and are processed in place. After machining, the burrs and flash are simply removed to avoid scratches during the transportation process);

[0057] Two side molds 4 are placed on the mold plate 1 and located on the left and right sides of the mold cavity of the mold plate. The mold surfaces of the two side molds 4 are arranged oppositely. The two side molds 4 are positioned with the mold plate 1 (through positioning pins) and detachably fixedly connected (through screws) (the two side molds 4 are used to form the left and right contours of the wing of the box segment structure. The mold surfaces of the two side molds 4 for forming the left and right contours of the wing are rough and finish machined according to the numerical control machining program). A cover plate 3 is placed on the top surfaces of the two side molds 4. The cover plate 3 is positioned with the top surfaces of the two side molds 4 (through positioning pins) and detachably fixedly connected (through screws) (the mold surface of the cover plate 3 for forming the upper contour of the wing is rough and finish machined according to the numerical control machining program);

[0058] A plurality of stoppers 6 are respectively placed on the left and right sides and the front and rear ends of the two side molds 4 on the mold plate 1. The plurality of stoppers 6 abut against the two side molds 4. The plurality of stoppers 6 are positioned with the mold plate 1 (through positioning pins) and detachably fixedly connected (through screws) (preferably, 3-4 stoppers 6 are arranged on each of the left and right sides of the two side molds 4, and 1 stopper 6 is arranged at each end of each side mold 4. The function of the stopper 6 is: because the tooling is heavy and not easy to move, it is difficult to position with the mold plate 1 through the positioning pin. By setting the stopper 6, an initial positioning position is given to the side mold 4 to facilitate the positioning of the side mold 4);

[0059] Two drill jigs 5 are placed on the mold plate 1 and located at the front and rear ends of the cover plate 3. The drill jigs 5 are positioned with the mold plate 1 (through positioning pins) and detachably fixedly connected (through screws) (the function is to drill positioning holes on the lugs reserved on the wing blank after forming. Through the positioning holes on the wing, the wing can be positioned repeatedly and with high precision by using pins);

[0060] The rib locator assembly 8 straddles the outside of the two side molds 4. The rib locator assembly 8 is positioned with the mold plate 1 (through positioning pins) and detachably fixedly connected (through screws).

[0061] Furthermore, four caster assemblies 7 are symmetrically fixed on the left and right sides of the frame 2.

[0062] Furthermore, four lifting rings 9 are symmetrically fixed on the left and right sides of the frame 2 (after calculating the load-bearing capacity, the tooling is lifted through the four lifting rings 9 for tooling transfer and transportation).

[0063] Furthermore, a plurality of circular positioning balls are provided on the top surface of the side mold 4. A plurality of circular grooves are provided at the corresponding positions on the bottom surface of the cover plate 3 relative to the plurality of circular positioning balls. The plurality of circular positioning balls are positioned and connected with the plurality of circular grooves (to realize the initial positioning of the cover plate 3 and the side mold 4).

[0064] Further, the rib locator assembly 8 includes a plurality of rib locators, each rib locator including a U-shaped frame 8-1, a connecting plate 8-2, a positioning plate 8-3 and two bottom plates 8-4; the U-shaped frame 8-1 is formed by square steel pipes, the upper and lower end faces of the cross beam of the U-shaped frame 8-1 are both flat surfaces, a connecting plate 8-2 is fixed in the middle of one side surface of the cross beam of the U-shaped frame 8-1, the positioning plate 8-3 is detachably and fixedly connected to the outer plate surface of the connecting plate 8-2 (by two connecting screws), the outer plate surface of the positioning plate 8-3 is an inclined surface 8-5 (the main function of the inclined surface 8-5 is to position the wing rib), and one bottom plate 8-4 is fixed at each end of the U-shaped frame 8-1 (for connecting with the template 1).

[0065] Further, one side of the top surface of the stop block 6 is provided with an inclined surface 6-1 (facilitating the placement of the wing rib in the tooling cavity), two bushings are fixed in the stop block 6, a positioning pin is fixed in each bushing, and the stop block 6 and the template 1 are positioned by two positioning pins and are detachably and fixedly connected to the template 1 by two screws.

[0066] Specific Embodiment Two: As Figures 1 - 20 shown, this embodiment discloses a method for forming a box-section structure wing by using the tooling described in any one of the claims in Specific Embodiments One to Six, and the method includes the following steps:

[0067] Step One: Assemble the tooling base; first move the frame 2 (by the caster assembly 7 or the lifting ring 9) to the working position, and then fixedly connect the template 1 and the upper end of the frame 2 (by welding) to form the tooling base;

[0068] Step Two: Hand lay the skin on one side of the wing on the template 1; specifically: lay the composite material on the surface of the cavity of the template, and for every two layers laid, hand lay a vacuum bag for vacuuming, and after pre-compaction treatment (which is an existing process), remove the vacuum bag until the required thickness of the skin is laid;

[0069] Hand lay part of the wing beam on the two side molds 4; specifically: first lay the composite material on the surfaces of the two side molds 4, and for every two layers laid, hand lay a vacuum bag for vacuuming, and after pre-compaction treatment (which is an existing process), remove the vacuum bag until the required thickness of part of the wing beam is laid;

[0070] Step 3: Place multiple stoppers 6 on the mold plate 1 and outside the periphery of the mold cavity of the mold plate. The multiple stoppers 6 are positioned with the mold plate 1 (through positioning pins) and detachably fixedly connected (through screws). Finally, place two side molds 4 on the left and right sides of the mold cavity of the mold plate. The mold surfaces of the two side molds 4 are arranged oppositely. The two side molds 4 are positioned with the mold plate 1 (through positioning pins) and detachably fixedly connected (through screws). The multiple stoppers 6 abut against the two side molds 4 (the two side molds 4 are limited by the multiple stoppers 6), and the space enclosed by the mold cavity of the mold plate and the two side molds 4 forms a tooling cavity;

[0071] Step 4: Place the preformed other part of the wing beam in the tooling cavity. The other part of the wing beam and the part of the wing beam on the two side molds 4 are positioned (through positioning pins or positioning surfaces) to form a wing beam combination. Lay composite materials on the upper surface of the wing beam combination to the required thickness and compact them to make an integral wing beam. Then place the preformed wing rib in the middle of the integral wing beam. After placement, place the rib locator assembly 8 across the outside of the two side molds 4. The rib locator assembly 8 is positioned with the mold plate 1 (through positioning pins) and detachably fixedly connected (through screws). Use the rib locator assembly 8 to check the wing rib, and finally adjust and position the wing rib to a suitable position (use the inclined surface 8-5 of the positioning plate 8-3 to check whether the placement position of the wing rib is appropriate. If the inclined surface 8-5 abuts against the wing rib, the placement position is appropriate; otherwise, adjust the position of the wing rib until it is adjusted to a suitable position to avoid misplacement);

[0072] Step 5: After the wing rib is positioned, disassemble the rib locator assembly 8. Then position the cover plate 3 with the top surfaces of the two side molds 4 (through positioning pins) and detachably fixedly connect (through screws). Package all the components above the mold plate 1 (including the cover plate 3, the two side molds 4 and the multiple stoppers 6) in a manually pasted vacuum bag, evacuate the air, and send the tooling into the autoclave for heat preservation, pressure holding and curing to make a wing blank of the box section structure;

[0073] Step 6: After curing is completed, transfer the tooling to the indoor area and ventilate and cool it to room temperature. Then, remove the vacuum bag, place two drill jigs 5 on the mold plate 1 and at the front and rear ends of the cover plate 3. The drill jigs 5 are positioned with the mold plate 1 (through positioning pins) and detachably fixedly connected (through screws). Use the drill jigs 5 to drill positioning holes at the specified positions on the wing blank of the box section structure. After the positioning holes are drilled (clean the tooling to prevent foreign objects from appearing on the tooling), disassemble the drill jigs 5;

[0074] Step 7: Demold; first, disassemble the cover plate 3, the multiple stoppers 6 and the two side molds 4 in sequence, and then take out the wing blank of the box section structure (demolding should be carried out strictly in accordance with the demolding direction to reduce damage to the formed blank of the wing of the box section structure during demolding. After demolding, perform a series of treatments such as assembling, oiling and rust prevention on the tooling, and then store it in the warehouse for future use);

[0075] Step Eight: After demolding, trim and polish the boundary of the wing blank of the box-section structure to make the wing of the box-section structure;

[0076] Step Nine: Perform moisture-proof and anti-corrosion treatments on the surface of the wing of the box-section structure (which is a prior art), and pass the inspection.

[0077] Furthermore, in Step Five, during the vacuum pumping process, a complete vacuum leakage inspection shall be carried out. The minimum complete vacuum is 0.08 MPa (before the leakage inspection, the vacuum bag is connected to the vacuum system for at least 15 minutes. After that, turn off the vacuum system, and the reading of the vacuum gauge does not drop by more than 0.017 MPa after 5 minutes).

[0078] Furthermore, in Step Five, the curing temperature is 120 °C, the curing pressure is 0.6 Mpa, keep warm and press for 120 - 180 minutes, and detect that the negative pressure reading of the vacuum degree does not drop by more than 0.017 MPa.

[0079] The template 1, the frame 2, the cover plate 3, the side mold 4, the stop block 6 and the rib positioner assembly 8 are all made of metal Q235-A.F material; the drill jig 5 is made of metal 6061-T651 material; the corner wheel assembly 7 and the lifting ring 9 are both selected as standard parts.

[0080] The wing of the box-section structure is formed by co-curing the skin, the wing beam and the wing ribs together. The skin and the profile are formed by the template 1, the wing beam and the profile are formed by the cover plate 3 and the two side molds 4, and the wing ribs are positioned by the rib positioner assembly 8.

[0081] For those skilled in the art, it is obvious that the present invention is not limited to the details of the above exemplary embodiments, and the present invention can be implemented in other forms without departing from the spirit or basic characteristics of the present invention. Therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting. The scope of the present invention is defined by the appended claims rather than the above description. Therefore, all changes falling within the meaning and scope of the equivalent conditions of the claims are intended to be included in the present invention. Any reference signs in the claims should not be regarded as limiting the claimed claim.

[0082] In addition, it should be understood that although this specification is described according to the embodiments, not every embodiment only contains an independent technical solution. The narrative way of this specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A method for forming a wing with a box-section structure, characterized in that: The method is realized by using a wing forming tooling for a box-section structure. The forming tooling includes a template (1), a frame (2), a cover plate (3), two side molds (4), two drilling jigs (5), a plurality of stoppers (6), and a rib locator assembly (8); the top of the frame (2) is fixedly connected to the template (1) to form the tooling base; the two side molds (4) are placed on the template (1) and located on the left and right sides of the template cavity. The mold surfaces of the two side molds (4) are arranged opposite to each other. The two side molds (4) are positioned and detachably fixedly connected to the template (1). A cover plate (3) is placed on the top surfaces of the two side molds (4). The cover plate (3) is positioned and detachably fixedly connected to the top surfaces of the two side molds (4); a plurality of stoppers (6) are respectively placed on the left and right sides and the front and rear ends of the template (1) on both sides of the two side molds (4). The plurality of stoppers (6) abut against the two side molds (4). The plurality of stoppers (6) are positioned and detachably fixedly connected to the template (1); the two drilling jigs (5) are placed on the template (1) and located at the front and rear ends of the cover plate (3). The drilling jigs (5) are positioned and detachably fixedly connected to the template (1); the rib locator assembly (8) straddles the outside of the two side molds (4). The rib locator assembly (8) is positioned and detachably fixedly connected to the template (1); The method includes the following steps: Step 1: Assemble the tooling base; first, move the frame (2) to the working position, and then fixedly connect the upper ends of the template (1) and the frame (2) to form the tooling base; Step 2: Paste one side of the wing skin on the template (1); specifically: lay the composite material on the mold surface of the template cavity. For every two layers laid, paste a vacuum bag and evacuate it. After pre-compaction treatment, remove the vacuum bag until the required thickness of the skin is laid; Paste a part of the wing beam on the two side molds (4); specifically: first, lay the composite material on the mold surfaces of the two side molds (4). For every two layers laid, paste a vacuum bag and evacuate it. After pre-compaction treatment, remove the vacuum bag until the required thickness of the part of the wing beam is laid; Step 3: Place a plurality of stoppers (6) on the template (1) and located outside the periphery of the template cavity. The plurality of stoppers (6) are positioned and detachably fixedly connected to the template (1). Finally, place the two side molds (4) on the left and right sides of the template cavity. The mold surfaces of the two side molds (4) are arranged opposite to each other. The two side molds (4) are positioned and detachably fixedly connected to the template (1). The plurality of stoppers (6) abut against the two side molds (4). The space formed between the template cavity and the two side molds (4) constitutes the tooling cavity; Step 4: Place the pre-formed other part of the wing beam in the tooling cavity. The other part of the wing beam and the part of the wing beam on the two side molds (4) are positioned to form a wing beam combination. Lay the composite material on the upper surface of the wing beam combination to the required thickness and compact it to make the integral wing beam; then place the pre-formed wing rib in the middle of the integral wing beam. After placement, place the rib locator assembly (8) across the outside of the two side molds (4). The rib locator assembly (8) is positioned and detachably fixedly connected to the template (1). Use the rib locator assembly (8) to check the wing rib, and finally adjust and position the wing rib to a suitable position; Step Five: After the wing rib is positioned, disassemble the rib locator assembly (8), then position and detachably fix the cover plate (3) to the top surfaces of the two side molds (4), encapsulate all components above the form plate (1) in a cured vacuum bag, evacuate the air, and send the tooling into the autoclave for heat preservation, pressure holding, and curing to form a wing blank with a box-section structure; Step Six: After curing is completed, transfer the tooling indoors and ventilate and cool it to room temperature; then, remove the vacuum bag, place the two drill jigs (5) on the form plate (1) and at the front and rear ends of the cover plate (3), position and detachably fix the drill jigs (5) to the form plate (1), and use the drill jigs (5) to drill positioning holes at the specified positions on the wing blank with a box-section structure; after the positioning holes are drilled, disassemble the drill jigs (5); Step Seven: Demold; first, disassemble the cover plate (3), multiple stoppers (6), and the two side molds (4) in sequence, and then take out the wing blank with a box-section structure; Step Eight: After demolding is completed, trim and polish the boundary of the wing blank with a box-section structure to form a wing with a box-section structure; Step Nine: Perform moisture-proof and anti-corrosion treatments on the surface of the wing with a box-section structure and pass the inspection.

2. The method for forming a wing of a box segment structure according to claim 1; characterized in that: In Step Five, during the evacuation process, a complete vacuum leak check shall be carried out, and the minimum complete vacuum shall be 0.08 MPa.

3. The method for forming a wing with a box-section structure according to claim 1; characterized in that: In Step Five, the curing temperature is 120 °C, the curing pressure is 0.6 MPa, heat preservation and pressure holding are carried out for 120 - 180 minutes, and it is detected that the negative pressure reading of the vacuum degree does not decrease by more than 0.017 MPa.

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