阅读说明：本技术 一种无机富勒烯碳纤维复合材料无人机螺旋桨的制备方法 (Preparation method of unmanned aerial vehicle propeller made of inorganic fullerene-carbon fiber composite material ) 是由 王南南 朱艳秋 雷原 满泉言 陈丁 于 2020-04-03 设计创作，主要内容包括：本发明公开了一种无机富勒烯碳纤维复合材料无人机螺旋桨的制备方法,属于无人航行器零部件技术领域,本发明通过无机富勒烯的加入可以提高碳纤维复合材料的耐磨性、抗弯强度和抗冲击性能。螺旋桨在碳纤维基体的高强度性能基础上,还具有通过混合无机富勒烯和聚四氟乙烯所加强的耐磨性,抗弯强度以及柔韧性等优点,无机富勒烯增强铝基纳米复合材料具有轻质的特点和极佳的减震性能,以及吸收冲击波的能力,使得其在轻质减震材料和高性能防护材料中具有良好的应用前景,并且制备成本较低,可进行工业化生产,具有较高的实用价值。(The invention discloses a preparation method of an unmanned aerial vehicle propeller made of an inorganic fullerene-carbon fiber composite material, belonging to the technical field of unmanned aerial vehicle parts. The propeller has the advantages of wear resistance, bending strength, flexibility and the like which are enhanced by mixing the inorganic fullerene and the polytetrafluoroethylene on the basis of the high-strength performance of the carbon fiber substrate, the inorganic fullerene reinforced aluminum-based nano composite material has the characteristics of light weight, excellent damping performance and the capability of absorbing shock waves, so that the propeller has good application prospect in light damping materials and high-performance protective materials, and the propeller is low in preparation cost, can be industrially produced and has high practical value.)

1. A preparation method of an unmanned aerial vehicle propeller made of an inorganic fullerene carbon fiber composite material is characterized by comprising the following steps: the method comprises the following steps:

step 1: preparing a matrix, namely preparing the carbon fiber, the polytetrafluoroethylene and the curing agent according to the weight ratio of 2: 1:1, stirring and mixing, adding the mixture into a melting furnace after mixing, continuously heating to 500 ℃, continuously stirring during heating, injecting the melted mixture into a matrix mold by using an injection molding machine after uniformly mixing, opening the matrix mold after the matrix mold is naturally cooled at normal temperature, and taking out the carbon fiber substrate;

step 2: manufacturing a reinforcing material, namely mixing carbon fibers, inorganic fullerene, epoxy resin and an additive in a weight ratio of 1: 0.5: 2: 1, adding the mixture into a magnetic stirrer, heating to 80 ℃, and continuously stirring for 20 minutes during the heating period;

and step 3: adding the mixture stirred by the magnetic stirrer in the step 2 into the bottom of the groove of the propeller mold, so that the stirred mixture is fully soaked at the bottom of the groove of the mold, and the specific gravity of the mixture is ensured to be about 25-30% of the whole propeller, immediately putting the carbon fiber substrate in the step 1 into the propeller mold by using a vacuum chuck, finally adding the mixture accounting for 25-30% of the whole propeller in the step 2, fully soaking the whole propeller mold, closing the mold and carrying out curing treatment after the material is added;

and 4, step 4: opening the mold and taking out the molded propeller when the mold in the step 3 is naturally cooled to room temperature;

and 5: and (5) grinding the edge of the propeller to remove burrs, and polishing the surface of the propeller to finish the preparation.

2. The method for preparing the propeller made of the inorganic fullerene-carbon fiber composite material for the unmanned aerial vehicle according to claim 1, wherein the method comprises the following steps: in the step 1, the injection molding pressure is kept at 15-25MPa during injection molding, and the injection molding temperature is 500 ℃.

3. The method for preparing the propeller made of the inorganic fullerene-carbon fiber composite material for the unmanned aerial vehicle according to claim 1, wherein the method comprises the following steps: the carbon fiber in the step 1 is bagasse-based carbon fiber, and the preparation process of the bagasse-based carbon fiber comprises the following steps: putting bagasse into a beaker filled with a sodium hypochlorite solution with the mass fraction of 5%, soaking for 12 hours, repeatedly filtering until the pH of the filtrate is close to neutral, putting the filtered bagasse into a drying box, and drying for 10 hours at 80 ℃;

the dried bagasse is contacted with an aqueous urea solution in a volume ratio of urea to deionized water of 1:1, soaked for 1h, the soaked bagasse is taken out, placed in a drying box, dried for 10h at 80 ℃, and repeatedly dried for 2-3 times to obtain sized bagasse;

putting the obtained sized bagasse into a vacuum tube furnace, sealing, introducing nitrogen, raising the temperature of the vacuum tube furnace to 400 ℃ at the speed of 5 ℃/min after exhausting air, and maintaining the temperature of the vacuum tube furnace for carbonization for 40min at 400 ℃;

then, the temperature of the vacuum tube furnace is increased to 1200 ℃ at the speed of 5 ℃/min, and the temperature is kept at 1200 ℃ for graphitization for 20min to obtain primary carbon fiber;

and (3) putting the primary carbon fiber into 45 wt% nitric acid water solution, soaking for 30min, taking out, putting into deionized water, rinsing for 2 times, putting the oxidized carbon fiber into a drying oven, and drying for 10h at 80 ℃ to obtain the bagasse-based carbon fiber.

4. The method for preparing the propeller made of the inorganic fullerene-carbon fiber composite material for the unmanned aerial vehicle according to claim 1, wherein the method comprises the following steps: the additive in the step 2 is formed by mixing an anti-aging agent, a flame retardant and a curing agent in the same proportion.

5. The method for preparing the propeller made of the inorganic fullerene-carbon fiber composite material for the unmanned aerial vehicle according to claim 1, wherein the method comprises the following steps: and the curing treatment in the step 3 is to preserve heat of the propeller mould for 1-3 hours by using an intermediate frequency heating furnace, wherein the heat preservation temperature is 180 ℃.

6. The method for preparing the propeller made of the inorganic fullerene-carbon fiber composite material for the unmanned aerial vehicle according to claim 1, wherein the method comprises the following steps: the inorganic fullerene in the step 2 is an aluminum-based nano composite fullerene material, and the synthesis process of the aluminum-based nano composite fullerene material is as follows: putting the inorganic fullerene nano-particles IF-WS2 into ethanol and dispersing by using an ultrasonic probe, mixing the inorganic fullerene nano-particles IF-WS2 and the ethanol mixture with vigorous stirring at 80-90 ℃ with Al powder until all ethanol is evaporated, drying in an oven at 110-130 ℃ for 11-13 hours to obtain a primary mixture sample, extruding the sample by a fused deposition modeling 3D printing technology, and controlling the temperature of a printing extrusion head to be 560-670 ℃ to complete synthesis.

7. The method for preparing the propeller made of the inorganic fullerene-carbon fiber composite material for the unmanned aerial vehicle according to claim 6, wherein the method comprises the following steps: the time for dispersing the ultrasonic probe is 0.8-1.2 hours, the ultrasonic frequency is 80-90 KHz, and in the fused deposition modeling 3D printing process, hot pressing is carried out for 30 minutes under the conditions that the hot pressing temperature is 560-650 ℃, the pressure is 75-85 KN, and the atmosphere is N2.

The method for preparing the propeller made of the inorganic fullerene-carbon fiber composite material for the unmanned aerial vehicle according to claim 6, wherein the method comprises the following steps: heating the mixture of the inorganic fullerene nano-particles IF-WS2 and ethanol to 80 ℃, adding aluminum powder particles for mixing, rapidly stirring until the ethanol is completely volatilized to prepare a mixed solid sample of 20-30 wt% IF-WS2 and the aluminum powder, and then placing the mixed solid sample in an oven at 120 ℃ for drying for 12 hours.

Technical Field

The invention relates to the technical field of unmanned aircraft parts, in particular to a preparation method of an unmanned aerial vehicle propeller made of an inorganic fullerene carbon fiber composite material.

Background

The Unmanned Aerial Vehicle (UAV) has the advantages of flexibility, quick response, high safety, unmanned flight, low operation requirement and the like, and is widely applied to the fields of electric power, communication, weather, agriculture, oceans, photography and the like.

The screw is the essential part of unmanned aerial vehicle as the main lift part of unmanned aerial vehicle, has very important influence to unmanned aerial vehicle's overall performance parameter. Because unmanned aerial vehicle's characteristic often requires the screw to have characteristics such as light weight, high strength, high temperature resistant, corrosion-resistant, especially under bad weather such as sand and dust, the screw can guarantee that self quality is not influenced. Therefore, how to obtain a propeller with better wear resistance, bending strength and impact resistance is a problem to be solved by those skilled in the art.

Disclosure of Invention

The invention aims to provide a preparation method of an unmanned aerial vehicle propeller made of an inorganic fullerene-carbon fiber composite material, and solves the technical problems that the existing unmanned aerial vehicle propeller is heavy, poor in high-temperature resistance and incapable of resisting corrosion.

A preparation method of an unmanned aerial vehicle propeller made of an inorganic fullerene-carbon fiber composite material comprises the following steps:

step 1: preparing a matrix, namely preparing the carbon fiber, the polytetrafluoroethylene and the curing agent according to the weight ratio of 2: 1:1, stirring and mixing, adding the mixture into a melting furnace after mixing, continuously heating to 500 ℃, continuously stirring during heating, injecting the melted mixture into a matrix mold by using an injection molding machine after uniformly mixing, opening the matrix mold after the matrix mold is naturally cooled at normal temperature, and taking out the carbon fiber substrate;

step 2: manufacturing a reinforcing material, namely mixing carbon fibers, inorganic fullerene, epoxy resin and an additive in a weight ratio of 1: 0.5: 2: 1, adding the mixture into a magnetic stirrer, heating to 80 ℃, and continuously stirring for 20 minutes during the heating period;

and step 3: adding the mixture stirred by the magnetic stirrer in the step 2 into the bottom of the groove of the propeller mold, so that the stirred mixture is fully soaked at the bottom of the groove of the mold, and the specific gravity of the mixture is ensured to be about 25-30% of the whole propeller, immediately putting the carbon fiber substrate in the step 1 into the propeller mold by using a vacuum chuck, finally adding the mixture accounting for 25-30% of the whole propeller in the step 2, fully soaking the whole propeller mold, closing the mold and carrying out curing treatment after the material is added;

and 4, step 4: opening the mold and taking out the molded propeller when the mold in the step 3 is naturally cooled to room temperature;

and 5: and (5) grinding the edge of the propeller to remove burrs, and polishing the surface of the propeller to finish the preparation.

In the step 1, the injection molding pressure is kept at 15-25MPa during injection molding, and the injection molding temperature is 500 ℃.

The carbon fiber in the step 1 is bagasse-based carbon fiber, and the preparation process of the bagasse-based carbon fiber comprises the following steps: putting bagasse into a beaker filled with a sodium hypochlorite solution with the mass fraction of 5%, soaking for 12 hours, repeatedly filtering until the pH of the filtrate is close to neutral, putting the filtered bagasse into a drying box, and drying for 10 hours at 80 ℃;

the dried bagasse is contacted with an aqueous urea solution in a volume ratio of urea to deionized water of 1:1, soaked for 1h, the soaked bagasse is taken out, placed in a drying box, dried for 10h at 80 ℃, and repeatedly dried for 2-3 times to obtain sized bagasse;

putting the obtained sized bagasse into a vacuum tube furnace, sealing, introducing nitrogen, raising the temperature of the vacuum tube furnace to 400 ℃ at the speed of 5 ℃/min after exhausting air, and maintaining the temperature of the vacuum tube furnace for carbonization for 40min at 400 ℃;

then, the temperature of the vacuum tube furnace is increased to 1200 ℃ at the speed of 5 ℃/min, and the temperature is kept at 1200 ℃ for graphitization for 20min to obtain primary carbon fiber;

and (3) putting the primary carbon fiber into 45 wt% nitric acid water solution, soaking for 30min, taking out, putting into deionized water, rinsing for 2 times, putting the oxidized carbon fiber into a drying oven, and drying for 10h at 80 ℃ to obtain the bagasse-based carbon fiber.

The additive in the step 2 is formed by mixing an anti-aging agent, a flame retardant and a curing agent in the same proportion.

And the curing treatment in the step 3 is to preserve heat of the propeller mould for 1-3 hours by using an intermediate frequency heating furnace, wherein the heat preservation temperature is 180 ℃.

The inorganic fullerene in the step 2 is an aluminum-based nano composite fullerene material, and the synthesis process of the aluminum-based nano composite fullerene material is as follows: putting the inorganic fullerene nano-particles IF-WS2 into ethanol and dispersing by using an ultrasonic probe, mixing the inorganic fullerene nano-particles IF-WS2 and the ethanol mixture with vigorous stirring at 80-90 ℃ with Al powder until all ethanol is evaporated, drying in an oven at 110-130 ℃ for 11-13 hours to obtain a primary mixture sample, extruding the sample by a fused deposition modeling 3D printing technology, and controlling the temperature of a printing extrusion head to be 560-670 ℃ to complete synthesis.

The time for dispersing the ultrasonic probe is 0.8-1.2 hours, the ultrasonic frequency is 80-90 KHz, and in the fused deposition modeling 3D printing process, hot pressing is carried out for 30 minutes under the conditions that the hot pressing temperature is 560-650 ℃, the pressure is 75-85 KN, and the atmosphere is N2.

Heating the mixture of the inorganic fullerene nano-particles IF-WS2 and ethanol to 80 ℃, adding aluminum powder particles for mixing, rapidly stirring until the ethanol is completely volatilized to prepare a mixed solid sample of 20-30 wt% IF-WS2 and the aluminum powder, and then placing the mixed solid sample in an oven at 120 ℃ for drying for 12 hours.

By adopting the technical scheme, the invention has the following technical effects:

the addition of the inorganic fullerene can improve the wear resistance, bending strength and impact resistance of the carbon fiber composite material. The propeller has the advantages of wear resistance, bending strength, flexibility and the like which are enhanced by mixing the inorganic fullerene and the polytetrafluoroethylene on the basis of the high-strength performance of the carbon fiber substrate, the inorganic fullerene reinforced aluminum-based nano composite material has the characteristics of light weight, excellent damping performance and the capability of absorbing shock waves, so that the propeller has good application prospect in light damping materials and high-performance protective materials, and the propeller is low in preparation cost, can be industrially produced and has high practical value.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to preferred embodiments. It should be noted, however, that the numerous details set forth in the description are merely for the purpose of providing the reader with a thorough understanding of one or more aspects of the present invention, which may be practiced without these specific details.