CN113268832A

CN113268832A - Design method of composite material bonding mold

Info

Publication number: CN113268832A
Application number: CN202110628350.2A
Authority: CN
Inventors: 邵一丹
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-06-04
Filing date: 2021-06-04
Publication date: 2021-08-17
Anticipated expiration: 2041-06-04
Also published as: CN113268832B

Abstract

A design method of a composite material bonding mold comprises the following steps: s1: designing a product bonding surface; s2: integrally designing a mould; the step S1 includes: s11: establishing a gold model of a multi-sample scanning product; s12: establishing a profile model with rebound compensation; s13: designing a molded surface product line and a rim of the mold; the step S2 includes: s21: the fixed frame and the molded surface are flexibly connected; s22: the mounting design of the heat radiating fins on the windward side, the vacuum joint and the thermocouple; s23: designing a product quick-mounting cover and a sealing strip; the invention provides a method for designing a whole set of composite material bonding molds which is universal for various machine types from product reading, data processing, model building, digital-analog simulation, tool design to cycle inspection, adopts a digital-analog design method with rebound compensation in bonding molded surface design, greatly improves the precision of maintaining the molded surface data of products, shortens the manufacturing cycle of molds and reduces the manufacturing cost aiming at the repair of large-size composite material maintenance components.

Description

Design method of composite material bonding mold

Technical Field

The invention belongs to the field of civil aviation maintenance, and particularly relates to a design method of a composite material bonding mold.

Background

Since the seventies of the last century, secondary load-bearing structures and interior structures of airplanes are made of composite materials, and carbon fiber composite materials have the advantages of high strength, high modulus and the like, are rapidly applied to civil aircrafts, cover fuselage structures basically and completely until the 21 st century, and gradually develop to primary load-bearing structures. Therefore, as a civil aviation maintenance industry, in the repair of composite material members, the rapid development of bonding molds in the directions of multiple specifications, large size and the like is met, and new challenges are met. The maintenance of the composite material member mainly adopts a vacuum bag hot-press molding process, a maintenance member composite material prepreg sheet is pressed on a mold, an aluminum alloy honeycomb and a resin bonding film sandwich structure are placed, then a porous separation film, a surface adhesive tape, a breathable cloth and the like are sequentially laid layer by layer, finally the maintenance member and all layers are sealed on the bonding mold by a vacuum bag and a vacuum adhesive tape, and the maintenance member and all layers are filled into an autoclave. Pressing each layer of thin plate on the mould through compressed air, continuously vacuumizing in the vacuum bag, extracting volatile matters in the thermosetting process and air between each layer of the thin plate, minimizing the acting area of the compressed air on the whole maintenance component, heating to melt the adhesive, preserving heat and curing, then cooling to bond the composite prepreg, the aluminum alloy honeycomb and the resin bonding film sandwich into a whole, and keeping the outline and the shape of the prepreg thin plate the same as the bonding profile of the mould. In the whole hot pressing process flow, the forming surface of the maintenance component is tightly attached to the molding surface of the bonding mold, so that the shape of the maintenance component can be equal to the molding surface of the bonding mold.

The invention provides a set of method for designing a composite material bonding mold which is universal from product reading, data processing, model building, digital-analog simulation, tool design to cycle inspection and is suitable for various types of products. In particular to the structural repair of Fan cowling (Fan cowling) of various models of wave-sound and air passenger planes. Selecting a Boeing747-400 model as an example, and referring to the chapter number of an aircraft maintenance manual: 51-70-04. In the maintenance manual, the maintenance member is required to be wrapped by a porous separation membrane, a surface adhesive tape, a breathable cloth and the like in sequence, and then the maintenance member is put into a vacuum bag for thermal bonding process maintenance, so that the operation procedure is complicated and the consumption of consumables is large. The conventional mold design method in China adopts a design mode of analog size transmission (namely mold line template-master mold-forming mold), profile data are transmitted through a physical part in the design process, the transmission precision of the profile data is low, the processing cost for the master mold is high, the processing period of the whole mold is long, the rapid development of the current bonding mold in the directions of multiple specifications, large size and the like cannot be adapted, and the storage of the master mold and the inspection of the profile data of the bonding mold are also very difficult.

In view of the above problems, a design method of a composite material bonding mold is needed to meet the requirements of mold design.

Disclosure of Invention

The invention aims to optimize the traditional thermal bonding process flow, overcome the defects of the prior art in production and provide a design method of a composite material bonding die.

The purpose of the invention is realized as follows: a design method of a composite material bonding mold comprises the following steps:

s1: designing a product bonding surface;

s2: and (5) integrally designing the die.

Further, the step S1 includes:

s11: and establishing a gold model of the multi-sample scanning product. Firstly, a single sample is scanned for multiple times, a data model of a single product is established by using an averaging method for data processing, then a plurality of samples are selected, a data model of a plurality of samples is established by using the same method of the single sample, product deformation and design tolerance are comprehensively considered, and finally, a golden data model of the product is established by using a plurality of samples for digital-analog processing.

S12: and establishing a profile model with rebound compensation. And (3) slicing the gold data model in a direction orthogonal to the symmetry axis, then performing finite element simulation on each two-dimensional slice model, and establishing a springback compensation model. And finally, splicing and fitting the molded surface model with the springback compensation.

S13: and designing a mold profile product line and edges. After the mold surface is determined, the mold surface is expanded outwards by 4-6mm along the mold surface model and then is lifted to the opening direction by 2-3mm to be used as a product line. After the product line is determined, the product line is extended by 125mm in the tangential direction and then is bent at a right angle and extended by 30-50mm to be used as the edge of the molded surface model.

Further, the step S2 includes:

s21: the fixed frame and the molded surface are flexibly connected. The bonding molded surface is fixed by a frame structure with enough strength and rigidity, and the whole structure of the die is manufactured by adopting a square steel frame structure. And the frame structure and the bonding molded surface are fixed by adopting adjustable stay cable type flexible connection.

S22: and the mounting design of the heat radiating fins on the windward side, the vacuum joint and the thermocouple. Uniformly arranging radiating fins at the bottom of the bonding molded surface of the die in the direction of airflow of the autoclave; the vacuum joint is integrated on the product quick-mounting cover; the thermocouple is embedded in the bottom of the bonding profile of the mold.

S23: the design of the product fast-assembling lid and sealing strip. A brand-new product quick-assembly cover is designed to replace the traditional breathable cloth, heat-preservation cotton and a vacuum bag, and the sealing strip which can be repeatedly used at the periphery of the quick-assembly cover is used for replacing the traditional vacuum adhesive tape.

The advantages of the invention are as follows:

1. the invention provides a method for designing a whole set of composite material bonding mould which is universal for various machine types from product reading, data processing, model building, digital-analog simulation, tool design to cycle inspection.

2. The invention adopts a digital-analog design method with rebound compensation in the design of the bonding molded surface, greatly improves the precision of the molded surface data of the maintenance product, shortens the manufacturing period of the die and reduces the manufacturing cost aiming at the repair of the large-size composite material maintenance component.

3. In the overall design of the die, the packaging material of the maintenance component is integrated on the product quick-mounting cover of the die, so that the operation process is simplified, the consumption of consumables is reduced, and the operation working hour is shortened.

Drawings

FIG. 1 is a flow chart of the overall design of a composite bonding mold.

FIG. 2 is a surface-treated version of a fairing of an engine fan of a certain type.

Fig. 3 is a gold model of a multi-sample scanning product.

Fig. 4 shows the two-dimensional slice model spring back deformation.

FIG. 5 is a three-dimensional model sliced orthogonally to the axis of symmetry.

Fig. 6 is a two-dimensional slice model of the repair member.

Fig. 7 is a process of establishing a two-dimensional slice model with rebound compensation.

Fig. 8 is a design structure view of a fixed frame.

FIG. 9 is a view of the design of the quick lid of the product.

Fig. 10 is a self-checking color difference error analysis diagram.

Detailed Description

In order to make the technical solutions in the embodiments of the present application better understood, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

The embodiment of the application provides a design method of a composite material bonding mold.

Example 1. As shown in fig. 1-10:

a design method of a composite material bonding mold comprises the following steps:

s1: designing a product bonding surface;

s2: and (5) integrally designing the die.

The step S1 includes:

s11: and establishing a gold model of the multi-sample scanning product.

Firstly, a single sample is scanned for multiple times, a data model of a single product is established by using an averaging method for data processing, then a plurality of samples are selected, a data model of a plurality of samples is established by using the same method of the single sample, product deformation and design tolerance are comprehensively considered, and finally a product gold model is established by using a plurality of sample digital-analog processing.

As shown in fig. 2-10:

the scanning method of the single product comprises the following steps: the method comprises the steps of removing paint on the surface of a maintenance component until a fiber layer is formed, cleaning the surface, placing the maintenance component on a bracket which does not generate stress deformation, enabling a bonding surface to be outward, standing the maintenance component in a controlled environment with the temperature of 20 +/-2 ℃ and the humidity of 35-45% for more than 4 hours, and then pasting laser tracking reflector plates (CCR for short) on a bonding working surface at equal intervals, wherein the pasting density of the CCR reflector can be increased for a profile with large curvature and complex configuration. Scanning the bonding surface, linking with poly work space data analysis software to generate a high-density point cloud data packet, and under the condition that an oversized component instrument cannot be scanned at one time, scanning in a segmented mode, aligning and splicing point cloud data. Finally, a single sample single-scanning high-density point cloud data packet is generated.

Data processing of multiple scans of a single product: the same method for scanning a single product is adopted, the single product is scanned for multiple times to obtain high-density point cloud data (about 30 thousands) of the single product, noise reduction and impurity removal are carried out by using an N-point average filtering method, then filtering is carried out by using a maximum deviation value method, and a data packet is compressed to about 5 thousands of gridded point cloud data. In order to avoid the large data volume of single processing, high-density point cloud data can be partitioned, then data references of a plurality of data packets are aligned, point cloud data of the same position are combined, the data processing method is repeated, and finally all blocks are spliced to obtain a mean value model of multiple scans of a single sample.

As shown in fig. 3-10:

and (3) processing a product multi-sample model to establish a product gold model: the method for establishing the mean model by adopting the single-sample multi-scanning is adopted to scan multiple samples, and because the obtained point cloud data is a data set of the multi-sample multi-scanning and the point cloud data of the large-size component is obtained by firstly partitioning and then combining, in the process of establishing the curved surface by using the point cloud data, the NURBS curved surface is established by adopting a line configuration surface method, firstly the smoothness of the curve is ensured, bad points (namely deviation position points) are removed by applying a uniform curve fitting command, and the curvature change of the curve is kept uniform. In places with larger curvature, redundant curvature offset points are deleted (namely the shortest distance between a sampling point and the initial curved surface is less than the offset distance, the sampling point is a redundant point) so as to avoid the phenomenon of self-crossing of the offset curved surface caused by the fact that the offset distance is less than the main curvature radius, and then the smoothness of the curved surface is ensured by adjusting the curvature comb on the section. And finally, carrying out detail processing such as bridging, transition, cutting and the like on each section of the curved surface to generate a complete NURBS curved surface model. The method comprehensively considers the deformation and the design tolerance of the product and establishes a product gold model. Because the maintenance product is an adhesive surface tightly attached to the mold, the product gold model is used as a basic model of the adhesive surface of the mold.

S12: and establishing a profile model with rebound compensation.

As shown in fig. 4-10:

because the composite material thermal bonding process is to cure and bond different materials of each layer into a whole by using a resin adhesive, and the springback and the warping deformation generated in the curing process are inevitable, a gold model of a product obtained by scanning is required to be a configuration after curing, and a profile model of a bonding mould is a configuration before curing, so that a profile model with springback compensation is required to be established to offset the deformation in the curing process.

As shown in fig. 5-10:

as Fan cowlings (Fan cowling) of various types are generally in a U-shaped geometric symmetrical structure, internal residual stress is restricted mutually, so that the deformation of the whole maintenance component along the direction of the symmetrical axis is small, and the deformation of the whole maintenance component in the direction orthogonal to the symmetrical axis is close to each other. Therefore, the three-dimensional model can be sliced in the direction orthogonal to the symmetry axis, the expected deformation of the whole three-dimensional model is fitted by analyzing the deformation of the single two-dimensional model, the method has the advantages of small calculated amount, high simulation efficiency and no influence on the design precision of a digital model, the design precision can be completely covered by the manufacturing precision of the fiber prepreg paving layer, and the method is a simple and effective simulation method.

As shown in fig. 6-10:

in the process of curing and bonding, the stress-deformation analysis by taking the process as the guide of the maintenance component has the following main reasons of resilience and warping: thermal strain caused by the anisotropy of the material, resin curing shrinkage strain, stress gradient in the component formed by temperature and resin curing degree, resin flow caused by the resin pressure gradient and mechanical constraint of a tool. The modeling mode of the invention different from the traditional theoretical research is as follows: firstly, according to actual production experience, a maintenance component has a glue absorption layer poor glue area on the surface attached with a vacuum bag, and a glue rich area with higher resin content on the surface attached with a tool, so that a non-uniform resin fluid curing shrinkage model is established; and secondly, establishing an anisotropic stress model of the multi-layer material along the thickness direction by using a plurality of layers of fiber prepreg sheets, non-uniform hardened resin adhesive layers and an aluminum alloy honeycomb sandwich structure according to the actual laying condition of the maintenance component. Since the thermal expansion coefficient of the fiber prepreg of the bonding mould profile material and the repair member is similar, the mechanical constraint stress of the tool can be ignored.

The method for establishing the profile model with rebound compensation comprises the following steps: the product gold model is used as a basic model of the bonding profile of the mold, slices are made in the direction orthogonal to the symmetry axis of the basic model according to engineering experience, the positions and the number of the slices are determined by predicting the size of the profile, if the profile has an opening or a part with large profile change, the number of the slices can be increased, and the number of the slices can be reduced for relative singleness of the structure. In short, the more slices are selected, the higher the precision of the three-dimensional model correction is, and the smoother the three-dimensional model correction is. And then carrying out finite element simulation on each two-dimensional slice model, and establishing a springback compensation model. And finally, splicing and fitting the molded surface model with the springback compensation.

The method for establishing the finite element simulation springback compensation model of the two-dimensional slice model comprises the following steps: the uniformity of the hot atmosphere of the autoclave is assumed to be good, the wave sound standard or the national first-level tank standard is met, the uniformity of the airflow field is also ensured on the design of the main body framework of the mold, and the temperature of the bonding surface of the mold is consistent. Wherein the coupling temperature field only considers the two aspects of the heat release of the curing reaction of the resin adhesive and the forced convection heat exchange inside the autoclave. And the pressure field is the sum of the positive pressure of the autoclave body and the negative pressure in the vacuum bag, and the pressure at each part is the same under the assumption that the vacuum bag has no air leakage. The lay-up of the fibre prepreg was (45/0/-45/90/45/0/-45/0). In conclusion, the stress analysis of the two-dimensional slice model is carried out by taking X-Z as a global coordinate axis, 1-3 as a product coordinate axis and taking temperature and pressure as variables.

Heterogeneous resin fluid curing shrinkage volume-stress model:

in equation 1

In order to shrink the volume for the resin to cure,

for total linear curing shrinkage strain, V_fIs the fiber volume content, V_rThe resin poisson ratio.

Multilayer material anisotropic stress-deformation model:

in equation 2

Respectively the plane stress of each layer of material,

is the modulus constant of the resin, σ_x，σ_zRespectively node stress, τ_xzIs a shear force. V_13cIs Poisson's ratio, E_11c，E_33cRespectively is the modulus of elasticity, G_13cIs the shear modulus.

Substituting a plurality of layers of fiber prepregs, a non-uniform hardened resin bonding layer and an aluminum alloy honeycomb structure into a corresponding formula according to an actual sequence, and only considering the accumulated total strain of fiber prepreg sheets of a die bonding surface (namely a tool surface):

i in equation 3 is the number of layers of the repair member

As shown in fig. 7-10:

after the two-dimensional slice model is built, the geometric dimensions are input by using COMPRO simulation software, the geometric dimensions are substituted into the material parameters of the fiber prepreg, the epoxy resin adhesive film and the aluminum alloy honeycomb, the two-dimensional slice model is subjected to grid division, and boundary conditions anda constraint relationship to each other. Inputting the temperature rise and fall condition and the vacuum pressure parameters of the thermal bonding process, and simulating the accumulated stress deformation displacement delta X of the fiber prepreg sheet on the bonding surface (namely the tool surface) of the two-dimensional slice model after the thermal bonding process is completed_z(coordinate after thermal bonding-coordinate before thermal bonding), the maximum opening position (i.e., the maximum value of Z axis) was judged as the X-axis deformation displacement Δ X_zmaxWhether the deformation displacement is greater than (0.2+ L/10) mm (wherein L is the maximum opening distance of the U-shaped structure and the unit is m), if not, the deformation displacement is sequentially compensated to the X-axis coordinate (namely X ') of the two-dimensional slice model according to the Z axis of the global coordinate axis'_z＝X_z-ΔX_z) And the obtained model data is used as model data before simulation, and the operations are repeated and repeated. Up to Δ X_zmaxAnd (4) meeting the requirements, wherein the compensated data at the moment is the final two-dimensional slice model with rebound compensation.

And simulating all the two-dimensional slice models in the same way to obtain the two-dimensional slice models with rebound compensation which meet the requirements, and then splicing and fitting the curve groups according to the previous slice positions to obtain the three-dimensional model with the rebound compensation bonding molded surface.

S13: and designing a mold profile product line and edges. After the profile model with rebound compensation is determined, the profile model is expanded outwards by 4-6mm and then is raised by 2-3mm towards the opening direction to be used as a product line or a paving line, so that the maintenance product is prevented from falling off from the bonding profile in the thermal expansion process. After a product line is determined, extending 125mm outwards along the tangential direction, then bending the right angle and extending for 30-50mm, and using the product line as the edge of the profile model to reduce the closing-up deformation of the product (one side of the fast-assembly cover hinge needs to be extended by 50mm more). In order to conveniently take out the maintenance product from the molded surface, chamfering needs to be carried out on the edge part, the inner angle of the molded surface is larger than 100 degrees, the chamfering radius of the edge part is larger than 25mm, the inner angle of the molded surface is smaller than 100 degrees, and the chamfering radius of the edge is larger than 12 mm; if the profile is an external corner the edge portion is chamfered to a radius greater than 6 mm.

The design of the bonding molded surface of the die is finished.

As shown in fig. 8-10:

the step S2 includes:

s21: the fixed frame and the molded surface are flexibly connected. The design principle of the fixed frame is as follows: the bonding profile is fixed to the maximum extent, and materials with small specific heat capacity and a configuration with good ventilation performance are selected as far as possible. The fixing frame of the traditional die adopts a thin plate grid structure, and the fixing frame of the invention adopts a square tube frame structure with enough strength and rigidity, so that the thermal expansion stress in the symmetrical axis direction of a U-shaped structure of a Fan cowling (Fan cowling) can be counteracted mutually in the process of a thermal bonding process, the ventilation of the whole structure is better, and the total thermal capacity is lower. The square tube frame structure and the bonding molded surface are flexibly connected in an adjustable stay cable mode, so that thermal expansion stress in the normal direction of the bonding molded surface formed by different materials of the fixed frame and the bonding molded surface can be eliminated, and the bonding molded surface can be finely adjusted conveniently during mold period verification.

The specific design method of the fixed frame comprises the following steps: the fixing points are arranged at equal circumferential angle intervals in the direction orthogonal to the symmetry axis of the U-shaped structure of the Fan cowling (Fan cowling), and the fixing points are arranged at equal intervals in the direction along the symmetry axis, and according to engineering experience and structural strength of the square tube frame, the fixing points are generally arranged at intervals of 15 degrees in the direction orthogonal to the symmetry axis and at intervals of 100mm in the direction along the symmetry axis.

The specific design method of the flexible connection of the molded surfaces comprises the following steps: each fixed point on the fixed frame structure is connected with an adjustable inhaul cable, and the other end of the inhaul cable is connected with the bottom of the bonding molded surface through high-temperature silica gel.

S22: and the mounting design of the heat radiating fins on the windward side, the vacuum joint and the thermocouple. For a mold which is deeper along the air flow direction, in order to ensure that the temperature of the mold is uniform at all positions of a product bonding molded surface in an autoclave and the temperature following performance of the mold in the autoclave is good, radiating fins can be generally arranged at the bottom of the bonding molded surface along the air flow direction in the autoclave, and the fins are not integral but divided into a plurality of sections so as to prevent thermal expansion stress. The fins are arranged so as not to obstruct the flow of the air stream.

The mounting mode of the vacuum joint is as follows: in order to ensure the bonding quality required by the manual, the vacuum bag is about 40cm according to the engineering experience²The area needs to be provided with a vacuum connector which is integrated into the productThe quick-assembly cover is covered (the design of the quick-assembly cover is shown in S23), the vacuum tube faces upwards, the product is conveniently packaged, the air leakage risk of the vacuum bag is reduced, and the adhesive is effectively prevented from being sucked into the vacuum tube in a molten state.

The thermocouple installation mode is as follows: according to the requirements of the manual, the product is tightly attached to the lower portion of the vacuum bag, and the vacuum pumping is performed to enable the product to be tightly attached to the product, so that the temperature of the product is monitored in real time, the product fast-assembling cover replaces the original product packaging (the fast-assembling cover is designed to be S23), therefore, the mode of embedding the bottom of the bonding molded surface of the mold is adopted in the installation of the thermocouple, the product is maintained to the maximum extent, the packaging efficiency of the product is improved, and the surface of the product is prevented from being crushed.

As shown in fig. 9-10:

Wherein the design of product fast-assembling lid does: and if the cover is large in size, spokes can be pulled in the middle of the square tube frame to reduce deformation. And then covering a layer of convection high-temperature silica gel film on the peripheral frame to replace the adhesive absorption cloth, the breathable cloth, the heat preservation cotton and the vacuum bag required by the manual. The convection high-temperature silica gel film is provided with a groove towards the surface of the product, and gas can be convected between the product and the cover when the vacuum pumping is carried out, so that the silica gel film can be completely pressed on the product to replace functions of breathable cloth, heat-preservation cotton and a vacuum bag required by a manual.

The design of the sealing strip is as follows: a circle of an angle type sealing strip is adhered to a peripheral frame of the product quick-mounting cover, the opening direction of the angle type is outward, the product quick-mounting cover and a die are connected through a hinge and a lock catch, and the traditional vacuum adhesive tape adhering type sealing is replaced by sealing strip extrusion type sealing.

The overall design of the composite material bonding mould is finished.

As shown in fig. 10:

the mold is manufactured and finished in the using process, different from a metal mold, the composite material bonding mold is easy to age, warp and layer due to repeated temperature rise and fall changes, the bonding molded surface can be periodically tested in order to ensure the molded surface data of a product and monitor the state of the mold, the testing method has no domestic or international standard reference, and a set of unified testing standard does not exist in the industry. The invention adopts a self-checking method with higher recognition in the industry: and (poly work) space data analysis software is used, profile model data with springback compensation are imported to serve as true value data of the detected mold, a reference point alignment (RPS) method is used for aligning the real mold object with the datum coordinates of the data model, the bonding profile of the to-be-detected model is comprehensively scanned, the spatial position relations of the real mold object and each point of the data model are compared one by one, and a color difference error analysis chart is generated. According to engineering experience, a plurality of detection points (generally about 30 points) in the maximum color difference area in the error analysis chart are selected, and a detection point error analysis report is obtained by using a single-point measurement mode. Referring to ISO14253 product geometry specifications, the self-checking tolerance of the composite bonding mold is defined as: plus or minus 0.8 plus L/2mm (L is the maximum opening distance of the U-shaped die and is measured in meters).

It is noted that, in this document, relational terms such as "first" and "second," and the like, may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

Other embodiments of the present application will be apparent to those skilled in the art from consideration of the specification and practice of the application disclosed herein. This application is intended to cover any variations, uses, or adaptations of the invention following, in general, the principles of the application and including such departures from the present disclosure as come within known or customary practice within the art to which the invention pertains. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the application being indicated by the following claims. It will be understood that the present application is not limited to the precise arrangements described above and shown in the drawings and that various modifications and changes may be made without departing from the scope thereof. The scope of the application is limited only by the appended claims.

Claims

1. A design method of a composite material bonding mold is characterized by comprising the following steps:

s1: designing a product bonding surface;

s2: and (5) integrally designing the die.

2. The method for designing a composite material bonding mold according to claim 1, wherein: the step S1 includes:

s11: establishing a gold model of a multi-sample scanning product;

s12: establishing a profile model with rebound compensation;

s13: and designing a mold profile product line and edges.

3. The method for designing a composite material bonding mold according to claim 1, wherein: the step S2 includes:

s21: the fixed frame and the molded surface are flexibly connected;

s22: the mounting design of the heat radiating fins on the windward side, the vacuum joint and the thermocouple;

s23: the design of the product fast-assembling lid and sealing strip.