CN110947606A

CN110947606A - Method for improving tear resistance and strengthening protection of airplane

Info

Publication number: CN110947606A
Application number: CN201911262668.2A
Authority: CN
Inventors: 周诗敏; 朱凯立; 雷向阳; 李小军
Original assignee: Casley (shanghai) New Materials Co Ltd
Current assignee: Casley (shanghai) New Materials Co Ltd
Priority date: 2019-12-10
Filing date: 2019-12-10
Publication date: 2020-04-03

Abstract

The invention discloses a method for improving the tear resistance and strengthening the protection of an airplane, which is to spray an anti-explosion material with a yellowing-resistant nano structure on a stressed bracket of the airplane or on the skin of the airplane. Further tear-resistant protection is provided for the aircraft by spraying the anti-explosion material with the yellowing-resistant nano structure, and the possibility of wing breakage is reduced to the maximum extent. The tear resistance is improved, the speed of the airplane can be further improved, and a new competitive advantage is brought.

Description

Method for improving tear resistance and strengthening protection of airplane

Technical Field

The invention relates to the field of aircrafts, in particular to a method for improving the tear resistance and strengthening protection of an airplane.

Background

In the flying process of an airplane or an aircraft, according to the principle of hydrodynamics, when the airplane slides forwards, the air flow speed of the upper side is higher than that of the lower side due to different shape designs of the upper side and the lower side of the wing of the airplane, the air pressure of the upper side is smaller than that of the lower side, so that a pressure difference is generated on the wing, the direction of the pressure difference is vertical upwards, the pressure difference is larger when the speed of the airplane is higher, and the airplane can take off when the pressure difference is larger than the weight of the airplane.

By this principle we are clear. The wings of an aircraft are the main stressed objects of the aircraft. It is subjected to extremely large forces. At some point, the force of the pressure difference may be too great, which may cause extreme accidents such as wing breakage, severe deformation and failure to recover (e.g. heavy airplane, fast flying, etc.).

Another concept is referred to here, namely the fatigue phenomenon of metals. The fatigue phenomenon is a condition that a crack of metal gradually expands under the action of variable load which is lower than the ultimate strength of the metal and finally fails. It is simply understood that the metal breaks as it bends.

Most aircraft are of alloy material. Such as aluminum alloy, magnesium alloy, titanium alloy, and alloy steel is used in some airplanes. These alloy materials are all light alloys. Although aluminum and magnesium are relatively low in strength, the strength of aluminum-magnesium alloys can be improved by adding different alloy phases, but the fatigue phenomenon of metals may still occur. The inner beam of the wing is the main stressed part of the wing, and usually adopts super hard aluminum and steel or titanium alloy; the joint part of the wing beam and the fuselage adopts high-strength structural steel. The wing skin adopts superhard aluminum with good compression resistance and hard aluminum with good tensile and fatigue resistance respectively because the stress conditions of the upper wing surface and the lower wing surface are different.

In order to understand the performance and safety of aircraft manufacturing materials, scientists have designed a series of experiments to test aircraft, the main of which is static force experiments. The static force experiment is one of the contents of the structure experiment, so that the distribution conditions of the strength, the rigidity, the stress and the deformation of the aircraft structure or component under the action of the static load can be observed and researched, and the static force experiment is an important means for verifying the structural strength and the static force analysis correctness of the aircraft.

Disclosure of Invention

The technical problem to be solved by the invention is a method for improving the tear resistance and strengthening the protection of an airplane, spraying an anti-yellowing explosion-proof material containing an isocyanate nano structure, having a nano-scale net structure, strong bond energy, difficult fracture compared with other materials, having obvious effect on protecting various materials, and greatly improving the tear resistance of the airplane when being used on the airplane

The invention is realized by the following technical scheme: a method for improving the tear resistance and strengthening protection of an airplane comprises the following steps of spraying an anti-explosion material with a yellowing-resistant nano structure on a stressed bracket of the airplane or on the skin of the airplane, and when constructing the bearing part of the airplane:

firstly, after a frame is manufactured on an airplane, the integral frame of the airplane is assembled, including the connection part of a fuselage and a wing, surface treatment is carried out on the part needing spraying, such as sand blasting and polishing processes, a certain roughness is ensured, the surface is ensured to be clean, and no adverse factor interference of oil stain, rust and dust exists;

secondly, coating a layer of primer in order to improve the bonding force between the bearing part of the airplane and the anti-yellowing explosion-proof material containing the isocyanate nano-structure;

step three, assembling the prepared anti-yellowing explosion-proof material component A and component B containing the isocyanate nanostructure to a Curie spraying H-XP3 device, and spraying A, B two components by the device;

step four, the spraying operation can not be interrupted, the spraying thickness range is selected to be 0.3-50mm, 6, the spraying reinforced part comprises a rivet riveting part, and the spraying thickness range is 1-50 mm;

fifthly, cutting off redundant parts by using a sharp blade after spraying is finished at a position where a hole needs to be reserved and by using an adhesive tape or blocking the corresponding position;

when the skin and other parts of the airplane are constructed, the method comprises the following specific steps:

firstly, polishing the surface paint surface by using processes of sand paper, a grinding wheel or sand blasting and the like to a certain rough surface, and removing surface dust to prepare for the next step;

secondly, coating a layer of primer in order to improve the bonding force between the airplane part and the anti-yellowing explosion-proof material containing the isocyanate nanostructure;

step four, the spraying operation can not be interrupted. Selecting the thickness range of spraying to be 0.3-50 m;

fifthly, the spraying reinforced part comprises a rivet riveting part, and the spraying thickness range is 1-50 mm;

and sixthly, blocking the corresponding position at the position where the hole needs to be reserved by using an adhesive tape or other materials, and cutting off the redundant part by using a sharp blade after the spraying is finished.

And step seven, coating the skin of the stressed bearing part in the nano explosion-proof material as completely as possible, and performing integral spraying to form the yellowing-resistant explosion-proof material containing the isocyanate nano structure into an integral molding.

As a preferred technical scheme, the roughness of the grinding is 50, 60, 80, 100, 120, 150, 180, 220, 280, 320, 400, 500 and 600 meshes.

Preferably, the primer is an epoxy primer or a polyurethane primer.

The invention has the beneficial effects that: the anti-tear protection method provided by the invention provides further anti-tear protection for the aircraft by spraying the anti-explosion material with the yellowing-resistant nano structure, and reduces the possibility of wing breakage to the maximum extent. The tear resistance is improved, the speed of the airplane can be further improved, and a new competitive advantage is brought.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

FIG. 1 is a schematic structural diagram of the present invention.

Detailed Description

All of the features disclosed in this specification, or all of the steps in any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.

Any feature disclosed in this specification (including any accompanying claims, abstract and drawings), may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.

In the description of the present invention, it is to be understood that the terms "one end", "the other end", "outside", "upper", "inside", "horizontal", "coaxial", "central", "end", "length", "outer end", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, should not be construed as limiting the present invention.

Further, in the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.

The use of terms such as "upper," "above," "lower," "below," and the like in describing relative spatial positions herein is for the purpose of facilitating description to describe one element or feature's relationship to another element or feature as illustrated in the figures. The spatially relative positional terms may be intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "below" or "beneath" other elements or features would then be oriented "above" the other elements or features. Thus, the exemplary term "below" can encompass both an orientation of above and below. The device may be otherwise oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

In the present invention, unless otherwise explicitly specified or limited, the terms "disposed," "sleeved," "connected," "penetrating," "plugged," and the like are to be construed broadly, e.g., as a fixed connection, a detachable connection, or an integral part; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

As shown in figure 1, an anti-explosion material 2 with a yellowing resistant nano structure is sprayed on a stressed bracket of an airplane or an airplane skin 1.

Aircraft construction typically produces load-bearing beams, which are often "I" shaped load-bearing structures. The force to which each segment may be subjected can be accurately obtained, generally by scientific calculation. And spraying anti-explosion materials with anti-yellowing nano structures of different thicknesses according to different stresses. The thicker nanometer explosion-proof material is coated on the part which is stressed more accurately.

First, after the frame is manufactured, the whole frame of the airplane, including the connection part of the fuselage and the wing, is assembled. And (3) performing surface treatment on the part to be sprayed, such as sand blasting, polishing and other processes, and ensuring certain roughness. 50, 60, 80, 100, 120, 150, 180, 220, 280, 320, 400, 500 and 600 meshes, and is preferably made of coarse sand paper, grinding wheel or quartz sand, so as to ensure clean surface without interference of adverse factors of oil stain and rust dust and the like.

In order to improve the bonding force between the aircraft bearing part and the anti-yellowing explosion-proof material containing the isocyanate nano-structure, a layer of primer is coated, and preferably epoxy primer or polyurethane primer.

Taking a component A and a component B of an anti-yellowing isocyanate nanostructure-containing explosion-proof material which are prepared in advance. Was fitted to a curek spray H-XP3 apparatus, with which A, B two-component spray was applied.

The spraying operation can not be interrupted. The thickness of the spray coating is selected within the range of 0.3-50 mm. Preferably 0.5-30 mm.

The touch coating strengthening part comprises: rivet joints (or other joints at various locations of the aircraft). The thickness range of the spray coating is 1-50mm.

And (3) at the position where the hole needs to be reserved (such as the requirement of connection with the skin of the airplane or the interior of the airplane and the like), using adhesive tapes or blocking the corresponding position. After the spraying was completed, the excess was cut off with a sharp blade.

The spraying point should also have the following requirements: the stressed load-bearing part should be wrapped in the nanometer explosion-proof material as completely as possible so as to obtain the best protection effect.

Skin of the aircraft and other parts:

firstly, polishing the surface: and (3) polishing the surface paint surface by using processes of sand paper, a polishing wheel or sand blasting and the like to a certain rough surface, and removing surface dust to prepare for the next step. The rough surface is specially polished to improve the bonding force. 50, 60, 80, 100, 120, 150, 180, 220, 280, 320, 400, 500, 600 mesh. Preferably, coarser sandpaper, grinding wheels or quartz sand is selected. The polished surface is required to be free of disadvantages such as greasy dirt, rust, dust, etc.

In order to improve the bonding force between the airplane part and the anti-yellowing explosion-proof material containing the isocyanate nano structure, a layer of primer is coated, and preferably epoxy primer or polyurethane primer.

The prepared anti-yellowing explosion-proof material component A and component B containing the isocyanate nanostructure are assembled to a Curie spray H-XP3 device, and the device is used for spraying A, B two components.

The spraying operation can not be interrupted. The thickness of the spray coating is selected in the range of 0.3 to 50mm, preferably 0.5 to 30 mm.

And (3) blocking the corresponding position by using adhesive tape or other materials when the hole needs to be reserved (such as the requirement of connection with the skin of the airplane or the interior of the airplane and the like), and cutting off the redundant part by using a sharp blade after the spraying is finished.

The stressed bearing part of the skin is difficult to be completely wrapped in the nano explosion-proof material as much as possible, but the skin is integrally coated, so that the yellowing-resistant explosion-proof material containing the isocyanate nano structure is integrally formed.

An aircraft fuel tank belongs to a flammable and explosive component and is an important protection part of an anti-yellowing anti-explosion material containing an isocyanate nano structure.

The construction method comprises the following steps:

through surface treatment, the surface of the oil tank is cleaned, and oil stain, rust, dust and the like are prevented.

In order to improve the bonding force with the anti-yellowing isocyanate nanostructure-containing explosion-proof material, a layer of primer is brushed, and preferably epoxy primer or polyurethane primer.

After the primer is coated and dried, spraying the anti-explosion material with the yellowing resistance and the isocyanate nano structure, and taking the prepared anti-explosion material A component and B component with the yellowing resistance and the isocyanate nano structure. The anti-explosion material containing the isocyanate nano structure and resisting yellowing can be integrally formed by assembling the anti-explosion material to a Gurek spraying H-XP3 device and spraying A, B components with the device. During spraying, in order to improve the deformation resistance and further protection, an explosion-proof material needs to be sprayed on the surface of the whole oil tank, screws need to be left and screwed or positions need to be exposed, adhesive paper or other materials are made in advance to block corresponding positions, after spraying is completed, the redundant parts are cut off by a sharp blade, and the oil tank is sprayed and wrapped by the explosion-proof material which is yellowing-resistant and contains the isocyanate nano structure.

The anti-yellowing explosion-proof material containing isocyanate nano-structure is another invention patent applied by the company, the application number is 201910599797.4, and the following components are briefly introduced as follows:

the catalyst mainly comprises isocyanate and polycarbonate polyol or polyether polyol, wherein the isocyanate reacts with the polycarbonate polyol or the polyether polyol to form carbamido, and dibutyltin dimaleate or dibutyltin sulfate or dibutyltin dilaurate is adopted as the catalyst;

the auxiliary materials comprise an organic catalyst, amino-terminated polyether polyol, a flame retardant, a plasticizer, a diamine chain extender, an antioxidant, a flatting agent, a dispersing agent, a coupling agent, an anti-settling agent, an antistatic agent and nano rutile titanium dioxide.

The method specifically comprises the following steps:

step one, preparing a prepolymer of the component A;

(1) fully mixing diisocyanate, an organic catalyst and sodium bicarbonate in advance, and charging nitrogen for storage;

(2) the polyether polyol and polycarbonate polyol are fully mixed and vacuumized and dehydrated at the temperature of 115 ℃, and when the content is lower than 0.1 percent. Cooling to 80 ℃, then adding the mixture while stirring, controlling the temperature at 80 ℃ and reacting for 6 hours to obtain a component A;

step two, preparation of the component B:

adding amino-terminated polyether polyol, diamine chain extender, antioxidant, flatting agent, dispersant, coupling agent, antistatic agent fatty alcohol-polyoxyethylene ether, phosphorus-containing flame retardant, plasticizer and other components into a stirring kettle in sequence, fully stirring, finally adding nano rutile type titanium dioxide, fully stirring, adding the medicament into each batch, and stirring for at least 30 minutes.

The above description is only an embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that are not thought of through the inventive work should be included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope defined by the claims.

Claims

1. A method for improving the tear resistance and strengthening the protection of an airplane is characterized in that: when an explosion-proof material with a yellowing-resistant nano structure is sprayed on a stressed support of an airplane or an airplane skin, and a bearing part of the airplane is constructed, the method comprises the following specific steps:

2. A method of increasing tear resistance and enhancing protection of an aircraft as defined in claim 1, wherein: the roughness of the grinding is 50, 60, 80, 100, 120, 150, 180, 220, 280, 320, 400, 500 and 600 meshes.

3. A method of increasing tear resistance and enhancing protection of an aircraft as defined in claim 1, wherein: the primer is epoxy primer or polyurethane primer.