Carbon fiber unmanned aerial vehicle component forming process

Abstract

The application discloses a carbon fiber unmanned aerial vehicle part forming process and belongs to the unmanned aerial vehicle forming technical field, and comprises the following steps: taking a heated shrinkage polymer latex air bag matched with the shape of an unmanned aerial vehicle part as a mold core; carbon fiber prepreg is laid on the surface of the mold core through a multi-angle and multi-layer laying process to obtain a preformed part; the laying process comprises the following steps: sequentially laying a first carbon cloth layer, a second carbon cloth layer, a third carbon cloth layer, a fourth carbon cloth layer, a fifth carbon cloth layer and a sixth carbon cloth layer from inside to outside; the preformed part is formed by a hot press, and after the mold core is removed, a carbon fiber unmanned aerial vehicle part crude product is obtained; the carbon fiber unmanned aerial vehicle part crude product is polished and finished to obtain a carbon fiber unmanned aerial vehicle part finished product. The application realizes the stable laying of the multi-layer carbon cloth.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of unmanned aerial vehicle part forming processing, and relates to a carbon fiber unmanned aerial vehicle part forming process. BACKGROUND

[0002] Carbon fiber is a new type of fiber material with a carbon content of more than 95%, high strength, high modulus and high temperature resistance, and is the first among all chemical fibers with high temperature resistance. It is widely used in the fields of aerospace, electric power, new energy and major infrastructure projects. The wide application of carbon fiber not only brings "lightweight" in the application field, but also brings additional effects of "energy saving and emission reduction".

[0003] Carbon fiber can significantly improve the flight performance, load capacity and environmental adaptability of unmanned aerial vehicles due to its excellent performance, and is often used to prepare landing gear, arms and other parts of unmanned aerial vehicles. In the manufacturing process of unmanned aerial vehicles, the application of carbon fiber is usually combined with integrated forming technology. Integrated forming technology is a technology in which multiple layers of carbon fiber cloth are covered on a preform model, and then through curing, forming and heat treatment steps, the carbon fiber cloth is tightly combined with the model to finally form the frame structure of the unmanned aerial vehicle. However, due to the integration of multiple layers of carbon cloth, internal stress concentration or mutual constraint during shrinkage of each layer of resin during the curing stage is easily caused, resulting in uneven shrinkage, deformation, cracks, bubbles, uneven surface, poor finish and other common defects, and a high rate of defective products in the production process. SUMMARY

[0004] The purpose of the present application is to provide a carbon fiber unmanned aerial vehicle part forming process that solves the above problems.

[0005] The technical scheme adopted by the present application is as follows:

[0006] A carbon fiber unmanned aerial vehicle part forming process, comprising the following steps:

[0007] S1, using a heated and retracted polymer latex air bag matching the shape of the unmanned aerial vehicle part as a mold core;

[0008] S2, laying carbon fiber prepreg on the surface of the mold core through a multi-angle and multi-layer laying process to obtain a preform; the multi-angle and multi-layer laying process comprises the following steps: laying a first carbon cloth layer, a second carbon cloth layer, a third carbon cloth layer, a fourth carbon cloth layer, a fifth carbon cloth layer and a sixth carbon cloth layer in sequence from inside to outside;

[0009] The first carbon cloth layer and the sixth carbon cloth layer are both composed of 3K twill-200 carbon fiber prepreg;

[0010] The second carbon cloth layer and the fifth carbon cloth layer are both composed of ±C45°-150 carbon fiber prepreg;

[0011] The third carbon cloth layer is composed of C0°-150 carbon fiber prepreg;

[0012] The fourth carbon cloth layer is composed of C90°-150 carbon fiber prepreg;

[0013] S3, hot pressing the preform on a molding machine, and after the mold core is removed, a carbon fiber unmanned aerial vehicle part crude product is obtained;

[0014] S4, polishing and finishing the carbon fiber unmanned aerial vehicle part crude product to obtain a carbon fiber unmanned aerial vehicle part finished product.

[0015] In the present application, the first carbon cloth layer, the second carbon cloth layer, the third carbon cloth layer, the fourth carbon cloth layer, the fifth carbon cloth layer, and the sixth carbon cloth layer are continuously transitioned between adjacent carbon cloths, achieving smooth and stable laying of the multiple layers of carbon cloth, and no significant pores appear between adjacent layers.

[0016] Further, the fiber direction in the ±C45°-150 carbon fiber prepreg is arranged in two directions of 45° and -45°.

[0017] Further, the unmanned aerial vehicle part is a boom or a landing gear.

[0018] Further, the 3K twill-200 carbon fiber prepreg, the ±C45°-150 carbon fiber prepreg, the C0°-150 carbon fiber prepreg, and the C90°-150 carbon fiber prepreg are all obtained by impregnation treatment with the same resin composition.

[0019] Further, the resin composition is composed of resin slurry and a curing agent; the resin slurry is prepared from the following components in parts by weight: 5.5-7.5 parts of a ZnO@C composite derived from a spiro orthocarbonate monomer modified MOF, 30-35 parts of a bisphenol A epoxy resin, 35-40 parts of a bisphenol F epoxy resin, 8-10 parts of an epoxy diluent, 1-2 parts of a polyether modified polydimethylsiloxane dispersant, and an initiator; wherein the amount of the curing agent is 50% of the total amount of the bisphenol A epoxy resin and the bisphenol F epoxy resin; and the amount of the initiator is 0.8% of the mass of the ZnO@C composite derived from the spiro orthocarbonate monomer modified MOF.

[0020] In order to adapt to the multi-layer and multi-angle carbon cloth, avoid the uneven shrinkage stress between the multi-layer carbon cloth due to the thermal shrinkage of the epoxy resin in the heating and curing process, and the deformation phenomenon such as delamination and warping occurs; the spiro orthocarbonate expansion monomer is introduced into the resin to offset the thermal shrinkage of the epoxy resin; in the introduction process of the spiro orthocarbonate expansion monomer, the MOF derived ZnO@C composite is used as the carrier of the spiro orthocarbonate expansion monomer, and the porous structure thereof is utilized to inhibit the expansion rate of the expansion monomer to a certain extent and maintain the entire resin system in a relatively balanced state; because, the obvious shrinkage or expansion of the entire resin composition during curing will affect the uneven change of the interlayer flow, and in the actual application process, although the epoxy resin will shrink due to heating, the shrinkage rate of the epoxy resin is not high, and in general cases, it is lower than the expansion rate of the spiro orthocarbonate expansion monomer, therefore, the application wants to use the MOF derived ZnO@C composite as the carrier of the spiro orthocarbonate expansion monomer to inhibit the expansion degree of the expansion monomer, avoid the phenomenon that the resin composition will obviously expand during the curing process, and help to maintain the balance of the shrinkage and expansion of the entire resin system. In addition, the MOF derived ZnO@C composite has stable performance and certain thermal conductivity, which can not only enhance the mechanical properties of the resin on the basis of balancing the resin shrinkage, but also help to uniformly transfer heat during curing and reduce the stress caused by temperature gradient.

[0021] Further, the spiro orthocarbonate expansion monomer modified MOF derived ZnO@C composite is prepared by the following method:

[0022] The MOF-74(Zn) precursor is placed in a tube furnace, calcined under argon protection, and cooled to obtain the MOF derived ZnO@C composite; the MOF derived ZnO@C composite is dispersed in toluene, stirred uniformly, then 3-aminopropyltriethoxysilane and glacial acetic acid are added, heated and reacted, filtered to obtain the aminated MOF derived ZnO@C composite;

[0023] The spiro orthocarbonate expansion monomer and 3-glycidyl ether propyltrimethoxysilane are heated and reacted under the catalysis of dibutyltin dilaurate to obtain an intermediate; the aminated ZnO@C composite is dispersed in anhydrous toluene, the intermediate and triethylamine are added, heated and reacted, filtered, washed and dried to obtain the spiro orthocarbonate expansion monomer modified MOF derived ZnO@C composite; wherein the spiro orthocarbonate expansion monomer is 3,9-dihydroxymethyl-3',9'-diethyl-1,5,7,11-tetraoxaspiro[5,5]undecane.

[0024] Further, the epoxy diluent is allyl glycidyl ether AGE.

[0025] Further, the curing agent is methyl hexahydrophthalic anhydride, and the initiator is triflic anhydride initiator.

[0026] Further, the resin composition is prepared by the following method: mixing bisphenol A epoxy resin, bisphenol F epoxy resin and epoxy diluent, mechanically stirring at room temperature for 15-20 minutes to obtain a uniform resin base liquid; adding polyether modified polydimethylsiloxane dispersant and spiro orthocarbonate expansion monomer modified MOF derived ZnO@C composite into the resin base liquid, transferring to a high-speed dispersion machine, and high-speed shearing dispersion at room temperature for 30-45 minutes to obtain a premix slurry; adding initiator triflic anhydride into the premix slurry, and continuing to stir at room temperature for 10-15 minutes to obtain a resin slurry; before use, preheating the resin slurry to 45-50 DEG C, then adding a curing agent, stirring and defoaming to obtain the resin composition.

[0027] Further, the preform is formed on a hot press in step S3, the temperature is 145-150 DEG C, and after the mold core is removed, a carbon fiber unmanned aerial vehicle part crude product is obtained.

[0028] Therefore, the present application has the following beneficial effects:

[0029] 1. The angle transition between adjacent carbon cloths in the first carbon cloth layer, the second carbon cloth layer, the third carbon cloth layer, the fourth carbon cloth layer, the fifth carbon cloth layer and the sixth carbon cloth layer in the present application is continuous, the laying of the multiple layers of carbon cloths is flat and stable, there is no significant gap between adjacent layers, the product after forming has no appearance defects and achieves the characteristics of light weight and high strength;

[0030] 2. The present application uses a high polymer latex air bag that shrinks under heat as a mold core, during the heating forming and curing process, the mold core will shrink, the volume will decrease, and the mold core will be separated from the formed product, when demolding, the mold core can be directly pulled out, the demolding is simple, and the product appearance will not be deformed or abraded during the demolding process;

[0031] 3. In order to adapt to the multiple layers and multiple angles of carbon cloths, and avoid uneven shrinkage stress between the multiple layers of carbon cloths due to the thermal shrinkage of the epoxy resin during the heating and curing process, and avoid deformation phenomena such as delamination and warping, a spiro orthocarbonate expansion monomer is introduced into the resin to offset the thermal shrinkage of the epoxy resin;

[0032] 4. The MOF derived ZnO@C composite is used as a carrier of the spiro orthocarbonate expansion monomer, which plays a role in uniform heating and mechanical property enhancement of the resin on the basis of maintaining the shrinkage and expansion balance of the entire resin system. DETAILED DESCRIPTION

[0033] In order to make the objectives, technical solutions and advantages of the present application clearer, the present application will be further described in detail below with reference to the embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and not to limit the present application, that is, the described embodiments are only a part of the embodiments of the present application, but not all the embodiments. The components of the embodiments of the present application described and shown herein can be arranged and designed in various different configurations.

[0034] Therefore, the following detailed description of the embodiments of the present application provided is not intended to limit the scope of the claimed present application, but only represents selected embodiments of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative work are within the scope of protection of the present application.

[0035] It should be noted that the relational terms such as "first" and "second" and the like are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply that there is any such actual relationship or order between these entities or operations. Moreover, the terms "comprising", "including" or any other variant thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus including a series of elements includes not only those elements, but also other elements not explicitly listed or inherent to such a process, method, article or apparatus. Without more limitations, the element defined by the statement "comprising a" does not exclude the presence of additional identical elements in the process, method, article or apparatus including the element.

[0036] The features and performances of the present application will be further described in detail below with reference to the embodiments.

[0037] The present application is a carbon fiber unmanned aerial vehicle part forming process, comprising the following steps:

[0038] S1, using a heated and retracted polymer latex air bag matching the shape of the unmanned aerial vehicle part as a mold core;

[0039] S2, laying carbon fiber prepreg on the surface of the mold core through a multi-angle and multi-layer laying process to obtain a preformed part; the multi-angle and multi-layer laying process comprises the following steps: laying a first carbon cloth layer, a second carbon cloth layer, a third carbon cloth layer, a fourth carbon cloth layer, a fifth carbon cloth layer and a sixth carbon cloth layer in sequence from inside to outside;

[0040] The first carbon cloth layer and the sixth carbon cloth layer are both composed of 3K twill-200 carbon fiber prepreg;

[0041] The second carbon cloth layer and the fifth carbon cloth layer are both composed of ±C45°-150 carbon fiber prepreg; the fiber direction in the ±C45°-150 carbon fiber prepreg is arranged in the 45° and -45° directions;

[0042] The third carbon cloth layer is composed of C0°-150 carbon fiber prepreg;

[0043] The fourth carbon cloth layer is composed of C90°-150 carbon fiber prepreg;

[0044] S3, hot pressing of the preform in a molding machine, after removing the mold core, a carbon fiber unmanned aerial vehicle part crude product is obtained;

[0045] S4, polishing and finishing the carbon fiber unmanned aerial vehicle part crude product to obtain a carbon fiber unmanned aerial vehicle part finished product.

[0046] In the following examples, the unmanned aerial vehicle part is an arm or a landing gear.

[0047] In the following examples, the 3K twill-200 carbon fiber prepreg, ±C45°-150 carbon fiber prepreg, C0°-150 carbon fiber prepreg, and C90°-150 carbon fiber prepreg are prepared by impregnation with the same resin composition.

[0048] In the following examples, the resin composition is composed of a resin slurry and a curing agent; the resin slurry is prepared from the following components in parts by weight: 5.5-7.5 parts of a spiro ortho carbonate expansion monomer modified MOF derived ZnO@C composite, 30-35 parts of a bisphenol A epoxy resin, 35-40 parts of a bisphenol F epoxy resin, 8-10 parts of an epoxy diluent, 1-2 parts of a polyether modified polydimethylsiloxane dispersant, and an initiator; wherein the amount of the curing agent is 50% of the total amount of the bisphenol A epoxy resin and the bisphenol F epoxy resin; the amount of the initiator is 0.8% of the mass of the spiro ortho carbonate expansion monomer modified MOF derived ZnO@C composite.

[0049] In the following examples, the spiro ortho carbonate expansion monomer modified MOF derived ZnO@C composite is prepared by the following method:

[0050] The MOF-74(Zn) precursor was placed in a tube furnace, and was raised to 200°C at a rate of 1°C / min under argon protection, and was kept for 1 h; then was raised to 350°C at a rate of 0.5°C / min, and was kept for 2 h; finally was raised to 450°C at a rate of 2°C / min, and was kept for 4 h, and was cooled to obtain a MOF-derived ZnO@C composite; 1 g of the MOF-derived ZnO@C composite was dispersed in 50 mL of toluene, and 2 ml of 3-aminopropyltriethoxysilane and 0.1 mL of glacial acetic acid were added after uniform stirring, and was refluxed at 110°C for 8 h, and was filtered to obtain an aminated MOF-derived ZnO@C composite;

[0051] 1 g of spiroorthocarbonate dilatant monomer (3,9-dihydroxymethyl-3',9'-diethyl-1,5,7,11-tetraoxaspiro[5,5]undecane) was reacted with 1.2 g of 3-glycidyloxypropyltrimethoxysilane at 80°C for 6 h under the catalysis of 0.05 g of dibutyltin dilaurate to obtain an intermediate reactant (without separation, directly for the next step); 1 g of the aminated MOF-derived ZnO@C composite was dispersed in 30 mL of anhydrous toluene, and the intermediate reactant and 0.1 g of triethylamine were added, and was stirred at 80°C for 12 h, and was filtered, washed and dried to obtain a spiroorthocarbonate dilatant monomer modified MOF-derived ZnO@C composite; wherein the spiroorthocarbonate dilatant monomer is 3,9-dihydroxymethyl-3',9'-diethyl-1,5,7,11-tetraoxaspiro[5,5]undecane.

[0052] In the following examples, the epoxy diluent is allyl glycidyl ether AGE.

[0053] In the following examples, the curing agent is methylhexahydrophthalic anhydride, and the initiator is triflic anhydride initiator.

[0054] In the following examples, the resin composition is prepared by the following method: mixing bisphenol A epoxy resin (liquid), bisphenol F epoxy resin (liquid) and epoxy diluent, mechanically stirring at room temperature at a speed of 500-800 rpm for 15-20 minutes to obtain a uniform resin base liquid; adding polyether modified polydimethylsiloxane dispersant and spiro orthocarbonate expansion monomer modified MOF derived ZnO@C composite to the resin base liquid, transferring to a high-speed dispersion machine, high-speed shearing dispersion at room temperature at a speed of 3000-3500 rpm for 30-45 minutes until the composite is uniformly dispersed and the system has no visible agglomerates, to obtain a premix slurry; adding initiator triflic anhydride to the premix slurry, continuing to stir at room temperature at a speed of 500-800 rpm for 10-15 minutes to obtain a resin slurry; before use, preheat the resin slurry to 45-50°C (preferably 50°C in actual use), then add the curing agent, stir to degas, and obtain the resin composition, which is used for impregnation treatment in the process of preparing carbon fiber prepreg.

[0055] In the following examples, the preform is formed by hot pressing in step S3 at a temperature of 145-150°C (preferably 150°C in actual preparation), and after the mold core is removed, a carbon fiber unmanned aerial vehicle part is obtained.

[0056] Example 1

[0057] The carbon fiber unmanned aerial vehicle part forming process provided by the preferred embodiment of the present application takes the arm as the processing object, and includes the following steps:

[0058] S1, using a heated and retracted polymer latex air bag matching the shape of the unmanned aerial vehicle part as a mold core;

[0059] S2, laying carbon fiber prepreg on the surface of the mold core by a multi-angle and multi-layer laying process to obtain a preform; the multi-angle and multi-layer laying process includes the following steps: laying a first carbon cloth layer, a second carbon cloth layer, a third carbon cloth layer, a fourth carbon cloth layer, a fifth carbon cloth layer, and a sixth carbon cloth layer from inside to outside; (the number of sheets used for each layer is determined according to the surface area of the processed part, and the processed part is completely covered by a single layer; the thickness parameters of the following specifications of carbon cloth used in this embodiment are 200g / m 2 , the thickness of 0.25mm / single layer, 150g / m 2 , the thickness of 0.15mm / single layer, and 3K twill, and the carbon cloth other than 3K twill uses T700);

[0060] The first carbon cloth layer and the sixth carbon cloth layer are both composed of 3K twill-200 carbon fiber prepreg; “-200” is the grammage, and “-150” has the same meaning below;

[0061] The second carbon cloth layer and the fifth carbon cloth layer are both composed of ±C45°-150 carbon fiber prepreg; the fiber direction in the ±C45°-150 carbon fiber prepreg is arranged in an interwoven manner in two directions of 45° and -45°;

[0062] The third carbon cloth layer is composed of C0°-150 carbon fiber prepreg;

[0063] The fourth carbon cloth layer is composed of C90°-150 carbon fiber prepreg;

[0064] S3, hot pressing of the preform in a molding machine at a temperature of 150°C, and after removal of the mold core, a carbon fiber unmanned aerial vehicle part crude product is obtained;

[0065] S4, polishing and finishing of the carbon fiber unmanned aerial vehicle part crude product to obtain a carbon fiber unmanned aerial vehicle part finished product;

[0066] The 3K twill-200 carbon fiber prepreg, ±C45°-150 carbon fiber prepreg, C0°-150 carbon fiber prepreg, and C90°-150 carbon fiber prepreg are all obtained by impregnation with the same resin composition, and the resin composition for impregnation treatment is composed of a resin slurry and a curing agent (methyl hexahydrophthalic anhydride). The resin slurry is prepared from the following components in parts by weight: 5.5 parts of spiro ortho carbon monomer modified MOF derived ZnO@C composite, 30 parts of bisphenol A epoxy resin, 35 parts of bisphenol F epoxy resin, 8 parts of epoxy diluent (allyl glycidyl ether AGE), 1 part of polyether modified polydimethylsiloxane dispersant, and initiator (triflic anhydride initiator). The amount of the curing agent is 50% of the total mass of the bisphenol A epoxy resin and the bisphenol F epoxy resin. The amount of the initiator is 0.8% of the mass of the spiro ortho carbon monomer modified MOF derived ZnO@C composite. The resin composition is prepared by the following method: mixing the bisphenol A epoxy resin, the bisphenol F epoxy resin, and the epoxy diluent, and mechanically stirring at a speed of 800 rpm for 15 minutes at room temperature to obtain a uniform resin base liquid; adding the polyether modified polydimethylsiloxane dispersant and the spiro ortho carbon monomer modified MOF derived ZnO@C composite to the resin base liquid, and transferring to a high-speed disperser for high-speed shearing dispersion at a speed of 3500 rpm for 30 minutes at room temperature until the composite is uniformly dispersed and there are no visible agglomerates in the system to obtain a premix slurry; adding the initiator triflic anhydride to the premix slurry, and continuing to stir at a speed of 500 rpm for 15 minutes at room temperature to obtain a resin slurry; before use, preheat the resin slurry to 50°C, then add the curing agent, and stir to degas to obtain the resin composition for impregnation, which is used for impregnation treatment of the corresponding carbon fiber to obtain carbon fiber prepreg.

[0067] Example 2

[0068] This embodiment is based on Example 1, and differs from Example 1 in that the resin composition for impregnation treatment in this embodiment is composed of a resin slurry and a curing agent (methyl hexahydrophthalic anhydride), and the resin slurry is prepared from the following components in parts by weight: 6.5 parts of spiro ortho carbonate dilatant monomer modified MOF derived ZnO@C composite, 33 parts of bisphenol A epoxy resin, 38 parts of bisphenol F epoxy resin, 9 parts of epoxy diluent (allyl glycidyl ether AGE), 1.5 parts of polyether modified polydimethylsiloxane dispersant, initiator (trifluoromethanesulfonic anhydride initiator); wherein the amount of the curing agent is 50% of the total amount of bisphenol A epoxy resin and bisphenol F epoxy resin; the amount of the initiator is 0.8% of the mass of the spiro ortho carbonate dilatant monomer modified MOF derived ZnO@C composite; the rest is consistent with Example 1. The physical object before step S2 of laying in this embodiment (heating forming) is flat, and there is no obvious abnormal phenomenon such as edge lifting and bulging.

[0069] Example 3

[0070] This embodiment is based on Example 1, and differs from Example 1 in that the resin composition for impregnation treatment in this embodiment is composed of a resin slurry and a curing agent (methyl hexahydrophthalic anhydride), and the resin slurry is prepared from the following components in parts by weight: 6.5 parts of spiro ortho carbonate dilatant monomer modified MOF derived ZnO@C composite, 33 parts of bisphenol A epoxy resin, 38 parts of bisphenol F epoxy resin, 9 parts of epoxy diluent (allyl glycidyl ether AGE), 1.5 parts of polyether modified polydimethylsiloxane dispersant, initiator (trifluoromethanesulfonic anhydride initiator); wherein the amount of the curing agent is 50% of the total amount of bisphenol A epoxy resin and bisphenol F epoxy resin; the amount of the initiator is 0.8% of the mass of the spiro ortho carbonate dilatant monomer modified MOF derived ZnO@C composite; the rest is consistent with Example 1. The physical object before step S2 of laying in this embodiment (heating forming) is flat, and there is no obvious abnormal phenomenon such as edge lifting and bulging.

[0071] Comparative Example 1

[0072] Based on Example 2, and differing from Example 2, the resin composition for impregnation treatment in this comparative example is composed of a resin slurry and a curing agent (methyl hexahydrophthalic anhydride), and the resin slurry is composed of 33 parts of bisphenol A epoxy resin, 38 parts of bisphenol F epoxy resin, and 9 parts of epoxy diluent (allyl glycidyl ether AGE), wherein the amount of the curing agent is 50% of the total amount of bisphenol A epoxy resin and bisphenol F epoxy resin. The preparation method, carbon cloth laying process, etc. refer to Example 1; the resin used in this comparative example is a commonly used epoxy resin, and the carbon fiber prepreg used in this comparative example is equivalent to the existing carbon fiber prepreg.

[0073] Comparative Example 2

[0074] Based on example 2, different from example 2, the resin composition for impregnation treatment in the present comparative example is composed of resin slurry and curing agent (methyl hexahydrophthalic anhydride), the resin slurry is prepared from the following components in parts by weight: 3.2 parts of spiro ortho carbonate expansion monomer, 33 parts of bisphenol A epoxy resin, 38 parts of bisphenol F epoxy resin, 9 parts of epoxy diluent (allyl glycidyl ether AGE), 1.5 parts of polyether modified polydimethylsiloxane dispersant, initiator (triflic anhydride initiator); wherein the amount of curing agent is 50% of the total amount of bisphenol A epoxy resin and bisphenol F epoxy resin; the amount of initiator is 0.8% of the mass of spiro ortho carbonate expansion monomer; the rest is consistent with example 2; the spiro ortho carbonate expansion monomer in the present comparative example does not use MOF derived ZnO@C composite as carrier, but is used directly, which is equivalent to using spiro ortho carbonate expansion monomer to modify the epoxy resin mixture; the present comparative example does not add MOF derived ZnO@C composite, the amount of spiro ortho carbonate expansion monomer is adjusted accordingly, and the preparation method is also adjusted accordingly, which does not include the preparation method of spiro ortho carbonate expansion monomer modified MOF derived ZnO@C composite.

[0075] Comparative example 3

[0076] Based on example 2, different from example 2, the resin composition for impregnation treatment in the present comparative example is composed of resin slurry and curing agent (methyl hexahydrophthalic anhydride), the resin slurry is prepared from the following components in parts by weight: 3.2 parts of spiro ortho carbonate expansion monomer, 33 parts of bisphenol A epoxy resin, 38 parts of bisphenol F epoxy resin, 9 parts of epoxy diluent (allyl glycidyl ether AGE), 1.5 parts of polyether modified polydimethylsiloxane dispersant, initiator (triflic anhydride initiator); wherein the amount of curing agent is 50% of the total amount of bisphenol A epoxy resin and bisphenol F epoxy resin; the present comparative example does not contain spiro ortho carbonate expansion monomer and initiator in the resin composition, and the rest is consistent with example 2.

[0077] Comparative example 4

[0078] Based on example 2, different from example 2, the present comparative example does not include initiator (triflic anhydride initiator) in the resin composition for impregnation treatment, and the rest is consistent with example 2.

[0079] Comparative example 5

[0080] Based on example 2, different from example 2, the laying process in the present comparative example lays the second carbon cloth layer, the third carbon cloth layer, the fourth carbon cloth layer, the fifth carbon cloth layer and the sixth carbon cloth layer from inside to outside, does not lay the first carbon cloth layer, and the second carbon cloth layer is laid first. The rest is consistent with example 2.

[0081] Comparative Example 6

[0082] Based on Example 2, different from Example 2, in the laying process of the present comparative example, the first carbon cloth layer, the third carbon cloth layer, the fourth carbon cloth layer, the fifth carbon cloth layer and the sixth carbon cloth layer are laid from inside to outside in turn, and the second carbon cloth layer is not laid. The rest is consistent with Example 2.

[0083] Comparative Example 7

[0084] Based on Example 2, different from Example 2, in the laying process of the present comparative example, the first carbon cloth layer, the second carbon cloth layer, the fourth carbon cloth layer, the fifth carbon cloth layer and the sixth carbon cloth layer are laid from inside to outside in turn, and the third carbon cloth layer is not laid. The rest is consistent with Example 2.

[0085] Comparative Example 8

[0086] Based on Example 2, different from Example 2, in the laying process of the present comparative example, the first carbon cloth layer, the second carbon cloth layer, the third carbon cloth layer, the fifth carbon cloth layer and the sixth carbon cloth layer are laid from inside to outside in turn, and the fourth carbon cloth layer is not laid. The rest is consistent with Example 2.

[0087] Comparative Example 9

[0088] Based on Example 2, different from Example 2, in the laying process of the present comparative example, the first carbon cloth layer, the second carbon cloth layer, the third carbon cloth layer, the fourth carbon cloth layer and the sixth carbon cloth layer are laid from inside to outside in turn, and the fifth carbon cloth layer is not laid. The rest is consistent with Example 2.

[0089] Comparative Example 10

[0090] Based on Example 2, different from Example 2, in the laying process of the present comparative example, the first carbon cloth layer, the second carbon cloth layer, the third carbon cloth layer, the fourth carbon cloth layer and the fifth carbon cloth layer are laid from inside to outside in turn, and the sixth carbon cloth layer is not laid. The rest is consistent with Example 2.

[0091] Test Example 1

[0092] The appearance characteristics of the carbon fiber unmanned aerial vehicle arm rough products prepared in Examples 1-3 and Comparative Examples 1-10 were detected, whether obvious defects such as deformation, cracks, bubbles and uneven surface appeared or not, and the results are shown in Table 1; wherein the arm rough product prepared in the range of Example 2 can be directly demolded after heating and curing, and the mold core shrinks;

[0093] Table 1 Appearance characteristics of carbon fiber unmanned aerial vehicle arm rough products

[0094] Appearance of carbon fiber unmanned aerial vehicle arm rough product (after heat molding) Example 1 No significant defects such as deformation, cracks, bubbles, surface unevenness Example 2 No significant defects such as deformation, cracks, bubbles, surface unevenness Example 3 No significant defects such as deformation, cracks, bubbles, surface unevenness Comparative Example 1 Partial deformation, fine cracks, and surface unevenness occurred Comparative Example 2 Bulging and surface unevenness occurred Comparative Example 3 Partial warping deformation, fine cracks, and surface unevenness occurred Comparative Example 4 No significant defects such as deformation, cracks, bubbles, surface unevenness Comparative Example 5 Surface unevenness was significant Comparative Example 6 Significant cracks and pores were present Comparative Example 7 Visible twisting deformation Comparative Example 8 Visible bending deformation Comparative Example 9 Visible pores were present Comparative Example 10 Surface unevenness was significant and had a sharp burr feeling

[0095] Compared with the comparative examples, the crude product prepared in the embodiments of the present application has no abnormality on the surface except the edge with the allowable burr and other features that need to be polished; the crude product (unqualified) prepared in Comparative Example 1 has a rough surface, and local cracks and deformation appear; the crude product (unqualified) prepared in Comparative Example 6 has obvious pores.

[0096] Test Example 2

[0097] In Test Examples 1-3, the mechanical properties of the finished carbon fiber unmanned aerial vehicle arm product after fine grinding prepared in Examples 1-3 and Comparative Examples 1-4 and the rejection rate of 100 pieces in batch production are tested, and the results are shown in Table 2.

[0098] Tensile strength test: reference ASTM D3039 standard test method; sample preparation: standard dumbbell-shaped samples (100 mm in length, 12.7 mm in width, and the actual thickness of the finished product) are cut from each finished arm product; equipment: electronic universal testing machine (0.5 level of accuracy); test procedure: the sample is clamped in the wedge-shaped clamp of the testing machine, ensuring that the sample axis is consistent with the loading direction, the loading speed is set to 2 mm / min, the tensile force is applied until the sample breaks, the maximum load is recorded, and the tensile strength is calculated, tensile strength = maximum load / original cross-sectional area of the sample;

[0099] Bending strength test: reference ASTM D790 standard test method; sample preparation: rectangular beam samples (128 mm in length, 12.7 mm in width, and the actual thickness of the finished product) are cut from the finished arm product; equipment: electronic universal testing machine (equipped with a three-point bending clamp); test procedure: the sample is placed on the three-point bending clamp with a support span of 100 mm, the loading speed is set to 1 mm / min, the load is applied at the midpoint of the span, until the sample cracks or breaks, the maximum bending load is recorded, and the bending strength is calculated, bending strength = 3xFxL / (2xbxh 2 (F is the maximum bending load, L is the support span, b is the sample width, and h is the sample thickness);

[0100] Heat resistance test: reference GB / T 1634.2 standard; sample: 10 mm x 10 mm x 5 mm sample is cut from the finished arm product; equipment: heat distortion temperature tester; test procedure: the sample is placed under a temperature rising rate of 3 ℃ / min, a static load of 0.45 MPa is applied, and the temperature at which the heat distortion amount of the sample reaches 0.25 mm, i.e. the heat distortion temperature, is recorded;

[0101] Corrosion resistance: sample: 20mm x 20mm x 5mm sample is cut from finished product arm, the surface is polished flat; test medium: common working environment medium of unmanned aerial vehicle (5% NaCl solution, 0.1mol / L HCl solution, 0.1mol / L NaOH solution); test procedure: immerse the sample in the three kinds of medium completely, take out after room temperature immersion for 72h, observe whether there are corrosion phenomena such as bulge, delamination, discoloration on the surface;

[0102] Density: refer to GB / T 1463-2005 "Fiber Reinforced Plastics Density and Relative Density Test Method", determine by drainage method (immersion method);

[0103] Substandard rate: 100 pieces of arm finished products are produced in batch, the appearance defects (deformation, crack, bubble, uneven surface) are checked one by one, the products with appearance defects are substandard products, and the substandard rate = substandard quantity / 100 x 100%.

[0104] Table 2 Mechanical property detection and substandard rate detection results of finished products

[0105] Tensile strength (MPa) Flexural strength (MPa) Heat resistance Corrosion resistance Density Defective rate Example 1 3450±50 2020±38 ＞300℃ No corrosion was observed in any of the three media 1.5-1.6 g / cm 3 ]] ≤2% Example 2 3680±45 2080±40 ＞300℃ No corrosion was observed in any of the three media 1.5-1.6 g / cm 3 ]] ≤2% Example 3 3520±55 2040±42 ＞300℃ No corrosion was observed in any of the three media 1.5-1.6 g / cm 3 ]] ≤2% Comparative Example 1 2850±60 1650±45 ＞300℃ No corrosion was observed in any of the three media 1.5-1.6 g / cm 3 ]]> ＞15% Comparative Example 2 2050±55 1320±42 ＞300℃ No corrosion was observed in any of the three media 1.5-1.6 g / cm 3 ]] ＞10% Comparative Example 3 2920±58 1720±48 ＞300℃ No corrosion was observed in any of the three media 1.5-1.6 g / cm 3 ]] ＞10% Comparative Example 4 3250±50 1950±36 ＞300℃ No corrosion was observed in any of the three media 1.5-1.6 g / cm3 5-7%

[0106] The molding process of the application is stable, and the substandard rate is low; the unmanned aerial vehicle parts with high strength and light weight can be prepared, and have good corrosion resistance and heat resistance, and are suitable for complex environments such as high temperature. The spiro orthocarbonate expanded monomer modified MOF derived ZnO@C composite in the application can effectively improve the mechanical properties of the product and reduce the defects in the multi-layer lamination process.

[0107] Test example 3

[0108] The shrinkage or expansion rate of the resin composition in test example 2 and comparative examples 1-4 was detected, and the results are shown in Table 3;

[0109] Detection method: refer to standards GB / T 24148.9 and ISO 3521; the volume curing shrinkage rate of the cured resin is calculated according to the following formula: curing shrinkage rate = (1-ρbefore / ρafter) x 100%, wherein: ρbefore is the density of the resin before curing, g / cm 3 ; ρafter is the density of the resin after curing, g / cm 3 ; when the value is positive, it means that the resin shrinks after curing; when the value is negative, it means that the resin expands after curing; the density detection method of the resin is prior art, and the content of the reference standard can be referred to, and will not be described in detail here.

[0110] Table 3 Shrinkage or expansion rate of resin composition

[0111] Example 2 Comparative Example 1 Comparative Example 2 Comparative Example 3 Comparative Example 4 Shrinkage rate -0.1%~0.1% 2.2%-2.5% -1.2%~-1% 1.5%~1.8% 0.4%~0.6%

[0112] The spiro ortho carbonates expansion monomer in the absence of MOF@C support in the present application comparative example 2 has a violent and uncontrolled expansion behavior, with a clear and large expansion during the curing (monitored by real-time volume change), even if there is some shrinkage at the end, with a slight expansion, irreversible damage to the product has already occurred (bumps, unevenness).

[0113] The above description is merely the preferred embodiments of the present application, and is not used to limit the protection scope of the present application. Any modification, equivalent replacement and improvement made by any person skilled in the art within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims

1. A carbon fiber unmanned aerial vehicle component forming process, characterized by: The method comprises the following steps: S1, using a heated and retracted polymer latex air bag matched with the shape of the unmanned aerial vehicle part as a mold core; S2, laying carbon fiber prepreg on the surface of the mold core through a multi-angle and multi-layer laying process to obtain a preform; the multi-angle and multi-layer laying process comprises the following steps: laying a first carbon cloth layer, a second carbon cloth layer, a third carbon cloth layer, a fourth carbon cloth layer, a fifth carbon cloth layer and a sixth carbon cloth layer from inside to outside; The first carbon cloth layer and the sixth carbon cloth layer are both composed of 3K twill-200 carbon fiber prepreg; The second carbon cloth layer and the fifth carbon cloth layer are both composed of ±C45°-150 carbon fiber prepreg; The third carbon cloth layer is composed of C0°-150 carbon fiber prepreg; The fourth carbon cloth layer is composed of C90°-150 carbon fiber prepreg; S3, hot pressing the preform, and removing the mold core to obtain a carbon fiber unmanned aerial vehicle part roughcast; S4, polishing and finishing the carbon fiber unmanned aerial vehicle part roughcast to obtain a carbon fiber unmanned aerial vehicle part finished product; The 3K twill-200 carbon fiber prepreg, ±C45°-150 carbon fiber prepreg, C0°-150 carbon fiber prepreg and C90°-150 carbon fiber prepreg are all obtained through impregnation treatment of the same resin composition; The resin composition is composed of resin slurry and curing agent; the resin slurry is prepared from the following components in parts by weight: 5.5-7.5 parts of MOF-derived ZnO@C composite modified by spiro ortho-carbonate expansion monomer, 30-35 parts of bisphenol A epoxy resin, 35-40 parts of bisphenol F epoxy resin, 8-10 parts of epoxy diluent, 1-2 parts of polyether modified polydimethylsiloxane dispersant, and initiator; wherein the amount of the curing agent is 50% of the total amount of the bisphenol A epoxy resin and the bisphenol F epoxy resin; and the amount of the initiator is 0.8% of the mass of the MOF-derived ZnO@C composite modified by spiro ortho-carbonate expansion monomer.

2. A process for molding carbon fiber unmanned aerial vehicle components according to claim 1, wherein: The fiber direction in the ±C45°-150 carbon fiber prepreg is arranged in the directions of 45° and -45°.

3. A process for molding carbon fiber unmanned aerial vehicle components according to claim 1, wherein: The unmanned aerial vehicle part is a boom or a landing gear.

4. The process for molding carbon fiber unmanned aerial vehicle components of claim 1, wherein: The MOF-derived ZnO@C composite modified by spiro ortho-carbonate expansion monomer is prepared by the following method: The MOF-74(Zn) precursor is placed in a tube furnace and calcined under argon protection, and then cooled to obtain a MOF-derived ZnO@C composite; the MOF-derived ZnO@C composite is dispersed in toluene, stirred uniformly, and then 3-aminopropyltriethoxysilane and glacial acetic acid are added and heated to react, and then filtered to obtain an aminated MOF-derived ZnO@C composite; The spiroorthocarbonate dilatant monomer is reacted with 3-glycidyloxypropyltrimethoxysilane under the catalysis of dibutyltin dilaurate to obtain an intermediate reactant; the aminated ZnO@C composite is dispersed in anhydrous toluene, the intermediate reactant and triethylamine are added, and the reaction is heated; after filtration, washing and drying, the spiroorthocarbonate dilatant monomer modified MOF derived ZnO@C composite is obtained; wherein the spiroorthocarbonate dilatant monomer is 3,9-dihydroxymethyl-3',9'-diethyl-1,5,7,11-tetraoxaspiro[5,5]undecane.

5. The carbon fiber unmanned aerial vehicle component molding process of claim 1, wherein: The epoxy diluent is allyl glycidyl ether AGE.

6. A carbon fiber drone component molding process as claimed in claim 1, wherein: The curing agent is methyl hexahydrophthalic anhydride, and the initiator is triflic anhydride initiator.

7. The carbon fiber unmanned aerial vehicle component molding process of claim 1, wherein: The resin composition is prepared by the following method: mixing bisphenol A epoxy resin, bisphenol F epoxy resin and epoxy diluent, mechanically stirring at room temperature for 15-20 minutes to obtain a uniform resin base liquid; adding polyether modified polydimethylsiloxane dispersant and spiroorthocarbonate dilatant monomer modified MOF derived ZnO@C composite into the resin base liquid, transferring to a high-speed dispersion machine, and high-speed shearing dispersion at room temperature for 30-45 minutes to obtain a premix slurry; adding initiator triflic anhydride into the premix slurry, and continuing to stir at room temperature for 10-15 minutes to obtain a resin slurry; before use, the resin slurry is preheated to 45-50 DEG C, then the curing agent is added, and stirring and defoaming are carried out to obtain the resin composition.

8. The carbon fiber unmanned aerial vehicle component molding process of claim 1, wherein: In step S3, the preform is formed on a hot press, and the temperature is 145-150 DEG C; after removing the mold core, a carbon fiber unmanned aerial vehicle part crude product is obtained.