阅读说明：本技术 一种飞机防除冰复合材料及其制备方法 (Aircraft anti-icing and deicing composite material and preparation method thereof ) 是由 刘洪� 黄小彬 孔维梁 于 2019-10-29 设计创作，主要内容包括：本发明公开了一种防除冰复合材料及其制备方法,该复合材料为多层结构,多层结构自上而下依次为基材、片材、永磁体；基材由阳极氧化铝单通多孔材料吸附磁流体组成,片材为聚甲基丙烯酸甲酯板或铝板中的一种,基材底面与片材通过粘连剂粘连,永磁体与片材底面通过粘连剂粘连。本发明提供的复合材料防冰性能优异,冰几乎不会与基底发生粘附,结冰后冰极易从表面脱除,而且防冰寿命长,足以应对近70次的结冰除冰循环,而且具有复合方法简单便捷,成本低,实用性强等优点,可有效、长效的应用在飞机上,防止由于结冰事故发生。(The invention discloses an anti-icing and deicing composite material and a preparation method thereof, wherein the composite material is of a multilayer structure, and the multilayer structure comprises a base material, a sheet material and a permanent magnet from top to bottom in sequence; the base material is composed of an anodic alumina single-pass porous material adsorption magnetic fluid, the sheet material is one of a polymethyl methacrylate plate or an aluminum plate, the bottom surface of the base material is adhered to the sheet material through an adhesive, and the permanent magnet is adhered to the bottom surface of the sheet material through the adhesive. The composite material provided by the invention has excellent anti-icing performance, ice can hardly adhere to a substrate, the ice is very easy to remove from the surface after being frozen, the anti-icing service life is long, and the anti-icing material can be used for meeting freezing and deicing cycles of nearly 70 times, has the advantages of simple and convenient composite method, low cost, strong practicability and the like, can be effectively and long-term applied to an airplane, and prevents the occurrence of freezing accidents.)

1. The aircraft anti-icing and deicing composite material is characterized by being of a multilayer structure, wherein the multilayer structure sequentially comprises a base material, a sheet material and a permanent magnet from top to bottom; the base material is composed of an anodic alumina single-pass porous material adsorption magnetic fluid, the sheet is one of a polymethyl methacrylate plate or an aluminum plate, the bottom surface of the base material is adhered to the sheet through an adhesive, and the permanent magnet is adhered to the bottom surface of the sheet through the adhesive.

2. The aircraft deicing composite as set forth in claim 1, wherein said magnetic fluid is composed of a base fluid and suspended magnetic particles, said base fluid is composed of 80% by weight of paraffin oil and 20% by weight of class iii clean environment-friendly aviation kerosene, and said suspended magnetic particles are spherical ferroferric oxide treated with a surfactant.

3. An aircraft deicing composite as claimed in claim 2 wherein said spherical ferroferric oxide has a diameter of 5-20nm and said surfactant is sodium oleate or polyethylene glycol (PEG2000) having an average molecular weight of 2000.

4. An aircraft deicing composite as claimed in claim 1 wherein said anodized aluminum single pass porous material surface is comprised of a plurality of hexagonal columnar aluminum oxide cells, said anodized aluminum single pass porous material surface is of a honeycomb structure, said cells are internally provided with circular holes, said circular holes are provided with semicircular blocking layers at lower ends thereof, and said blocking layers are provided with aluminum layers thereunder.

5. An aircraft deicing composite as claimed in claim 4 wherein said circular holes have a pore size of 40-200nm, a hole depth of 30-80 μm, and a hole spacing of 300-500 nm.

6. An aircraft deicing composite as claimed in claim 1 wherein said sheet has a thickness of from 2 to 5 mm.

7. An aircraft deicing composite as set forth in claim 1 wherein said substrate, said sheet, and said permanent magnets are of the same area.

8. An aircraft deicing composite as set forth in claim 1 wherein said permanent magnet is one of a type N55 neodymium iron boron magnet or an EP-B type neodymium iron boron magnet or a samarium cobalt permanent magnet.

9. A method of manufacturing an aircraft deicing composite as claimed in any one of claims 1 to 8, comprising the steps of:

step 1: adhering the bottom surface of the base material to a sheet material by using an adhesive, wherein the base material is an anodic aluminum oxide single-pass porous material, and the sheet material is one of a polymethyl methacrylate plate or an aluminum plate;

step 2: adhering a permanent magnet below the sheet through an adhesive;

and step 3: and adding a magnetic fluid to the single-pass porous surface of the anodic aluminum oxide until the magnetic fluid just does not overflow from the single-pass porous surface of the anodic aluminum oxide, so as to obtain the anti-icing composite material.

10. A method of making an aircraft deicing composite as claimed in claim 9, wherein step 3 comprises:

step 3.1: treating suspended magnetic particles by using a surfactant, wherein the suspended magnetic particles are spherical ferroferric oxide, and the surfactant is sodium oleate or polyethylene glycol with the average molecular weight of 2000;

step 3.2: and (3) mixing the suspended magnetic particles obtained in the step (3.1) with a base liquid to obtain the magnetic fluid, wherein the base liquid is composed of paraffin oil accounting for 80% by weight and III-grade clean environment-friendly aviation kerosene accounting for 20% by weight.

Technical Field

The invention relates to the field of aerochemistry, in particular to an aircraft anti-icing and deicing composite material and a preparation method thereof.

Background

Icing is a common phenomenon in nature, and except a few cases, people suffer from various hazards caused by icing. In the field of wind power generation, wind power generation farms built in cold and humid areas also have a number of adverse effects due to the problem of icing on the surfaces of the blades and the units of the wind power generators. The icing phenomenon on the surface of the blade can cause the load of the blade to be increased and even to be deformed, the service life of the blade is shortened, the balance of the wind generating set is influenced, the generating efficiency is reduced, and the set is damaged. Reports show that the annual generating rate of the unit is reduced by 50 percent due to icing on the surface of the blade of the wind driven generator. In the aspect of outdoor power transmission facilities and communication lines, icing phenomena can also cause considerable harm. In 2008, the southern areas of China suffered from rare ice disasters. The continuous low temperature caused precipitation and icing causes the breakdown of large-range and long-time power transmission networks and communication lines and the interruption of transportation aorta such as roads, railways and the like. For the airplane with higher safety factor requirement, the airplane often flies or passes through in cloud layers, so that the airplane can often encounter a low-temperature and high-humidity supercooled environment in the air even in the winter where the airplane is not frozen, and the damage of the icing phenomenon to the airplane is most direct and obvious. According to statistics, the probability of air accident caused by icing exceeds 15%. In the 6 th and 3 rd 2006, in the implementation of a mission by one military transport plane of air force in China, 40 people on the plane all encounter a disaster when a certain place in Anhui crashes and crashes, and the direct reason for the accident is that the plane freezes in the air and crashes out of control after passing through the freezing area for many times. Therefore, the demand of the aircraft for efficient anti-icing materials is very urgent.

For example, chinese patents publication nos. CN106521465A and CN106520074A both disclose an anti-icing material for use in an aircraft, but the anti-icing performance is worried about under the conditions of large supercooling degree and frosting, the absolute life is still unsatisfactory, especially after repeated freezing and deicing cycles, it is difficult to ensure that the micro-nano structure on the surface is not destroyed, and the long-acting anti-icing effect cannot be achieved, and the anti-icing material has great disadvantages in application to aircraft.

Accordingly, those skilled in the art have endeavored to develop a material that can be used on aircraft to prevent and remove ice efficiently and for a long period of time.

Disclosure of Invention

In view of the above-mentioned defects of the prior art, the present invention is to solve the problem that the performance of the anti-icing and anti-icing materials currently used in airplanes is not good after long-term repeated use.

In order to achieve the aim, the invention provides an aircraft anti-icing and deicing composite material which is of a multilayer structure, wherein the multilayer structure sequentially comprises a base material, a sheet and a permanent magnet from top to bottom; the base material is composed of an anodic alumina single-pass porous material adsorption magnetic fluid, the sheet is one of a polymethyl methacrylate plate or an aluminum plate, the bottom surface of the base material is adhered to the sheet through an adhesive, and the permanent magnet is adhered to the bottom surface of the sheet through the adhesive.

Further, the magnetic fluid consists of base fluid and suspended magnetic particles, the base fluid consists of paraffin oil accounting for 80% by weight and III-grade clean environment-friendly aviation kerosene accounting for 20% by weight, and the suspended magnetic particles are spherical ferroferric oxide treated by a surfactant.

The base liquid can be purchased from the market, and the details are not described in the application.

Further, the diameter of the spherical ferroferric oxide is 5-20nm, and the surfactant is sodium oleate or Polyethylene Glycol (PEG2000) with the average molecular weight of 2000.

Further, the surface of the single-pass porous material of the anodized aluminum is composed of a plurality of hexagonal cylinder aluminum oxide cells, the surface of the single-pass porous material of the anodized aluminum is of a honeycomb structure, circular holes are formed in the cells, semicircular blocking layers are arranged at the lower ends of the circular holes, and aluminum layers are arranged below the blocking layers.

Furthermore, the aperture of the circular hole is 40-200nm, the hole depth is 30-80um, and the hole spacing is 300-500 nm.

Further, the thickness of the sheet is 2-5 mm.

Further, the areas of the base material, the sheet material and the permanent magnet are the same.

Further, the permanent magnet is one of an N55 type neodymium iron boron magnet or an EP-B type neodymium iron boron magnet or a samarium cobalt permanent magnet.

The invention also provides a preparation method of the aircraft anti-icing and deicing composite material, which comprises the following steps:

step 1: adhering the bottom surface of the base material to a sheet material by using an adhesive, wherein the base material is an anodic aluminum oxide single-pass porous material, and the sheet material is one of a polymethyl methacrylate plate or an aluminum plate;

step 2: adhering a permanent magnet below the sheet through an adhesive;

and step 3: and adding a magnetic fluid to the single-pass porous surface of the anodic aluminum oxide until the magnetic fluid just does not overflow from the single-pass porous surface of the anodic aluminum oxide, so as to obtain the anti-icing composite material.

Further, step 3 includes:

step 3.1: treating suspended magnetic particles by using a surfactant, wherein the suspended magnetic particles are spherical ferroferric oxide, and the surfactant is sodium oleate or polyethylene glycol with the average molecular weight of 2000;

step 3.2: and (3) mixing the suspended magnetic particles obtained in the step (3.1) with a base liquid to obtain the magnetic fluid, wherein the base liquid is composed of paraffin oil accounting for 80% by weight and III-grade clean environment-friendly aviation kerosene accounting for 20% by weight.

Wherein, the adhesion agent can be selected from AB glue, which is mainly used for adhesion, and the invention is not particularly limited.

The invention discloses an aircraft anti-icing and deicing composite material which is excellent in anti-icing performance, ice hardly adheres to a substrate, the ice is very easy to remove from the surface after being frozen, the anti-icing service life is long, the composite material can be used for coping with nearly 70 times of freezing and deicing cycles, the composite material has the advantages of being simple and convenient in composite method, low in cost, strong in practicability and the like, and can be effectively and long-term applied to an aircraft to prevent the occurrence of icing accidents.

The conception, the specific structure and the technical effects of the present invention will be further described with reference to the accompanying drawings to fully understand the objects, the features and the effects of the present invention.

Drawings

FIG. 1 is an SEM image of an anodized aluminum single pass porous material according to one embodiment of the invention;

FIG. 2 is a graph of ice adhesion versus the number of icing-deicing cycles for an anti-icing composite of one embodiment of the present invention under certain conditions;

FIG. 3 is an SEM image of an anodized aluminum single pass porous material according to another embodiment of the invention;

FIG. 4 is a graph of ice adhesion versus the number of icing-deicing cycles for a given condition of an anti-icing composite of another embodiment of the present invention;

FIG. 5 is a graph of ice adhesion versus the number of icing-deicing cycles for a given condition of an anti-icing composite according to yet another preferred embodiment of the present invention;

FIG. 6 is a graph showing the relationship between the ice adhesion under a certain condition and the number of icing-deicing cycles in the comparative example of the present invention;

FIG. 7 is a graph showing the relationship between the ice adhesion under a certain condition and the number of icing-deicing cycles in a further comparative example of the present invention.

Detailed Description

The technical contents of the preferred embodiments of the present invention will be more clearly and easily understood by referring to the drawings attached to the specification. The present invention may be embodied in many different forms of embodiments and the scope of the invention is not limited to the embodiments set forth herein.