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CN-117341227-B - High-strength carbon fiber shell forming process for unmanned aerial vehicle body

CN117341227BCN 117341227 BCN117341227 BCN 117341227BCN-117341227-B

Abstract

The application relates to the technical field of unmanned aerial vehicles, in particular to a high-strength carbon fiber shell forming process for an unmanned aerial vehicle body. A high-strength carbon fiber shell forming process for an unmanned aerial vehicle body comprises the following steps of material preparation, cutting, epoxy foaming material coating, material pasting, die assembly, hot press forming, demolding, finishing and finished product preparation, wherein the material preparation is carbon fiber cloth formed by preparing the same carbon fiber direction, the material pasting is to laminate n layers of carbon fiber cloth with epoxy foaming material coated on one side with m layers of carbon fiber cloth respectively, the fiber direction angles of two layers of carbon fiber cloth which are laminated randomly and adjacently are different, n is 3-6, and m is 8-15. The high-strength carbon fiber shell molding process provided by the application can prepare the carbon fiber shell with high strength and excellent appearance quality through simple process steps and optimized material combination, meets the requirements of the unmanned aerial vehicle body on strength and appearance quality, and has lower cost and higher production efficiency.

Inventors

  • DONG JINZHONG

Assignees

  • 厦门市嘉能科技有限公司

Dates

Publication Date
20260505
Application Date
20231122

Claims (7)

  1. 1. The high-strength carbon fiber shell forming process for the unmanned aerial vehicle body is characterized by comprising the following steps of preparing materials, cutting, coating an epoxy foaming material, attaching materials, closing die, hot press forming, demolding, finishing and obtaining a finished product, wherein the materials are carbon fiber cloth formed by preparing the same carbon fiber direction, the attaching materials are formed by attaching n layers of carbon fiber cloth with single-sided coated epoxy foaming material to m layers of carbon fiber cloth respectively, the fiber direction angles of any two adjacent carbon fiber cloth layers are different, n is 3-6, and m is 8-15; The epoxy foaming material comprises a component A and a component B, wherein the mass ratio (1-3) of the component A to the component B is 1, the component A comprises, by mass, 80-85 parts of bisphenol A epoxy resin E-51, 3-5 parts of reactive diluent, 0.5-1 part of coupling agent, 5-8 parts of modified thermal expansion microsphere and 0.5-1 part of foaming agent, and the component B comprises, by mass, 85-90 parts of amine curing agent and 10-15 parts of accelerator; the coupling agent is a composition of N- (beta-aminoethyl) -gamma-aminopropyl trimethyl (ethoxysilane, gamma- (methacryloyloxy) propyl trimethoxysilane and gamma-diethylenetriamine propylene triethoxysilane according to the mass ratio of 3:1-3:4-6; The preparation method of the modified thermal expansion microsphere comprises the steps of mixing 10 parts by mass of vinyl triethoxysilane, 100 parts by mass of ethanol and 200 parts by mass of water, adding 200-250 parts by mass of thermal expansion microsphere, fully stirring, heating to 50 ℃, refluxing for 50min, carrying out suction filtration on the treated thermal expansion microsphere, drying, crushing, grinding and sieving to obtain the modified thermal expansion microsphere with the particle size of 10-25 mu m.
  2. 2. The high-strength carbon fiber shell forming process for the unmanned aerial vehicle according to claim 1, wherein the hot press forming process parameters are that the temperature is 145-155 ℃, the forming pressure is 100-150kg/cm 2 , and the time is 1-2h.
  3. 3. The process for forming a high strength carbon fiber shell for an unmanned aerial vehicle according to claim 1, wherein the reactive diluent is one or more of propylene oxide propylene ether, butyl glycidyl ether, and glycerol epoxy resin.
  4. 4. The process for forming a high-strength carbon fiber shell for an unmanned aerial vehicle according to claim 1, wherein the average particle diameter of the modified thermal expansion microspheres is 10-25 μm, the initial foaming temperature of the modified thermal expansion microspheres is 105-115 ℃, and the maximum foaming temperature of the modified thermal expansion microspheres is 145-155 ℃.
  5. 5. The process for forming a high-strength carbon fiber shell for an unmanned aerial vehicle according to claim 1, wherein the foaming agent is one of azodiisovaleronitrile, azodicarbonamide and N, N-dinitroso pentamethylene tetramine.
  6. 6. The high-strength carbon fiber shell forming process for the unmanned aerial vehicle according to claim 1, wherein the amine curing agent is one of 1, 6-hexamethylenediamine, isophorone diamine and 1, 3-cyclohexyldimethylamine, and the accelerator is one of 2-phenylimidazole, 2-ethyl-4-methylimidazole and diethylenetriamine.
  7. 7. The process for forming the high-strength carbon fiber shell for the unmanned aerial vehicle according to claim 1, wherein the preparation method of the epoxy foaming material comprises the following steps of: S101, preparing a component A, namely adding bisphenol A epoxy resin E-51 into a reaction kettle according to the parts by weight, heating to 50 ℃, adding an active diluent, a coupling agent, modified thermal expansion microspheres and a foaming agent, stirring for 1-2 hours, uniformly mixing, and cooling to obtain the component A; S102, preparing the component B, namely adding an amine curing agent into a reaction kettle according to the parts by weight, keeping the temperature of the reaction kettle at 40 ℃, adding an accelerator, stirring for 1-2 hours, uniformly mixing, and standing to obtain the component B; s103, uniformly mixing the components A, B according to the mass ratio (1-3): 1 to obtain the epoxy foaming material, and coating one side of the epoxy foaming material on the surface of the carbon fiber cloth.

Description

High-strength carbon fiber shell forming process for unmanned aerial vehicle body Technical Field The application relates to the technical field of unmanned aerial vehicles, in particular to a high-strength carbon fiber shell forming process for an unmanned aerial vehicle body. Background With the continuous development of unmanned aerial vehicle technology, carbon fiber is used as an important material in unmanned aerial vehicle body structure, and the application of the carbon fiber in unmanned aerial vehicle body structure is gradually increased. The carbon fiber has the advantages of light weight, high strength, corrosion resistance, high rigidity, electromagnetic transparency and the like, and brings remarkable improvement to the performance and application field of the unmanned aerial vehicle. The carbon fiber single-shell structure means that main parts of an unmanned aerial vehicle such as a fuselage, wings, a tail wing and the like are all formed by an integral carbon fiber shell. The structure has the advantages of simplicity, high strength, low manufacturing cost and the like. Because need not too many connecting pieces and welding, single shell structure can improve unmanned aerial vehicle's structural stability for the flight performance is more reliable. However, the design and manufacture of the structure type are relatively complex, a carbon fiber cloth wet hand lay-up forming process is mainly adopted, and the defects of insufficient strength and insufficient appearance of the shell of the unmanned aerial vehicle exist. Therefore, there is a need to provide a novel high-strength carbon fiber shell molding process for unmanned aerial vehicle fuselages to solve the above-mentioned problems. Disclosure of Invention In order to solve the problems, the application provides a high-strength carbon fiber shell forming process for an unmanned aerial vehicle body, wherein the fiber direction angles of two layers of carbon fiber cloth which are arbitrarily and adjacently attached are different, so that the formed carbon fiber cloth is bonded by hot melting during hot press forming, the strength of the formed carbon fiber material is higher, an epoxy foaming material is arranged between the carbon fiber cloth layers, and during hot press forming, modified thermal expansion microspheres in the epoxy foaming material are heated to expand and the epoxy foaming material is foamed and swelled, so that the carbon fiber cloth can be supported, the formed carbon fiber material can be tightly matched with a cavity of a die, and the appearance quality of a finally formed workpiece is improved. The technical scheme is as follows: A high-strength carbon fiber shell forming process for an unmanned aerial vehicle body comprises the following steps of material preparation, cutting, epoxy foaming material coating, material pasting, die assembly, hot press forming, demolding, finishing and finished product preparation, wherein the material preparation is carbon fiber cloth formed by preparing the same carbon fiber direction, the material pasting is to laminate n layers of carbon fiber cloth with epoxy foaming material coated on one side with m layers of carbon fiber cloth respectively, the fiber direction angles of two layers of carbon fiber cloth which are laminated randomly and adjacently are different, n is 3-6, and m is 8-15. By adopting the technical scheme, the preparation method comprises the step of preparing carbon fiber cloth consisting of the same carbon fiber direction. The function of this step is to provide the carbon fiber material for the subsequent step. Cutting, namely cutting the carbon fiber cloth to adapt to the shape and the size of the unmanned aerial vehicle body. The function of this step is to cut the carbon fiber cloth into the desired shape and size. Coating epoxy foaming material, namely coating epoxy foaming material on part of the carbon fiber cloth. The function of this step is to provide a foamed layer for the carbon fiber cloth and to form a stronger carbon fiber material in a subsequent step. And (3) pasting n layers of carbon fiber cloth with single-sided epoxy foaming material coating and m layers of carbon fiber cloth respectively. The fiber direction angles of any two layers of adjacent carbon fiber cloth are different, n is 3-6, and m is 8-15. The function of this step is to form a multi-layer structure of carbon fiber layers, increasing the strength and stability of the fuselage. And (3) die assembly, namely placing the bonded carbon fiber cloth into a die for molding. The step has the effect of enabling the carbon fiber cloth to be tightly matched with the cavity of the die, and ensuring the shape and the size of the final finished product to be accurate. And (5) hot-press molding, namely hot-press molding the carbon fiber cloth in the die. The function of the step is to make the carbon fiber material stronger and improve the strength and durability through hot melt bonding. An