Method for light aeroplane covering

FIELD: transport.

SUBSTANCE: invention relates to method for covering light airplanes with polyester sheathing fabric, as well as to dispersive hot-gluing glue and its application for covering. For covering, polyester sheathing fabric with longitudinal shrinkage of 7% and transversal shrinkage of 5% at 160-180°C is used. In the process of covering light airplanes and/or their parts consisting of frame system, sheathing fabric in the area of its overhangs and frame parts is covered by dispersive hot-gluing glue and wrapped around longeron part of frame so that when connection between sheathing fabric and frame produced by glue is destructed the fabric could be held on frame carcass. Dispersive hot-gluing glue contains 80-88% of adhesive, 12-15% of hardener and 0.15-0.3% thickener, and the glue is polymerised at temperatures >40°C. The hardener contains 54-60% of solvent, 0.35-0.5% of naphthalensulfonic acid sodium salt-based stabiliser, 0.25-0.35% of propoxylated spirit-based emulsifier, 1.7-1.9% of polyetheramines-based hardener, 37-41% of polyisocyanate.

EFFECT: reliability and durability of light airplanes and/or their parts covering.

15 cl, 3 dwg

 

The invention relates to a method for covering light aircraft and/or parts of polyester upholstery fabric, as well as to the dispersion glue hot glue and to its use for the skin. In addition, the invention relates to a light aircraft or its parts, which are sheathed polyester fabric by the method according to the invention.

Systems and materials for covering light aircraft or aircraft models in the prior art. So, for example, EP 0737132 B1 describes suitable for processing iron, easy to use polyester upholstery fabric, consisting of polymerized multilayer system, which is applied on polyester fabric, specially designed for use as a fabric for covering light aircraft. Because the quality of fabric, ultimately, improves, it is no longer necessary after the application of varnish. However, if it is desirable, for example, for reasons of visual surface finishing, the fabric can still easily cover the top varnish.

Patterns that build the sheathe planes, very different and consist of such materials as aluminum, steel, wood, fiberglass or reinforced carbon fiber plastic. In accordance with these terms of processing, such as, for example, the temperature used for sheathing fabric, also vary the Lack of corresponding prior art systems covering light aircraft is that this procedure is associated with very high costs. That is, the plating is applied an adhesive varnish, which was first applied in several layers to sheathe structure. Then sheathing (finishing) material impregnated with solvents (e.g. acetone), which soften the adhesive lacquer. After that, his press in the softened adhesive lacquer. After drying cladding material straighten with hot air. Then about 5-10 promazyvanii Amalita, and if necessary, in the interim, need more polishing. It is necessary to ensure that not formed weeping formations. The last coating Amalita specially mixed with aluminum powder to achieve the blocking of UV radiation. Then 1-3 promazyvanija opaque finish. In conclusion, all this can be covered even with a transparent varnish. For all airplane designs this work is associated with a very high expenditure of time and when the damage cannot simply be ironed item again and again repair to carry out the entire process of covering and painting.

Proceeding from this prior art, the present invention tasked to develop a way that can be reliably used on light aircraft and/or parts, and precision plating, its durability, and the cost of materials and thus cost clapboard and each structure and the quality of the material sheathe a light aircraft should remain unchanged.

This problem is solved with the relevant invention in the manner specified in the claims. In accordance with this invention in the first embodiment relates to a method for covering light aircraft and/or parts thereof, consisting of a frame system, and a frame or part of a frame upholstered in polyester upholstery fabric, and upholstery fabric has a longitudinal shrinkage of 5-8%, preferably 7%, and a transverse shrinkage of 4-6%, preferably 5%, at 160-180°C, and the method comprises the following steps:

a) upholstery fabric in its overhangs, and parts of the frame, which will be upholstery fabric, smear a dispersion adhesive hot gluing and adhesive includes curing component that depolimerizuyutza at the temperature of processing >40°C, and

b) upholstery fabric thus wrapped around the spar of the frame, so that when the destruction of the obtained adhesive connection between the sheathing fabric and frame upholstery fabric continued to stay on frame frame.

Light aircraft in the sense of the invention can have a frame system consisting, for example, from wood, aluminum, steel, fiberglass or reinforced carbon fiber plastic.

Parts of a light aircraft are, for example, bearing surfaces, tail, nose spar, rear lounge is Ron, the main spar, spar rudder, ribs, Aileron or the fuselage.

Preferably use airtight sheathing fabric, as this leads to a particularly favorable properties during the flight.

In the method of lining according to the invention the sheathing itself shrinks, even if the glue breaks down (attenuated). This prevents the weakening of fabric sheathing. Excluded possible razdevanie tissue. Thus, the method leads to improved reliability and is therefore advantageous in comparison with the methods appropriate to the level of technology.

The plating method is preferably characterized by the fact that first upholstery fabric cut out so that the shape of the piece of fabric matches the primary form sheathe of the plane, and on each boundary line is left overhang (allowance), which serves to further attach the fabric to the side of the plane. Then the upholstery fabric on the inner side of the coat dispersion adhesive hot gluing in the area, which should be pasted on the structure of the aircraft. The structure is also coated in sheathe field of dispersion glue hot gluing. Dispersion glue hot gluing contains, as a component, hardening component, which is released already at relatively low temperature°C and allows you to depolimerizuet glue. Preferably, the adhesive is polymerized at temperatures of >40°C, particularly preferably at 40-60°C. the Relatively low processing temperatures have the advantage that the method is gentle for sheathing fabric and what you can achieve a more complete polymerization.

The advantage of the dispersion adhesive according to the invention is that it not only sticks together while applying heat, but also polymerized, that is sewn. The result is a thermally stable bonding.

In the case of metal structures, if necessary, before sheathing need to Polish all the rough edges, so as not to damage the upholstery fabric. It has also proven advantageous to degrease metal surface prior to plating, as it leads to better adhesion of the glue.

In the case of aluminum structures can before applying the dispersion glue hot gluing apply to aluminum construction thermostable priming lacquer. For steel structures before shell can preferably be applied thermostable primer.

A preferred method for covering light aircraft and/or parts thereof, in which a dispersive adhesive hot gluing contains 80-88% binder, 12-15% curing component and 0.15-0.3% thickener.

Under the percentage data in the sense of the invention should be understood weight percent.

PR is doctitle, binder contains a polyurethane dispersion, linear or slightly branched. In addition, the thickener is preferably based on polyurethane, particularly preferably the thickening agent is nonionic.

In one advantageous embodiment, curing component contains 54-60% of solvent, of 0.35-0.5% stabilizer based on the sodium salt naphtalenesulfonic acid, 0.25 to 0.35% of the emulsifier on the basis of propoxyethanol alcohol, 1.7 to 1.9% of hardener on the basis of polyetheramine and 37-41% MDI.

The solvent is preferably water is used. The stabilizer based on the sodium salt naphtalenesulfonic acid may represent, for example, Tamol NN 4501. As the emulsifier can be used emulsifier FD. Hardener based polyetheramine can be, for example, Jeffamine T403. Preferred aliphatic polyisocyanate, for example, Desmodur LPBUEJ471.

Advantageous first to fit the underside of the aircraft such that the first front in the direction of flight of the end wrap coated with glue part of fabric sheathing, and this part of iron a suitable tool. Then the rear end of the plane wrapped part of sheathing fabric, which, as in the case of the front end of the coated adhesive. Then this part of the iron in the same manner as the front end.

As the next stage is fitted to the upper side of the plane, again starting from the front in the direction of flight of the end, which is wrapped in coated glue the piece of fabric sheathing, then upholstery fabric pritagivaut, continued here also wrap the back end of the plane part of sheathing fabric is also coated with adhesive, and upholstery fabric pritagivaut in the same way.

In the following embodiment, the invention relates to a method for covering light aircraft and/or parts thereof, characterized in that:

a) for covering the tail upholstery fabric cut out so that the overhang (A) trim the edges to coat spar sheathe tail was (A=π·d·x)and (A=π·d·y) from the tail spar the same tail, where d is the diameter of the glue cloth sheathing tube (cm), x=1.5 to 2.0, preferably about 1.75, y=0,55-of 1.05, preferably of 0.8 and

b) the underside of the tail is fitted in such a way that the nose spar wrap around 1.75 turnover (from 550° to 700°) coated with glue part of sheathing fabric and this part pritagivaut, and then the tail spar wrap around 0.75 turnover (200°-350°) also missed glue part of sheathing fabric and this part pritagivaut identical way, then

(c) obtain the Ute upper side of the tail so that nose spar wrap around 0.5 turnover (150°-210°) coated with glue part of sheathing fabric and upholstery fabric pritagivaut, while the tail spar wrap then in less than a half-turn (120°-170°) also missed glue part of sheathing fabric and upholstery fabric pritagivaut the same way.

The result of this method of wrapping the covering itself "addictive", and this guarantees hold even if the adhesive is destroyed. This ensures a high degree of reliability and durability.

Preferably, first fitted to the upper side of the tail. To do this, first the bow spar turns sheathing fabric in 0.5 turnover (150°-210°, preferably 180°), and the clasping portion is coated with adhesive so as when wrapping the bottom side. Then upholstery fabric pritagivaet, and then the tail spar turns less than one-half turn (150°-210°, preferably 180°) also missed glue part of sheathing fabric and upholstery fabric pritagivaut the same way. This number of revolutions is advantageous for a high stability of the plating, while not affecting negatively on the aerodynamic characteristics of the sloping part of the aircraft due to local thickening.

In the next one preferred embodiment, about what westline method according to the invention in the plating vertical fin first covered the left side, while covering the right side of the upholstery fabric wrapped less than 0.5 turnover (110°-160°, preferably 144°) around the nose and tail spar, and the overlap on the spars is not juts out into the airflow. This version of the implementation in the case of the vertical fin provides stable plating, which endures induced air flow mechanical loads, sometimes significant, these structural elements.

In one of the following preferred embodiment of the method according to the invention with the covering of the fuselage first of all contact surfaces between the sheathing fabric and chassis promazyvaetsya dispersion glue hot glue and then upholstered, preferably in the following sequence: bottom - right side - left side - top side of the fuselage. Compliance with this sequence ensures that it will be convenient to handle hard-to-reach places. Preferably, the covering of the fuselage consists of as fewer individual parts, because it reduces the number of joints and seams.

In one of the following preferred embodiment of the method according to the invention before priduzivanja right of the fuselage skin, which was already postponed the structure of the fuselage and applied glue, left cladding fixed on the fuselage. Blah is odara this manner it is possible to transfer the structure of the fuselage on the inner side of the casing, then it is already possible to apply the adhesive, which allows the precise and equal application of fabric sheathing on both sides of the fuselage.

In one preferred embodiment, upholstery fabric then sit down, warming her one or twice using a hot air gun to about 200°C when installing a temperature from 280°C to 380°C, preferably 350°C and the actual temperature of the tissue is governed by the distance from the gun. Preferably, the plating process was completed this thermointelligence shrinkage of fabric sheathing. So, there is no shrinkage, fabric only pritagivaut until it snaps into place depolimerization glue. In this way, first, eliminate wrinkles, and secondly, the shrinkage of the film gives stability. This method saves time and preserves the environment, because they do not use any solvent. In addition, the increase in weight of the aircraft because of this covering 10-20 kg less than conventional methods of plating.

In the next one preferred embodiment, before covering flaps also coat the dispersion glue hot glue and after drying pritagivaut them riveting and a reinforcing plate to protect the closing of fabric sheathing. Patches, in the sense of the invention are small additional pieces of fabric sheathing. Preferably the, the use of flaps leads to the protection of the closing sheathing fabric from damage due to abrasion in areas with sharp edges. This ensures a longer service life and higher reliability.

In the next one preferred embodiment, priduzivanja sheathing fabric and/or flaps in the case of wooden structures is carried out at a temperature from 70°C to 110°C. Particularly advantageous application temperature of 90°C. For metallic structures priduzivanja sheathing fabric and/or flaps is carried out preferably at a temperature of from about 130°C to 170°C. This ensures that the dispersion glue hot gluing hardens without shrinkage while sheathing fabric. Since metals in principle are good conductors of heat and, therefore, relatively quickly remove the heat, you can use a slightly higher temperature.

In addition, the preferred method, characterized in that the seams are sealed (seal) tape with the teeth of the sheathing fabric, which coat a dispersion adhesive hot gluing according to one of the preceding paragraphs and then smooth the seam at 60°C-100°C, preferably at 90°C. Preferably, the cover seams dispersion adhesive hot-gluing a width of 4 mm under the tape. Sealing (sealing the W) significantly increases the strength and durability of the joints and thus the entire plating. In addition, the surface of the fuselage and lifting surfaces protected from moisture. Should the lining be salivates, depends on the structural design.

In one of the following preferred embodiment of the method according to the invention is applied to the optional marking of trimmed surfaces colored polyester film by cold bonding and additional proglazhivanija at 80°C. Polyester color film is preferably stable in size, thermostable and/or resistant to fuels. Achieved in this way is durable and individual final surface finish of the plane is easy to apply, and cold bonding prevents undesirable deformation of the existing sheathing.

In the next one preferred embodiment, the invention relates to a dispersion glue hot gluing containing 80-88% binder, 12-15% curing component and 0.15-0.3% thickener, and glue depolimerizuyutza at temperatures of >40°C.

Preferably, the binder contains a variance from linear to often weakly branched polyurethane. In addition, the preferred thickener based on polyurethane, particularly preferably the thickening agent is nonionic.

In addition, the preferred dispersion adhesive hot SCR is the air traffic management, in which curing component contains 54-60% of solvent, of 0.35-0.5% stabilizer based on the sodium salt naphtalenesulfonic acid, 0.25 to 0.35% of the emulsifier on the basis of propoxyethanol alcohol, 1.7 to 1.9% of hardener on the basis of polyetheramine, 37-41% MDI.

The solvent is preferably water is used. The stabilizer based on the sodium salt naphtalenesulfonic acid can be, for example, Tamol NN 4501. As the emulsifier can be used emulsifier FD. Hardener based polyetheramine can be, for example, Jeffamine T403. Preferred aliphatic polyisocyanate, for example, Desmodur LPBUEJ471.

The adhesive according to the invention is particularly advantageous for use in the method according to the invention, since the adhesive is thermally stable and therefore does not dissolve when proglazhivanie sheathing fabric. The adhesive is well suited for all materials light aircraft and has particularly good durability.

In the following embodiment, the invention relates to the use of dispersion adhesive hot gluing according to the invention for covering light aircraft and/or parts.

The following variant embodiment of the invention relates to a light aircraft or part thereof, characterized in that it is sheathed polyester upholstery fabric by the method according to the invention.

An example is

Exemplary embodiment 1.

Plating tail

After positioning the tail the entire frame structure outline in pencil on the inside and the outside of the structure to bear the entire contour of the tail on the inner side of the sheathing fabric. To this point in time is done transfer for both the top side and bottom side. The bottom side is the side, which is covered with the first and which the nose spar is wrapped with a cloth on the corner of 630° (figure 1).

The first 270° internal lining fabric after priduzivanja provide additional layer of glue on the outside to ensure optimal bonding. To select the cut lines for the tail, additionally marked the second line as the outer cut lines. The distance from the cut line to the main line in case of a nose spar is calculated according to the following formula:

Example: diameter (fore spar) = 5 cm

π·d (cm)·1,75=3,14·5 cm·1,75=27,5 see

Thus, the seam allowance on the front edge region is 27.5 see

For allowance of tissue from the tail spar fair the following formula:

Example: diameter (rear spar) = 2 cm

π·d (cm)·0,8=3,14·2 cm·0,8=5 cm

Thus, the seam allowance on the back edge of the region is 5 cm

Marked N. the tissue region from the outer cut lines to the line of the rear end of the spar, as well as areas that overlapped lateral edges and shelves, promazyvaetsya now a dispersion adhesive hot gluing. After drying, glue the fabric cut out. Where when you are wrapping a transverse rib or ribs, the area of the ribs and the ribs are cut. Formed when cutting the strips can pridurivajsja on the rib or transverse ribs as a "flap".

The plating process begins with the nose spar and then continues to the tail spar. For this sheathing cloth wrapped bow spar almost 360° (figure 2). Now you can start proglazhivanie fabric on the inner sides of the nose spar. For simplicity, always start with straight beams. Narrowing upholstered only after fixing the tissue in the tail spar. The fabric is wrapped around the nose spar sheathe patterns and pritagivaut (figure 2). In the area of narrowing the circumference of the nose spar, if necessary, reduced to 270°. Curves, such as wingtips, proglazhivaetsya iron. Because the material can be pulled under the application of heat, when priduzivanja need to grasp the structure of your other hand. Emerging wrinkles are removed by placing increased heating.

Around the area of the tail spar fabric iron on an angle of approximately 270°, in order to have as much area of the fixing other outer pipe iron 270°. When proglazhivanie the upper side of the platen outside of the structure occurs at the angle of circumference of the spar 180°. In addition, for the vertical fin, as for the horizontal tail, first edged bearing surface and all flaps "lower side".

So in the case of tubular design to prevent bonding fabric with myself when proglazhivanie, on the inner side surface proglazhivanii pipe is advanced to transfer patterns fit silicone paper.

Now prepare for covering the vertical tail surfaces. For this purpose it is positioned on the inner side of the fabric and mark the compass in the outer region. The distance from the marking compasses to the pipe for the first glue side equal to the circumference of the pipe + 75% of the circumference of the nasal tube and + 80% in the tail pipe. For the opposite side, it is about 40% of the circumference of the pipe. Then the vertical tail turn and mark the opposite side. Then both cladding vertical tail coat with glue, with pie (circular) markup represents the outer border of the adhesive layer. You need to ensure that all areas of the fabric, which are superimposed on the structure were coated with glue, to ensure a tight fit. After drying, is held open with a seam allowance of about 10-15 cm of vdol the outer circumference. Priduzivanja is carried out according to the above method.

After priduzivanja part, which relies directly on the pipe in the area where the tissue layer rests on a layer of fabric is applied to a dispersive adhesive hot gluing. After drying, iron outer side. Plating iron around the tubular design of 180°, and the tail pipe pritagivaet circumference of 280°. Wrinkles formed in the area of the fillets, you can remove the heat. If not all the wrinkles disappeared, their seat and pull optionally using a hot air gun and elevated temperature until the wrinkles disappear. In this work the fabric after removal of the hot air gun still need to keep some time for the adhesive to cool and to secure the fabric on the base.

Wrinkles that are still there after fixing the cladding is removed using a hot air gun set at a temperature of 350°C. the Temperature of the air entering the fabric, "is regulated by the distance from the fabric: the greater the distance, the colder the temperature load. To control shrinkage of the surface temperature measured with an infrared thermometer. It should not exceed 200°. When pressing the cloth to the structure without burning fingers, it is best to take a felt scraper. To the upper side of pure nautural on the lower side, in the case of the vertical fin n the mid pipe cause the auxiliary point. Tissue tailor in accordance with the marking and pritagivaut.

In the area of bends roughness of the upper side looks and seat high heat. On straight joints, where shrinkage is not required, iron at about 90-100°C (wooden structures). For metal structures, due to the high thermal conductivity may be usable temperature range from 130 to 170°C. to obtain a clean transitions, always with the help of a compass outline auxiliary lines, which are trim edges. Internal auxiliary lines are used to apply the adhesive only in the area where it is needed.

To prevent that the fabric will move, it is placed around the structure and fixed with adhesive tape. After the fabric is cut, it pritagivaut. On the radii, such as wingtips, fabric iron with increased heat and firmly seated.

Labels can be applied using a special film, which after cold gluing additional iron at about 80°C.

Exemplary embodiment 2.

The lining of bearing surfaces

The bearing surface is sheathed in a manner analogous to what was discussed for the tail. First, the structure of the bearing surface is transferred onto the inner side of the fabric. Practical to move the entire structure of the upper and lower sides n the existing surface unwound the cloth fabric. Then it is coated with glue in the marked area. Parallel to this promazyvaetsya adhesive strips, which will then be stripped, and the resulting so-flaps overlap everywhere where there is a rivet, for example, over stickers ribs. All applied patches promazyvaetsya then glue on the top side. After drying glue first sheathe lower side, then the upper side of bearing surfaces. When the plating is also advisable to do so to start with the nose spar and the trim around the nose spar. In places where the fabric is laid on the cloth, put a dispersive adhesive hot gluing. After drying the fabric tight pull on the tail spar and there's also pritagivaut. The circumference of the tail spar should be at least 270°. At the end of this work carrying surface rotates, and sheathed the upper side of the bearing surface in the same manner as already described. Thus it is necessary to watch that very carefully to prithwijit obstacles. On the root rib and the wing tips material pure smooth it around or into the root rib to get the maximum area of attachment for the glue and fabric. Breakthroughs cover is placed on the inner and outer side of the circular reinforcing patches. At the end of the process of pressing the left is iesa pipe wrinkles seat high heat using a hot air gun. If straightening is carried out using a hot air gun, it is recommended to cover the joints with strips of corrugated cardboard to glue because of the high temperature again softened and "delayed" fabric shrinkage. Since the shrinkage of the heat load is not in all places evenly distributed, this process should be repeated 1-2 times. Overlapping should be performed by a width of at least 5 cm (fore spar, rear spar).

Exemplary embodiment 3.

The fuselage skin

The fuselage is covered similarly to the bearing surface. The procedure corresponds to the diagram plating with figure 3. For the skin of the fuselage, you can start with either the fuselage or perifericheskie, with the chassis. Rough cut fabric is attached to the underside of the chassis, for example, adhesive tape, and mark all of the contact surface of the chassis, and fabric. There is also an external cutting line, and the pipe must obthayutsya angle of 270°. All contact places (like on the fabric and on the chassis, promazyvaetsya dispersion adhesive hot gluing. It is advisable to start with covering the bottom side of the chassis. After drying fabric glue specifically made and iron. As has already been described in example 1, the adhesive is applied at all nodal points. After drying smeared with glue fabric nalazhivaetsya in the form of a flap (patches)to prevent that the plating will be damaged the Jena sharp edges.

Dispersion glue hot gluing must be completely dry, before you can sheathe. This process can be accelerated by the gun mounted on the cold air. However, you need to ensure that it was indeed conducted with cold air. The hardener is already in the dispersion glue and reacts with the adhesive at a temperature ranging from about 50°C. This means that if the process is started, the glue will harden and no longer suitable for gluing fabric.

Covering the outer side of the chassis is similar to the hull bottom surface. Thus it is necessary to ensure that the seam allowance (cloth-cloth) before plating was coated a dispersion adhesive hot gluing. To achieve more accurate (net) seams paste over them with duct tape. The adhesive tape is removed before drying glue. All joints and holes increase nalivaeva thermomechanic tape with cloves. You can also handle hard-to-reach places.

The fuselage skin should consist of as fewer individual parts, to have a few joints and seams. First sheathed the lower side of the fuselage. This fabric should bow side shelf (zone) of the fuselage at an angle of approximately 270°. Then the right side of the fuselage is attached in one piece to the fuselage glue the second strip. The structure is transferred onto the fabric. Structural place on the fabric and structure of the fuselage smeared dispersion glue hot glue and left to dry. Then the fabric from front to back iron iron. This way you can also have a good coat and hard to reach areas of the fuselage.

Exemplary embodiment 4.

Preparation of dispersion adhesive

Preparation of liquid hardener

In 100 g of water with slow stirring, 0.7 g of dispersant and stabilizer, 0.5 g of emulsifier and 3.1 g of hardener on the basis of polyetheramine. After homogenization of these components in the solution portions is dispersed 67 g of powdery curing agent based on aliphatic MDI. This should not form any lumps. The solution is gently stirred until homogenization.

Add liquid hardener in the junction

Take 100 g of binder and vmeshivat it 0.3 g of thickener. After homogenization with slow stirring, 15 g of liquid hardener.

Air conditioning adhesive

The adhesive solution is slowly stirred further until there is no longer formed foam. This adhesive solution is finally filtered.

The list of reference positions

11, the upper side (sheathe airplane parts)

12 bottom (sheathe part of the plane)

13 fore spar

14 tail spar

15 adhesive coating

16 the inner side fabric

17 upholstery fabric bottom side of the fuselage

18 upholstery fabric right sides of the fuselage

19 upholstery fabric left side of the fuselage

20 upholstery fabric upper side of the fuselage

21 the fuselage

1. The method of covering light aircraft and/or parts thereof, consisting of a frame system, and a frame or frame parts fit polyester lining fabric, and upholstery fabric has a longitudinal shrinkage of 5-8%, preferably 7%, and a transverse shrinkage of 4-6%, preferably 5%, at 160-180°C, containing the following steps:
a) upholstery fabric in its overhangs, and parts of the frame, which will be upholstery fabric, smear a dispersion adhesive hot gluing and adhesive includes curing component that depolimerizuyutza at the temperature of processing >40°C, and
b) upholstery fabric thus wrapped around the spar of the frame, so that when the destruction of the obtained adhesive connection between the sheathing fabric and frame upholstery fabric held on the frame structure.

2. The method according to claim 1, and curing component dispersion adhesives are hot gluing depolimerizuyutza at temperatures of from 40° to 60°C.

3. The method according to claim 1, and a dispersive adhesive is hot gluing contains 80-88% of the binder, 12-15% curing component and 0.15-0.3% thickener.

4. The method according to claim 1, and curing component contains 54-60% of solvent, of 0.35-0.5% stabilizer based on the sodium salt naphtalenesulfonic acid, 0.25 to 0.35% of the emulsifier on the basis of propoxyethanol alcohol, 1.7 to 1.9% of hardener on the basis of polyetheramine, 37-41% MDI.

5. The method according to claim 1, characterized in that:
a) for covering the tail upholstery fabric cut out so that the overhang (A) trim the edges to coat spar sheathe tail was (A=π·d·x)and (A=π·d·y) from the tail spar the same tail, where d is the diameter of the glue cloth sheathing tube (cm), x=1.5 to 2.0, preferably about 1.75, y=0,55-of 1.05, preferably of 0.8 and
b) the lower side of tail tight by wrapping the nose spar approximately 1.75 turnover (from 550° to 700°) coated with glue part of sheathing fabric and priduzivanja this part, and then wrap the tail spar approximately 0.75 turnover (200°-350°) also missed glue part of sheathing fabric and priduzivanja this part of the identical way, then
c) fit the upper side of the tail by wrapping the nose spar approximately 0.5 turnover (150°-210°) coated with glue part of sheathing fabric and priduzivanja obseve the Noah fabric, while the tail spar wrap then in less than a half-turn (120°-170°) also missed glue part of sheathing fabric and upholstery fabric pritagivaut the same way.

6. The method according to claim 5, and then sheathing fabric seat, warming her one or twice to about 200°C by hot air gun set at a temperature of from 280°C to 380°C, preferably between 350°C and the actual temperature of the tissue is regulated by the distance to the gun.

7. The method according to claim 5, and before wrapping the flaps also coat the dispersion glue hot glue and after drying them nalajivayut on rivets and reinforcement plates to protect the closing of fabric sheathing.

8. The method according to claim 5, characterized in that priduzivanja sheathing fabric and/or flaps in the case of wooden structures is carried out at a temperature from 70°C to 110°C, preferably at 90°C.

9. The method according to claim 5, characterized in that priduzivanja sheathing fabric and/or flaps in the case of metal structures is carried out at a temperature of from about 130°C to 170°C.

10. The method according to one of claims 1 to 9, characterized in that the seams are sealed with tape with the teeth of the sheathing fabric, which is coated with a dispersion adhesive hot gluing under section 12 or 13 and then nalazhivaetsya on the seam at a temperature from 60°C to 100°C, preferably at 90°C.

12. Dispersion glue hot gluing containing 80-88% binder, 12-15% curing component and 0.15-0.3% thickener, and glue depolimerizuyutza at a temperature of >40°C.

13. Dispersion glue for para.12, and curing component contains 54-60% of solvent, of 0.35-0.5% stabilizer based on the sodium salt naphtalenesulfonic acid, 0.25 to 0.35% of the emulsifier on the basis of propoxyethanol alcohol, 1.7 to 1.9% of hardener on the basis of polyetheramine, 37-41% MDI.

14. Application of the dispersion glue hot gluing according to item 12 or 13 for covering light aircraft and/or parts.

15. Light aircraft or part thereof, characterized in that they are covered polyester lining cloth according to the method according to one of claims 1 to 11.



 

Same patents:

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EFFECT: higher strength.

7 dwg

FIELD: chemistry.

SUBSTANCE: composition contains epoxy diane resin, oligoether acrylate, curing agent, initiator and solid filler. The filler is silica gel or aerosil. The initiator is in form of benzoin or dimethoxyphenyl acetophenone ethers. Oligoether acrylate is selected from a group of dimethacrylate ethers. The curing agent used is aliphatic or aromatic diamine and aliphatic or aromatic tertiary amine. The photocurable adhesive composition is obtained by mixing all components until their complete dissolution. The obtained mixture is put between glued surfaces and exposed to UV light for not less than 5 min. Further, thermal post-polymerisation is carried out at temperature not higher than 50°C, followed by cooling and holding. The invention is used in production of organic light-emitting diodes to prolong their service life.

EFFECT: good adhesion to glass, weather resistance, low chemical aggressiveness, high water resistance and crack resistance when pressed between glass plates.

8 cl, 3 tbl, 3 ex

FIELD: chemistry.

SUBSTANCE: aqueous polyurethane dispersion composition contains polyurethane with carbodiimide and/or carboxyl groups, and polyurethane dispersion adhesive which contains polyurethane with carbodiimide and/or carboxyl groups. The polyurethanes are polyester-polyurethane elastomers. The aqueous polyurethane dispersion composition and polyurethane dispersion adhesive also contain at least one carbodiimide which contains at least one carbodiimide group. The aqueous polyurethane dispersion composition and polyurethane dispersion adhesive react with each other through a polyaddition reaction when heated to 50°C or higher. A polymeric film having an undercoating is obtained by depositing and drying the single-component aqueous polyurethane dispersion composition on a polymeric film. A composite is obtained by reacting the polymeric film having an undercoating with a substrate on which polyurethane dispersion adhesive is deposited and dried. The composite can be produced industrially and can be especially used in interior finishing, preferably of a component built into a transportation vehicle or can be used in the furniture industry.

EFFECT: high reliability of the composition.

5 cl, 3 tbl

FIELD: process engineering.

SUBSTANCE: invention relates to mechanical fining of shaped articles by films. Adhesive is applied on shaped article surface and film is applied thereto. Shape article represents a window section. Fining of said section is carried out using polyurethane adhesive PVC film, polyacrylate or poly ether. Note here that said section is heated on applying adhesive on its surface, or adhesive is heated on its application on section surface to at least 40°C. Proposed method allows rejecting pre-processing of section to be fined.

EFFECT: minimised lamination of applied film.

7 cl, 1 ex

FIELD: machine building.

SUBSTANCE: invention refers to fixing devices. Here is disclosed the fixing device with a fixing element consisting of a fixing part with a flat external surface and with thermo-fusible glue melted for binding the fixing element with a holder and joined with the flat external surface of the fixing element and with the holder, thus forming a flat glue binding between them; also the fixing element is equipped with a seat opened in the direction of its flat external surface wherein a pressed part is inserted. A retaining fixture is made in the zone of the seat. According to the first version the retaining fixture corresponds to at least part of a side internal wall of the seat, also the side internal wall of the seat has several ribs protruding radially inside and penetrating or pressed into the pressed part. According to the second version the retaining fixture has several fixing lugs projecting over the bottom of the seat. According to the third version the retaining fixture is formed with a fixing rod transferred in axial direction in the seat; while the pressed part has a hole for this fixing rod inserted into it.

EFFECT: ensuring preliminary assembly of fixing device eliminating melting pressed part out of thermo-fusible glue.

4 cl, 6 dwg

FIELD: construction.

SUBSTANCE: device has working plate with deepenings, lower or bottom surfaces of which are created by upper working surfaces of puncheons, which are pointedly displaced by their sides walls in deepenings in working plate. On working plate, aside from deepenings, there is a displaced reservoir that contains powder glue for filling of deepenings in working plate. As reservoir is being displaced, its side edges slide along working plate flush with its surface. On the other side of deepenings there are sleds arranged in working plate, which serve as support for fastening element placed in them and in which through openings are provided for puncheons extended upwards from working plate. Above deepenings in working plate there is a pressing puncheon with pressing plate lowered onto fastening element. At the distance from sleds there is a position of fastening elements heating prior to their placement into position above deepenings in working plate up to temperature required for sticking or melting of thermomelting glue to them.

EFFECT: method and device make it possible to evenly apply thermomelting glue, to glue surfaces of complex shape and to fully automate the process.

4 cl, 14 dwg

FIELD: wood-working industry; methods of production of the glued woodwork.

SUBSTANCE: the invention is pertaining to the method of production of the glued woodwork and the wooden components. The invention presents the method of production of the glued woodwork or the wooden components with usage of the glue systems. At that application of the glue on the heated wooden details or the wooden components is exercised by the separate application of the glue resin and the curing agent (the binding), or the glue system representing the mixture of the glue resin and the curing agent. Before application of the glue on the wooden details or components execute the uniform heating along the whole cross-section of the wooden details or the wooden components by means of the microwave radiation. The invention also presents the description of application of the method for production of the profile of the massive wood. The technical result of the invention is reduction of the time of pressing of the wooden details and the wooden components, the increased efficiency of the production of the glued structural wooden details and the wooden components.

EFFECT: the invention ensures reduction of the time of pressing of the wooden details and the wooden components, the increased efficiency of the production of the glued structural wooden details and the wooden components.

10 cl, 2 dwg

FIELD: wood-working industry; other industries; methods of the surfaces adhesive bonding.

SUBSTANCE: the invention is pertaining to the field of wood-working industry ,in particular, to the method of joining the surfaces including application of the adhesive bonding composition (A) on the surface of the first detail made out of the material, drying of the dissolvent by the evaporation (partial or complete),by the forced drying with production of the gluten composition (B) containing the solid substances of Х mass % directly after the stage of the drying, application of the component (C) containing the dissolvent having the content of the solid substances of Z mass % - on the surface of the second detail made out of the material. At that Z < X, joining the two surfaces together, so that the gluten composition (A) was in the contact with the component (C), pressing the two surfaces to each other. The invention also is pertaining to the method of production of the products on the basis of the wood.

EFFECT: the invention ensures the reliable adhesive bonding of surfaces.

19 cl, 1 tbl, 4 ex

FIELD: adhesives.

SUBSTANCE: objective of invention is to provide a method for joining two bodies with joint exhibiting elevated heat resistance. Proposed method is liable to be optimized and enables faster creation of joint. To that end, between surfaces to be joined, joining material containing at least one crosslinkable polymer or polymerizable and crosslinkable resin is placed. Surfaces to be interconnected and joining material situated between them are juxtaposed and at least one of the bodies is mechanically affected by at frequency 50 to 400 Hz and amplitude 0.5 to 2 mm to heat the assembly, which allows joining material to be converted into thermally set plastic, which imparts enhanced heat resistance to joint.

EFFECT: increased heat resistance of joint.

16 cl, 8 dwg, 1 tbl

FIELD: chemistry.

SUBSTANCE: invention relates to aldimines of formula (I)

where A does not contain active hydrogen and a primary amine group, or together with R7 denotes a (n+2)-valent hydrocarbon radical containing 3-20 carbon atoms and, if necessary, at least one heteroatom in form of oxygen of an ether group or nitrogen or a tertiary amine group; n equals 1, 2, 3 or 4; m equals 0,1, 2, 3 or 4; R1 and R2 each denotes a univalent hydrocarbon residue with 1-12 carbon atoms or together denote a divalent hydrocarbon radical which is part of a carbocyclic ring with 5-8 carbon atoms; R3 denotes H or alkyl; R4 and R5 independently denote CH3 or a univalent aliphatic radical containing 2-12 carbon atoms and optionally hydroxy groups; X denotes O, S, N-R6, or N-R7, where R6 denotes a univalent hydrocarbon radical containing 1-20 carbon atoms and having at least one hydroxy group; as well as curable compositions containing such aldimines and use of said compositions.

EFFECT: obtaining novel aldimines which can be used as curing agents in curable compositions.

22 cl, 18 ex, 6 tbl

FIELD: chemistry.

SUBSTANCE: present invention relates to a polyisocyanurate based adhesive which is obtained by reacting an organic polyisocyanate with a compound containing hydrogen atoms which are reactive towards isocyanate, in the presence of a trimerisation catalyst. The organic polyisocyanate is a polymer or prepolymer polyisocyanate, and content of the soft block in the adhesive ranges from 40 to 60 wt %. A reaction mixture for producing said adhesive is also described.

EFFECT: obtaining an adhesive capable of withstanding high maximum stress, having extremely fast setting and having a good and strong bond with the base, as well as high thermal stability, resistance to salty water and creep.

9 cl, 4 ex, 6 tbl

Gluing method // 2451040

FIELD: chemistry.

SUBSTANCE: method involves applying a UV curable adhesive resin composition, containing a photolatent base, onto at least one transparent surface of at least one of a first and a second substrate. The substrates are then brought together so that said adhesive composition lies in between. The adhesive composition is then exposed to actinic radiation for curing. The UV curable adhesive is a OH/NCO system or SH/NCO system. In another version of the gluing method, the first and second substrates are brought together after exposing the adhesive composition in between to actinic radiation.

EFFECT: disclosed gluing method enables faster curing of the adhesive.

5 cl, 10 tbl, 6 ex

FIELD: chemistry.

SUBSTANCE: composition contains one or more urethane prepolymers, having isocyanate residues, one or more compounds which catalyse the reaction of isocyanate residues with water or a compound which contains active hydrogen and one or more alpha-hydrocarbyl silane compounds. The urethane propolymer additionally contains a silane functional group. The composition additionally contains a compound or a polymer, containing silane residues. The composition additionally contains one or more compounds which catalyse silanol condensation. The composition is deposited onto the surface of glass or plastic with a coating or onto the surface of a substrate to obtain a sealant, then brought into contact and the composition is then hardened. The composition is placed between the glass or plastic with coating and the substrate. The sealing composition is used for binding an unprimed surface with a coating, such as a window lintel with glass with a transparent plastic, coated with an abrasive-resistant coating or with glass or plastic with a coating, additionally coated with glass cement, such as ceramic or organic glass cement.

EFFECT: improved composition properties.

10 cl, 2 ex

FIELD: chemistry.

SUBSTANCE: invention relates to a method of producing dispersions of blocked polyurethane prepolymers, use of dispersions obtained using said method to produce coating agents, adhesive substances and sealants and elastomers, said application products themselves, as well as substrates provided with coating agents. The method involves the following: I) a blocked polyurethane prepolymer is obtained first by reacting a) 100 equivalent % of at least one polyisocyanate with b) 50-90 equivalent %, in terms of isocyanate reactive groups, of a thermally split blocking agent, c) 5-45 equivalent %, in terms of isocyanate reactive groups, monohydroxycarboxylic acid as a hydrophilic agent and d) 0-25 equivalent %, in terms of isocyanate reactive groups, of polyhydroxycarboxylic acid as a hydrophilic agent and e) 0-15 equivalent %, in terms of isocyanate reactive groups, of at least one, in terms of isocyanate reactive groups, di- or polyfunctional component of a chain extender with molecular weight from 32 to 350 g/mol, where i) this takes place using (partially) water-miscible organic solvents which are inert to NCO-groups and have boiling point lower than 120°C (at 1013 mbar), ii) and they are used in such an amount that the polyurethane prepolymer contained in the reaction solution after complete conversion ranges from 70 to 98 wt %. Further, II) the polyurethane prepolymer solution obtained at step (I) is dispersed in water, where before, during or after dispersion, deprotonation of carboxylic acid groups with a base takes place at least partially, and then III) if needed, the contained organic solvent is completely removed during dispersion via distillation.

EFFECT: obtaining polyurethane dispersions which are stable during storage, endow said products of their application with good optical properties, high resistance to chemical reagents and pendulum hardness.

13 cl, 10 ex, 1 tbl

FIELD: chemistry.

SUBSTANCE: adhesive composition contains perchlorovinyl resin and an organic solvent. The composition contains dichloroethane as an organic solvent, as well as dibutyl phthalate and a modifier in form of epoxy diane resin ED-20 and N-nitrosodiphenylamine, with the following ratio of components in pts.wt: perchlorovinyl resin 20, organic solvent 80.0, dibutyl phthalate 1.0, epoxy diane resin ED-20 10.0-15.0, N-nitrosodiphenylamine 0.33-1.11.

EFFECT: invention increases strength when gluing together vulcanised rubber.

2 tbl

FIELD: chemistry.

SUBSTANCE: adhesive composition contains polychloroprene rubber nairit DP, butyl phenol formaldehyde resin 101 K, water, zinc oxide, magnesium oxide and an organic solvent which is a mixture of ethyl acetate and nefras. The composition additionally contains a modifier obtained first as a result of room temperature-reaction of an aliphatic amine - triethanolamine or polyethylene polyamine and silica filler Rosil R-175, with the following ratio of components, wt %: polychloroprene rubber nairit DP - 90.0, butyl phenol formaldehyde resin 101K - 90.0, water - 3.0, zinc oxide - 5.0, magnesium oxide - 11.0, organic solvent - 800.0, aliphatic amine - 0.1-0.2, silica filler Rosil R-175 - 10.0.

EFFECT: invention increases strength when gluing together vulcanised rubber.

2 tbl

FIELD: chemistry.

SUBSTANCE: invention relates to compositions based on silane-functional polymers, which are suitable for adhesive binding, sealing and coating porous substrates. The composition contains at least one silane-functional polymer, at least one organosilane and at least one organotitanate. The silane-functional polymer is a silane-functional polyurethane polymer or can be obtained through hydrosilylation of polymers, having terminal double bonds. The organosilane contains at least one sulphur atom. The organotitanate has ligands bound to a titanium atom through an oxygen-titanium bond. The ligands are selected from a group consisting of an alkoxy group, a sulphate group, a carboxylate group, a dialkylphosphate group and an acetylacetonate group. Content of the organotitanate in the composition is between 0.1 and 10 wt %. Content of the organosilane in the composition is between 0.1 and 7 wt %. The composition also contains at least one filler, content of which is between 10 and 70 wt %. The composition is used for binding, sealing and coating substrates made from concrete, mortar, brick, tiles, plaster, natural stone such as granite or marble, glass, glass-ceramic, metal or metal alloy, wood, plastic and lacquer.

EFFECT: obtained article, which is bound, sealed or coated using the composition, is a building structure, more specifically a building or civil construction structure; the composition guarantees efficient adhesion to a substrate even after storage in the presence of water.

17 cl, 1 tbl

FIELD: chemistry.

SUBSTANCE: foamed material consists of a single-component, moisture-curable composition containing at least one polymer P, having isocyanate groups and/or alkoxy silane groups, 10-60 vol. % of at least one gas and 10-30 wt % soot per total weight of the single-component foamed material which is curable in a moist medium. Application of the obtained foamed material is carried out primarily at temperature in the range of 10-40°C. The degree of foaming of the composition and, consequently, gas content of the single-component, moisture-curable foamed material varies during its application.

EFFECT: obtaining single-component, moisture-curable foamed material which can be used as an adhesive or a sealant/packing material for producing coatings or filling hollow structures with foamed material, particularly vehicles.

20 cl, 4 dwg, 1 ex

FIELD: chemistry.

SUBSTANCE: present invention relates to a single-component primer composition for substrates made from glass and/or plastic, having setting time of at least 1 month. Said composition includes: a base primer composition including (a) an isocyanate functional prepolymer derived from the reaction of an aliphatic polyisocyanate and a polyol, and which is partially reacted with an amino group of a secondary aminosilane, wherein the aminosilane includes two or three methoxy groups bound to a silicon atom, two or three ethoxy groups bound to a silicon atom, or a combination thereof; (b) an isocyanate functional prepolymer with an isocyanate content greater than 1%, which is the reaction product of an aromatic polyisocyanate and a polyol of Mn>300; and (c) at least one solvent for the components (a) and (b); and an ingredient including an oxazolidine ring or derivative thereof; a second adduct (i) of an aromatic polyisocyanate and (ii) mercaptosilane, aminosilane or both; a film-forming polymer. The invention also describes glued structure having a glass or plastic panel, containing the said composition, a method of gluing the glass panel to the frame of a vehicle, comprising a step for applying said composition and a glued structure made using said method.

EFFECT: obtaining primer with long setting time, which exhibits excellent stability during storage, during application of which the surface does not swell.

13 cl, 4 tbl

FIELD: transport.

SUBSTANCE: invention relates to aircraft building and concerns assembly technique of aeroplane units panels, in particular to aeroplane centre-section assembly technique. Method for assembling panels of aeroplane units includes assembling and riveting of specifically curved covering and straight stringers. Before assembling and riveting, stringers are preliminary shaped on loft with introducing deflection with advance of 3.0 mm to 5.0 mm and then strengthened on knock-drum device. Produced panels are used to perform assembling of aeroplane units.

EFFECT: improved quality of assembling and providing specified geometrical parameters of riveted panels.

2 dwg

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