Forming die and forming method for carbon fiber composite flight control machine equipment support

Abstract

The embodiment of the invention provides a forming die of a flight control machine equipment support made of a carbon fiber composite material. The forming die comprises an upper die, a lower die, an upper die locking piece and a core die used for being placed between the upper die and the lower die. The upper die comprises a middle upper die sub-block, a left upper die sub-block and a right upper die sub-block; the core mold comprises a left core mold sub-block and a right core mold sub-block, the left core mold sub-block and the right core mold sub-block respectively comprise a middle core mold and two edge core molds, each middle core mold comprises a middle core mold upper mold and a middle core mold lower mold which are overlapped, and each edge core mold comprises an edge core mold upper mold and an edge core mold lower mold which are overlapped. Compared with the prior art, the forming die is relatively simple and low in cost, the carbon fiber composite flight control machine equipment support is formed through the forming die, the internal quality of the obtained flight control machine equipment support is good, the forming procedure is simple, and the weight of the flight control machine equipment support cannot be increased.

Description

Technical Field

[0001] The present application relates to the technical field of carbon fiber production and molding, and in particular to a molding die and molding method for a carbon fiber composite material flight control equipment bracket. Background Art

[0002] In the field of aerospace, reducing weight plays a vital role in improving carrying capacity, increasing flight range, and reducing energy consumption. Carbon fiber composite materials are ideal materials for aerospace due to their light weight, high strength, high temperature resistance, good corrosion resistance and oxidation resistance.

[0003] In the aerospace field, carbon fiber composite flight control equipment brackets are often used to replace metal parts with the same structure. Due to their relatively complex structure, RTM molding, co-bonding or secondary bonding molding are often used. However, this molding method has high molding tooling (molding mold) costs, and the internal quality of the resulting parts is poor. In addition, the molding process is cumbersome and also increases the weight of the parts.

[0004] Therefore, an embodiment of the present application provides a molding die to solve the above problems. Summary of the Invention

[0005] An embodiment of the present application provides a forming mold for a carbon fiber composite material flight control equipment bracket. The forming mold is relatively simple and has low cost. Moreover, when the carbon fiber composite material flight control equipment bracket is formed using the forming mold, the obtained flight control equipment bracket has good internal quality. Not only is the forming process relatively simple, but the weight of the flight control equipment bracket will not be increased.

[0006] The present application provides a molding die for a carbon fiber composite material flight control device bracket, wherein the molding die is a hard metal mold, comprising an upper mold, a lower mold, an upper mold locking member, and a core mold for placement between the upper mold and the lower mold, wherein the upper mold is machined and manufactured according to the lower surface profile of the flight control device bracket to be formed;

[0007] The upper mold includes a middle upper mold block, a left upper mold block and a right upper mold block, the core mold includes a left core mold block and a right core mold block, the left core mold block and the right core mold block respectively include a middle core mold and two side core molds, each of the middle core molds includes a superimposed middle core mold upper mold and a middle core mold lower mold, and each of the side core molds includes a superimposed side core mold upper mold and a side core mold lower mold.

[0008] In the molding die of the carbon fiber composite material flight control machine equipment bracket described in the embodiment of the present application, it also includes an upper mold locking member, a core mold upper and lower mold positioning members, and a core mold upper and lower mold fixing member;

[0009] The left upper mold block and the right upper mold block are respectively provided with at least one upper mold positioning boss, and the lower mold is provided with an upper mold positioning groove corresponding to the upper mold positioning boss;

[0010] The middle upper mold block, the left upper mold block, and the right upper mold block are respectively provided with a first upper mold locking hole, the lower mold is processed and formed according to the upper surface profile of the flight control equipment bracket, and a second upper mold locking hole is provided on the molding margin area, and the upper mold locking member is used to lock and fix the middle upper mold block, the left upper mold block, and the right upper mold block to the lower mold respectively through the first upper mold locking hole and the second upper mold locking hole;

[0011] The middle core mold upper mold, the middle core mold lower mold, the side core mold upper mold and the side core mold lower mold are all provided with core mold upper and lower mold positioning holes and core mold upper and lower mold fixing holes. The core mold upper and lower mold positioning parts are used to position the middle core mold upper mold and the middle core mold lower mold through the core mold upper and lower mold positioning holes, and to position the side core mold upper mold and the side core mold lower mold. The core mold upper and lower mold fixing parts are used to fix the middle core mold upper mold and the middle core mold lower mold through the core mold upper and lower mold fixing holes, and to fix the side core mold upper mold and the side core mold lower mold.

[0012] In the molding die of the carbon fiber composite material flight control equipment bracket described in the embodiment of the present application, a core mold positioning and locking member is also included;

[0013] The side core mold is provided with a side core mold guide groove, and the lower mold is provided with a side core mold positioning locking hole. The core mold positioning locking piece is used to position and lock the side core mold and the lower mold through the side core mold guide groove and the side core mold positioning locking hole.

[0014] In the molding die of the carbon fiber composite material flight control equipment bracket described in the embodiment of the present application, a core mold gasket is also included;

[0015] When the core mold is mounted on the lower mold, the core mold gasket is used to be placed under the margin area at the bottom of the core mold to ensure the critical thickness dimension of the flight control equipment bracket to be formed.

[0016] The present application also provides a method for forming a carbon fiber composite material flight control equipment bracket, which is used in the forming mold of the carbon fiber composite material flight control equipment bracket described in the above embodiment. The method includes:

[0017] Adding a layer of soft rubber pressure-balancing pad on the contact surface between the upper mold and the core mold and the flight control equipment bracket to be formed, wherein the soft rubber pressure-balancing pad is formed by an autoclave;

[0018] Laying BMI resin carbon fiber unidirectional tape prepreg on the lower mold and the core mold with the soft rubber pressure pad added, and installing the core mold on the lower mold after the paving is completed;

[0019] Laying the BMI resin carbon fiber unidirectional tape prepreg on the upper mold, and after the paving is completed, the upper mold and the lower mold with the core mold installed are combined to make a bag;

[0020] The BMI resin carbon fiber unidirectional tape prepreg on the mold is cured and formed by using a hot autoclave according to a curing and molding process. After demoulding and processing, a carbon fiber composite material flight control equipment bracket is prepared.

[0021] In the carbon fiber composite material flight control equipment bracket molding method described in the embodiment of the present application, the step of adding a layer of soft rubber pressure equalizing pad on the contact surface between the upper mold and the core mold and the flight control equipment bracket to be molded comprises:

[0022] Use sandpaper to polish the preset polishing areas in the middle upper mold block, the left upper mold block, the right upper mold block, the side core mold, and the middle core mold, and lay a layer of uncured non-silicone rubber on the preset polishing areas after polishing;

[0023] The mold with the silicone rubber laid on it is used to make a bag as a whole, and then a hot autoclave is used to cure it. After the curing is completed, the auxiliary materials are removed to complete the production of the pressure equalizing pad.

[0024] In the carbon fiber composite material flight control equipment bracket molding method described in the embodiment of the present application, the bismuth resin carbon fiber unidirectional tape prepreg is laid on the lower mold and the core mold to which the soft rubber pressure equalizing pad has been added, and after the laying is completed, the core mold is installed on the lower mold, including:

[0025] Lay a layer of adhesive release cloth on the paving area of ​​the side core mold and the middle core mold where the soft rubber pressure pad is added;

[0026] The BMI resin carbon fiber unidirectional tape prepreg is laid on the lower mold and the side core mold and the middle core mold on which the adhesive release cloth is laid. After the laying is completed, the four side core molds are fixed by the side core mold guide grooves, the side core mold positioning locking holes and the core mold positioning locking parts. Then, the two middle core molds are positioned and placed according to the four side core molds, and a core mold gasket is placed in the bottom margin area of ​​the core mold;

[0027] After fixing the core mold, the sealing strip is laid outside the margin area of ​​the lower mold and the bag is pre-drawn. After the pre-drawing is completed, the twisted wire is filled in the R angle formed by the contact between the core mold and the core mold, and the core mold and the lower mold, and finally the entire layer of material of the remaining thickness is laid.

[0028] In the carbon fiber composite material flight control equipment bracket molding method described in the embodiment of the present application, the bismuth resin carbon fiber unidirectional tape prepreg is laid on the upper mold, and after the laying is completed, the upper mold and the lower mold after the core mold is installed are molded and bagged, including:

[0029] First, a layer of adhesive release cloth is laid in the paving area of ​​the middle upper mold block, the left upper mold block and the right upper mold block where the soft rubber pressure equalizing pad is added, and then the BMI resin carbon fiber unidirectional tape prepreg is laid;

[0030] The positions of the left upper mold block and the right upper mold block on the lower mold are determined by the upper mold positioning boss and the upper mold positioning groove, and then the middle upper mold block is placed to complete the positioning of the upper mold on the lower mold;

[0031] The middle upper mold block, the left upper mold block and the right upper mold block are respectively locked and fixed to the lower mold through the upper mold locking piece, the first upper mold locking hole and the second upper mold locking hole to complete the fixing of the upper mold;

[0032] After the mold is closed, the sealing strip and other auxiliary materials are laid outside the margin area of ​​the lower mold and the bag is made.

[0033] In the carbon fiber composite material flight control equipment bracket molding method described in the embodiment of the present application, the demoulding includes:

[0034] Remove the vacuum bag and other auxiliary materials on the surface of the flight control equipment bracket, as well as the middle upper mold block, the left upper mold block, the right upper mold block, the side core mold and the middle core mold, and then remove the flight control equipment bracket from the lower mold to complete the demolding.

[0035] In the carbon fiber composite material flight control equipment bracket forming method described in the embodiment of the present application, the processing includes:

[0036] Make holes and cut according to the surface size and hole position markings of the flight control equipment bracket.

[0037] The present invention provides a molding die for a carbon fiber composite flight control machine equipment support provided by an embodiment of the present invention, which is a hard metal mold, comprising an upper mold, a lower mold, an upper mold locking member, and a core mold for being placed between the upper mold and the lower mold, wherein the upper mold is processed according to the lower surface profile of the flight control machine equipment support to be formed; the upper mold comprises a middle upper mold block, a left upper mold block, and a right upper mold block, the core mold comprises a left core mold block and a right core mold block, the left core mold block and the right core mold block respectively comprise a middle core mold and two side core molds, each middle core mold comprises a superimposed middle core mold upper mold and a middle core mold lower mold, and each side core mold comprises a superimposed side core mold upper mold and a side core mold lower mold. Compared with the prior art, the molding die of the present application is relatively simple and has low cost, and the flight control machine equipment support formed by the molding die is good in internal quality, simple in molding process, and does not increase the weight of the flight control machine equipment support. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] To more clearly illustrate the technical solutions in the embodiments of the present application, the following briefly introduces the drawings required for describing the embodiments. Obviously, the drawings described below are only some embodiments of the present application. Those skilled in the art can also derive other drawings based on these drawings without inventive effort.

[0039] Figure 1 This is a schematic structural diagram of the carbon fiber composite material flight control equipment bracket provided in an embodiment of the present application.

[0040] Figure 2 This is a schematic structural diagram of a molding die for a carbon fiber composite material flight control equipment bracket provided in an embodiment of the present application.

[0041] Figure 3 A schematic structural diagram of the edge core mold provided in an embodiment of the present application.

[0042] Figure 4 A schematic flow chart of a method for forming a carbon fiber composite material flight control equipment bracket provided in an embodiment of the present application.

[0043] Figure 5 Another schematic flow chart of the method for forming a carbon fiber composite material flight control equipment bracket provided in an embodiment of the present application.

[0044] Figure 6 This is a schematic diagram of the molding of the soft rubber pressure-equalizing pad provided in an embodiment of the present application.

[0045] Description of Figure Numbers:

[0046] 10-upper mold 20-lower mold 30-core mold

[0047] 40- Upper mold locking piece 50- Core mold upper and lower mold positioning pieces

[0048] 60-core mold upper and lower mold fixing parts 70-upper mold positioning boss 80-upper mold positioning groove

[0049] 90-core mold positioning locking piece 100-edge core mold guide groove 110-core mold gasket

[0050] 101- middle upper mold block 102- left upper mold block 103- right upper mold block

[0051] 301-Middle core mold 302-Side core mold 3021-Side core mold upper mold

[0052] 3022-Edge core mold lower mold DETAILED DESCRIPTION

[0053] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the embodiments described are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without making creative efforts are within the scope of protection of this application.

[0054] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present application. In addition, the terms "first" and "second" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the said features. In the description of the present application, "multiple" means two or more, unless otherwise clearly and specifically defined.

[0055] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to mechanical connections, electrical connections, or mutual communication; they can refer to direct connections or indirect connections through an intermediate medium; they can refer to internal communication between two components or the interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on specific circumstances.

[0056] In this application, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.

[0057] The disclosure below provides many different embodiments or examples for realizing different structures of the present application. In order to simplify the disclosure of the present application, the components and settings of specific examples are described below. Of course, they are merely examples and are not intended to limit the present application. In addition, the present application may repeat reference numbers and / or reference letters in different examples, and such repetition is for the purpose of simplicity and clarity, and does not itself indicate the relationship between the various embodiments and / or settings discussed. In addition, the present application provides examples of various specific processes and materials, but those of ordinary skill in the art will appreciate the application of other processes and / or the use of other materials.

[0058] The embodiment of the present application provides a molding die for a carbon fiber composite material flight control machine equipment bracket, wherein the flight control machine equipment bracket is a multi-cavity structure, and its structural diagram is as shown in FIG. Figure 1 As shown, the part has three cavities on each side, a box-shaped structure in the middle, and an overall thickness of 4mm. Figure 2 and Figure 3 The molding mold of the carbon fiber composite material flight control equipment bracket is a hard metal mold, which includes an upper mold 10, a lower mold 20 and a core mold 30 for being placed between the upper mold 10 and the lower mold 20, wherein the upper mold 10 is processed according to the lower surface profile of the flight control equipment bracket to be formed.

[0059] Parts processing lines and hole position lines are left on the surfaces of the upper mold 10 and the lower mold 20.

[0060] The upper mold 10 includes a middle upper mold block 101, a left upper mold block 102 and a right upper mold block 103, and the core mold 30 includes a left core mold block and a right core mold block. The left core mold block and the right core mold block respectively include a middle core mold 301 and two side core molds 302. Each middle core mold 301 includes a superimposed middle core mold upper mold and a middle core mold lower mold, and each side core mold 302 includes a superimposed side core mold upper mold 3021 and a side core mold lower mold 3022.

[0061] As can be seen from the above, the core mold 30 has a total of six parts (two central core molds 301 and four side core molds 302). The embodiment of the present application is processed according to the cavity surface of the part (the flight control equipment bracket to be formed), and the core mold 30 is horizontally divided into blocks along the demolding direction to ensure the demolding of the part. Among them, to avoid being unable to demold due to the closed angle of the part, each central core mold is divided into a central core mold upper mold and a central core mold lower mold, and each side core mold 302 is divided into a side core mold upper mold 3021 and a side core mold lower mold 3022. In addition, guide holes are reserved in the core mold margin area at the four corners to ensure uniform pressure on the part.

[0062] In some embodiments, the molding die of the carbon fiber composite material flight control device bracket further includes an upper mold locking member 40 , a core mold upper and lower mold positioning members 50 , and a core mold upper and lower mold fixing members 60 .

[0063] Among them, the upper mold locking part 40 can be a locking bolt, the core mold upper and lower mold positioning parts 50 can be positioning pins, and the core mold upper and lower mold fixing parts 60 can be locking bolts.

[0064] At least one upper mold positioning boss 70 is provided on each of the left upper mold block 102 and the right upper mold block 103 , and an upper mold positioning groove 80 corresponding to the upper mold positioning boss 70 is provided on the lower mold 20 .

[0065] Among them, the upper mold positioning boss 70 and the upper mold positioning groove 80 are used to position the upper mold block 102 and the right upper mold block 103 on the lower mold 20, and the upper mold positioning groove 80 can be set in the molding margin area of ​​the lower mold 20.

[0066] The middle upper mold block 101, the left upper mold block 102 and the right upper mold block 103 are respectively provided with a first upper mold locking hole. The lower mold 20 is processed and formed according to the upper surface profile of the flight control equipment bracket to be formed. A second upper mold locking hole is provided on the forming margin area. The upper mold locking part 40 is used to lock and fix the middle upper mold block 101, the left upper mold block 102 and the right upper mold block 103 to the lower mold 20 respectively through the first upper mold locking hole and the second upper mold locking hole.

[0067] As can be seen from the above, the middle upper mold block 101 , the left upper mold block 102 and the right upper mold block 103 are all independently connected to the lower mold 20 through the upper mold locking member 40 .

[0068] The middle core mold upper mold, the middle core mold lower mold, the side core mold upper mold 3021 and the side core mold lower mold 3022 are all provided with core mold upper and lower mold positioning holes and core mold upper and lower mold fixing holes. The core mold upper and lower mold positioning parts 50 are used to position the middle core mold upper mold and the middle core mold lower mold through the core mold upper and lower mold positioning holes, and to position the side core mold upper mold 3021 and the side core mold lower mold 3022. The core mold upper and lower mold fixing parts 60 are used to fix the middle core mold upper mold and the middle core mold lower mold through the core mold upper and lower mold fixing holes, and to fix the side core mold upper mold 3021 and the side core mold lower mold 3022.

[0069] As can be seen from the above, the middle core mold upper mold and the middle core mold lower mold are positioned and connected through the core mold upper and lower mold positioning parts 50 and the core mold upper and lower mold fixing parts 60.

[0070] In some embodiments, the molding mold of the carbon fiber composite material flight control equipment bracket also includes a core mold positioning and locking member 90; a side core mold guide groove 100 is provided on the side core mold 302, and a side core mold positioning and locking hole is provided on the lower mold 20. The core mold positioning and locking member 90 is used to position and lock the side core mold 302 and the lower mold 20 through the side core mold guide groove 100 and the side core mold positioning and locking hole.

[0071] The core mold positioning locking member 90 may be a tapered pin, and the edge core mold positioning locking hole may be provided in the molding margin area of ​​the lower mold 20 .

[0072] In some embodiments, the molding mold of the carbon fiber composite material flight control equipment bracket also includes a core mold gasket 110; when the core mold 30 is installed on the lower mold 20, the core mold gasket 110 is used to be placed under the margin area at the bottom of the core mold to ensure the critical thickness dimension of the flight control equipment bracket to be formed.

[0073] Among them, the thickness of the core mold gasket is 4mm.

[0074] Among them, when using the forming mold to form a carbon fiber composite material flight control machine equipment bracket, the installation (molding) steps of the upper mold 10, the lower mold 20 and the core mold 30 are: first, the four side core molds 302 are positioned and fixed to the lower mold 20 through the core mold positioning locking piece 90, the side core mold guide groove 100 and the side core mold positioning locking hole, and then the two middle core molds 301 are positioned and placed on the lower mold 20 according to the side core mold 302, and the bottom margin of the core mold 30 is fixed. The core mold gasket 110 is placed in the area, and then the positions of the left upper mold block 102 and the right upper mold block 103 on the lower mold 20 are determined by the upper mold positioning boss 70 and the upper mold positioning groove 80, and then the middle upper mold block 101 is placed to complete the upper mold block positioning, and finally the middle upper mold block 101, the left upper mold block 102 and the right upper mold block 103 are locked and fixed to the lower mold 20 through the first upper mold locking hole, the second upper mold locking hole and the upper mold locking piece 40.

[0075] As can be seen from the above, compared with the prior art, the molding die of the present application is relatively simple and has a lower cost.

[0076] In summary, the forming mold of the carbon fiber composite material flight control equipment bracket provided in the embodiment of the present application is a hard metal mold, which includes an upper mold 10, a lower mold 20, an upper mold locking part 40 and a core mold 30 for being placed between the upper mold 10 and the lower mold 20, wherein the upper mold 10 is processed according to the lower surface profile of the flight control equipment bracket to be formed; the upper mold 10 includes a middle upper mold block 101, a left upper mold block 102 and a right upper mold block 103, the core mold 30 includes a left core mold block and a right core mold block, the left core mold block and the right core mold block respectively include a middle core mold 301 and two side core molds 302, each middle core mold 301 includes a superimposed middle core mold upper mold and a middle core mold lower mold, and each side core mold 302 includes a superimposed side core mold upper mold 3021 and a side core mold lower mold 3022. Compared with the existing technology, the molding mold of the present application is relatively simple and has low cost. Moreover, the internal quality of the flight control equipment bracket obtained by using the molding mold to mold the carbon fiber composite material flight control equipment bracket is good. Not only is the molding process relatively simple, but it also does not increase the weight of the flight control equipment bracket.

[0077] In the above embodiments, the description of each embodiment has its own focus. For parts that are not described in detail in a certain embodiment, reference can be made to the relevant descriptions of other embodiments.

[0078] See also Figures 4 to 6 The present application also provides a method for forming a carbon fiber composite material flight control device bracket, which is used in the molding die of the carbon fiber composite material flight control device bracket described in the above embodiment. The method comprises the following steps:

[0079] Step 101: adding a layer of soft rubber pressure-balancing pad on the contact surfaces of the upper mold and the core mold with the flight control device bracket to be formed, wherein the soft rubber pressure-balancing pad is formed in an autoclave.

[0080] Specifically, before laying the BMI resin carbon fiber unidirectional tape prepreg on the upper mold and the core mold, a layer of soft rubber pressure equalizing pad is first added to the upper mold and the core mold.

[0081] In some embodiments, the step of adding a layer of soft rubber pressure equalizing pad on the contact surface between the upper mold and the core mold and the flight control equipment bracket to be formed includes:

[0082] Use sandpaper to polish the preset polishing areas in the middle upper mold block, the left upper mold block, the right upper mold block, the side core mold, and the middle core mold, and lay a layer of uncured non-silicone rubber on the preset polishing areas after polishing;

[0083] The mold with the silicone rubber laid on it is used to make a bag as a whole, and then a hot autoclave is used to cure it. After the curing is completed, the auxiliary materials are removed to complete the production of the pressure equalizing pad.

[0084] Among them, the sandpaper can be 80#-160# sandpaper, and the preset grinding area is as follows Figure 6 The uncured non-silicone rubber has a thickness of 2 mm and a hardness of 70 Shore A.

[0085] The autoclave curing process is as follows: vacuum is applied throughout the process, with a vacuum level of no less than 950 mbar. Nitrogen is used as the curing medium, and the pressure is initially increased to 3 ± 0.1 bar. The temperature is then raised to 180 ± 5 °C at a rate of no less than 3 °C / min and held for 2 ± 0.1 h. After the holding period is complete, the temperature is lowered to below 60 °C and the pressure is released, ending the curing process.

[0086] Step 102: Lay BMI carbon fiber unidirectional tape prepreg on the lower mold and the core mold to which the soft rubber pressure pad has been added, and after the paving is completed, install the core mold on the lower mold.

[0087] The part (a carbon fiber composite flight control equipment bracket) has an overall thickness of 4mm and utilizes a single layer of T800 carbon fiber unidirectional tape bismaleimide resin prepreg with a cured thickness of 0.1mm. Specifically, the part layup consists of a 1mm lower mold ply, a 2mm core mold ply, and a 1mm upper mold ply.

[0088] In some embodiments, the process of laying BMI carbon fiber unidirectional tape prepreg on the lower mold and the core mold to which the soft rubber pressure equalizing pad has been added, and installing the core mold on the lower mold after the laying is completed, includes:

[0089] Lay a layer of adhesive release cloth on the paving area of ​​the side core mold and the middle core mold where the soft rubber pressure pad is added;

[0090] The BMI resin carbon fiber unidirectional tape prepreg is laid on the lower mold and the side core mold and the middle core mold on which the adhesive release cloth is laid. After the laying is completed, the four side core molds are fixed by the side core mold guide grooves, the side core mold positioning locking holes and the core mold positioning locking parts. Then, the two middle core molds are positioned and placed according to the four side core molds, and a core mold gasket is placed in the bottom margin area of ​​the core mold;

[0091] After fixing the core mold, the sealing strip is laid outside the margin area of ​​the lower mold and the bag is pre-drawn. After the pre-drawing is completed, the twisted wire is filled in the R angle formed by the contact between the core mold and the core mold, and the core mold and the lower mold, and finally the entire layer of material of the remaining thickness is laid.

[0092] The thickness of a single layer of adhesive release cloth is 0.1mm, and the core mold gasket is 4mm thick. The pre-vacuuming time for bag making is 15 ± 1min, and the pre-vacuuming pressure is no less than 800mbar. After the pre-vacuuming is completed, twisted wire is placed in the R-angle formed by the contact between the core molds and the core mold and the lower mold. Finally, the remaining 1mm thick layer of material is laid.

[0093] Step 103: paving BMI resin carbon fiber unidirectional tape prepreg on the upper mold, and after paving is completed, the upper mold and the lower mold with the core mold installed are combined to make bags.

[0094] In some embodiments, the process of paving the BMI resin carbon fiber unidirectional tape prepreg on the upper mold and, after the paving is completed, combining the upper mold with the lower mold after the core mold is installed to make the bag comprises:

[0095] First, a layer of adhesive release cloth is laid in the paving area of ​​the middle upper mold block, the left upper mold block and the right upper mold block where the soft rubber pressure equalizing pad is added, and then the BMI resin carbon fiber unidirectional tape prepreg is laid;

[0096] The positions of the left upper mold block and the right upper mold block on the lower mold are determined by the upper mold positioning boss and the upper mold positioning groove, and then the middle upper mold block is placed to complete the positioning of the upper mold on the lower mold;

[0097] The middle upper mold block, the left upper mold block and the right upper mold block are respectively locked and fixed to the lower mold through the upper mold locking piece, the first upper mold locking hole and the second upper mold locking hole to complete the fixing of the upper mold;

[0098] After the mold is closed, the sealing strip and other auxiliary materials are laid outside the margin area of ​​the lower mold and the bag is made.

[0099] Specifically, sealing strips are laid in the excess area of ​​the mold surface, and auxiliary materials such as vacuum joints and breathable felt isolation film vacuum bags are placed. The vacuum degree is required to be no less than 950mbar when making bags.

[0100] Among them, the thickness of a single layer of adhesive release cloth is 0.1mm.

[0101] Step 104: using an autoclave to cure and mold the BMI carbon fiber unidirectional tape prepreg on the mold according to a curing molding process, and after demoulding and processing, a carbon fiber composite material flight control equipment bracket is prepared.

[0102] Among them, the curing requirements are as follows: the parts are cured in an autoclave, the curing medium is nitrogen, and the whole curing process is vacuumed to control the temperature of the mold. Curing system: 1) Heat to 85℃±5℃ at a heating rate of 1~3℃ / min, maintain 85℃±5℃, and keep the temperature constant for at least 1±0.1 hours; 2) Heat to 95℃±5℃ at a heating rate of 1~3℃ / min, maintain 95℃±5℃, and keep the temperature constant for at least 1±0.1 hours; 3) Heat to 110℃±5℃ at a heating rate of 1~3℃ / min, maintain 110℃±5℃, and keep the temperature constant for at least 2±0.1 hours; 4) Heat to 125℃±5℃ (the lowest temperature of the thermocouple) at a heating rate of 1~3℃ / min, maintain 125℃±5℃, and keep the temperature constant for at least 3±0.1 5) After the insulation is completed, start pressurizing to 0.6MPa, maintain 125℃±5℃, 6bar constant temperature for at least 3±0.1 hours; 6) Heat to 190℃±5℃ (the lowest temperature of the thermocouple) at a heating rate of 1~3℃ / min, maintain 190℃±5℃, 6bar constant temperature for at least 2±0.1 hours; 7) Heat to 220℃±5℃ (the lowest temperature of the thermocouple) at a heating rate of 1~3℃ / min, maintain 220℃±5℃, 6bar constant temperature for at least 2±0.1 hours; 8) Cool down at a rate of no more than 3℃ / min, reduce the pressure to below 60℃, release the pressure, open the can, and end the curing.

[0103] In some embodiments, the demolding comprises:

[0104] Remove the vacuum bag and other auxiliary materials on the surface of the flight control equipment bracket, as well as the middle upper mold block, the left upper mold block, the right upper mold block, the side core mold and the middle core mold, and then remove the flight control equipment bracket from the lower mold to complete the demolding.

[0105] Among them, wooden wedges and other soft tools can be used to assist in demoulding.

[0106] In some embodiments, the processing comprises:

[0107] Make holes and cut according to the surface size and hole position markings of the flight control equipment bracket.

[0108] The embodiment of the present application adopts autoclave one-piece molding, and the overall size and key surface of the part are guaranteed by the hard metal mold. The curing pressure is transmitted by adding a soft equalizing pressure pad in the local area of ​​the local metal mold surface, and the internal quality of the part is guaranteed by combining the vacuum bag pressure and the autoclave pressure. By combining the hard metal mold with the soft rubber equalizing pressure pad, the autoclave one-piece molding of the multi-cavity carbon fiber composite material flight control equipment bracket can be achieved. The mold form is relatively simple, and the equalizing pressure pad molding method is relatively simple. This method can enhance the internal quality of the part while increasing the part molding efficiency, reducing the manufacturing process, and improving the product's market competitiveness.

[0109] Compared with the existing technology, the significant advantages of the present invention are: the present invention can realize the integrated molding of multi-cavity carbon fiber composite material flight control equipment bracket, adopt the autoclave process, optimize the pressure transmission path, enhance the internal quality of the parts, simplify the molding method, reduce the manufacturing process, increase the part molding efficiency, reduce the part manufacturing cost, and improve the product market competitiveness.

[0110] All of the above optional technical solutions can be combined in any way to form optional embodiments of the present application, and will not be described in detail here.

[0111] During specific implementation, the present application is not limited by the execution order of the various steps described. If no conflict occurs, some steps can be performed in other orders or simultaneously.

[0112] From the above, it can be seen that the carbon fiber composite material flight control equipment bracket molding method provided in the embodiment of the present application is to first add a layer of soft rubber equalizing pressure pad on the contact surface of the upper mold and the core mold with the flight control equipment bracket to be molded, and the soft rubber equalizing pressure pad is molded by a hot autoclave. Then, the double-male resin carbon fiber unidirectional tape prepreg is laid on the lower mold and the core mold to which the soft rubber equalizing pressure pad has been added, and the core mold is installed on the lower mold after the laying is completed. Then, the double-male resin carbon fiber unidirectional tape prepreg is laid on the upper mold, and after the laying is completed, the upper mold and the lower mold with the core mold installed are molded and bagged. Finally, the double-male resin carbon fiber unidirectional tape prepreg on the mold is cured and molded by a hot autoclave according to the curing molding process. After demolding and processing, a carbon fiber composite material flight control equipment bracket is prepared. The embodiment of the present application transmits curing pressure by adding a soft equalizing pressure pad to a local area of ​​the metal mold surface, combines vacuum bag pressure and autoclave pressure to ensure the internal quality of the part, and realizes the autoclave one-piece molding of a multi-cavity carbon fiber composite material flight control equipment bracket by combining a hard metal mold with a soft rubber equalizing pressure pad. The mold form is relatively simple, and the equalizing pressure pad molding method is relatively simple. While being able to enhance the internal quality of the part, it increases the part molding efficiency, reduces the manufacturing process, and improves the product's market competitiveness.

[0113] The above is a detailed introduction to the forming mold and forming method of a carbon fiber composite material flight control equipment bracket provided in the embodiment of the present application. Specific examples are used in this article to illustrate the principles and implementation methods of the present application. The description of the above embodiments is only used to help understand the technical solution and core idea of ​​the present application; ordinary technicians in this field should understand that they can still modify the technical solutions recorded in the aforementioned embodiments, or replace some of the technical features therein with equivalents; and these modifications or replacements do not cause the essence of the corresponding technical solution to deviate from the scope of the technical solution of the embodiments of the present application.

Claims

1. A molding die for a carbon fiber composite material flight control equipment bracket, characterized in that: The molding die is a hard metal die, which includes an upper die, a lower die, and a core die placed between the upper die and the lower die, wherein the upper die is processed according to the lower surface profile of the flight control machine equipment bracket to be formed; The upper mold includes a middle upper mold block, a left upper mold block and a right upper mold block, the core mold includes a left core mold block and a right core mold block, the left core mold block and the right core mold block respectively include a middle core mold and two side core molds, each of the middle core molds includes a superimposed middle core mold upper mold and a middle core mold lower mold, and each of the side core molds includes a superimposed side core mold upper mold and a side core mold lower mold.

2. The molding die of the carbon fiber composite material flight control equipment bracket according to claim 1, characterized in that: It also includes an upper mold locking piece, a core mold upper and lower mold positioning piece, and a core mold upper and lower mold fixing piece; The left upper mold block and the right upper mold block are respectively provided with at least one upper mold positioning boss, and the lower mold is provided with an upper mold positioning groove corresponding to the upper mold positioning boss; The middle upper mold block, the left upper mold block and the right upper mold block are respectively provided with a first upper mold locking hole, the lower mold is processed and formed according to the upper surface profile of the flight control machine equipment bracket to be formed, and a second upper mold locking hole is provided on the forming margin area, and the upper mold locking member is used to lock and fix the middle upper mold block, the left upper mold block and the right upper mold block with the lower mold respectively through the first upper mold locking hole and the second upper mold locking hole; The middle core mold upper mold, the middle core mold lower mold, the side core mold upper mold and the side core mold lower mold are all provided with core mold upper and lower mold positioning holes and core mold upper and lower mold fixing holes. The core mold upper and lower mold positioning parts are used to position the middle core mold upper mold and the middle core mold lower mold through the core mold upper and lower mold positioning holes, and to position the side core mold upper mold and the side core mold lower mold. The core mold upper and lower mold fixing parts are used to fix the middle core mold upper mold and the middle core mold lower mold through the core mold upper and lower mold fixing holes, and to fix the side core mold upper mold and the side core mold lower mold.

3. The molding die of the carbon fiber composite material flight control machine equipment bracket according to claim 2, characterized in that: Also includes a core mold positioning locking member; The edge core mold is provided with an edge core mold guide groove, and the lower mold is provided with an edge core mold positioning and locking hole. The core mold positioning and locking member is used to position and lock the edge core mold and the lower mold through the edge core mold guide groove and the edge core mold positioning and locking hole.

4. The molding die of the carbon fiber composite material flight control equipment bracket according to claim 3, characterized in that: Also included is a core mold gasket; When the core mold is installed on the lower mold, the core mold gasket is used to be placed under the margin area at the bottom of the core mold to ensure the critical thickness dimension of the flight control machine equipment bracket to be formed.

5. A method for molding a carbon fiber composite material flight control machine equipment bracket, used in the molding die of the carbon fiber composite material flight control machine equipment bracket according to claim 4, characterized in that: The method comprises: A layer of soft rubber pressure-balancing pad is added on the contact surface between the upper mold and the core mold and the flight control equipment bracket to be formed, wherein the soft rubber pressure-balancing pad is formed by a hot-pressing tank; Laying the BMI resin carbon fiber unidirectional tape prepreg on the lower mold and the core mold to which the soft rubber pressure equalizing pad has been added, and installing the core mold on the lower mold after the paving is completed; Laying the BMI resin carbon fiber unidirectional tape prepreg on the upper mold, and after the paving is completed, the upper mold and the lower mold with the core mold installed are molded together to make a bag; The BMI carbon fiber unidirectional tape prepreg on the mold is cured and formed by using a hot autoclave according to a curing and molding process, and a carbon fiber composite material flight control machine equipment bracket is prepared after demoulding and processing.

6. The method for forming a carbon fiber composite material flight control equipment bracket according to claim 5, characterized in that: The method of adding a layer of soft rubber pressure equalizing pad on the contact surface between the upper mold and the core mold and the flight control machine equipment bracket to be formed comprises: Use sandpaper to grind the preset grinding areas in the middle upper mold block, the left upper mold block, the right upper mold block, the side core mold and the middle core mold, and lay a layer of uncured non-silicone rubber in the preset grinding areas after grinding; The mold with the silicone rubber laid on it is used to make a bag as a whole, and then cured in an autoclave. After the curing is completed, the auxiliary materials are removed to complete the manufacture of the pressure equalizing pad.

7. The method for forming a carbon fiber composite material flight control equipment bracket according to claim 6, characterized in that: The method comprises: laying the BMI resin carbon fiber unidirectional tape prepreg on the lower mold and the core mold to which the soft rubber pressure equalizing pad has been added, and installing the core mold on the lower mold after the laying is completed, comprising: Lay a layer of adhesive release cloth in the paving area of ​​the edge core mold and the middle core mold where the soft rubber pressure equalizing pad is added; The BMI resin carbon fiber unidirectional tape prepreg is laid on the lower mold and the side core mold and the middle core mold on which the adhesive release cloth is laid. After the laying is completed, the four side core molds are fixed by the side core mold guide grooves, the side core mold positioning locking holes and the core mold positioning locking parts, and then the two middle core molds are positioned and placed according to the four side core molds, and a core mold gasket is placed in the bottom margin area of ​​the core mold; After fixing the core mold, lay the sealing strip outside the surplus area of ​​the lower mold and pre-draw the bag. After the pre-drawing is completed, fill the twisted wire at the R angle formed by the contact between the core mold and the core mold, and the core mold and the lower mold, and finally complete the paving of the entire layer of material of the remaining thickness.

8. The method for forming a carbon fiber composite material flight control equipment bracket according to claim 7, characterized in that: The method of paving the BMI resin carbon fiber unidirectional tape prepreg on the upper mold, and after the paving is completed, the upper mold and the lower mold after the core mold is installed are molded and bag-made, including: Firstly lay a layer of adhesive release cloth in the laying area of ​​the middle upper mold block, the left upper mold block and the right upper mold block where the soft rubber pressure equalizing pad is added, and then lay the BMI resin carbon fiber unidirectional tape prepreg; The positions of the left upper mold block and the right upper mold block on the lower mold are determined by the upper mold positioning boss and the upper mold positioning groove, and then the middle upper mold block is placed to complete the positioning of the upper mold on the lower mold; The middle upper mold block, the left upper mold block and the right upper mold block are respectively locked and fixed with the lower mold through the upper mold locking piece, the first upper mold locking hole and the second upper mold locking hole to complete the fixing of the upper mold; After the mold is closed, the sealing strip and other auxiliary materials are laid outside the margin area of ​​the lower mold and the bag is made.

9. The method for forming a carbon fiber composite material flight control equipment bracket according to claim 8, characterized in that: The demoulding comprises: Remove the vacuum bag and other auxiliary materials on the surface of the flight control machine equipment bracket, as well as the middle upper mold block, the left upper mold block, the right upper mold block, the side core mold and the middle core mold, and then remove the flight control machine equipment bracket from the lower mold to complete demolding.

10. The method for forming a carbon fiber composite material flight control equipment bracket according to claim 9, characterized in that: The processing includes: Make holes and cut according to the surface size and hole markings of the flight control equipment bracket.

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