CN102029248B - Method for spraying alarm identification on surface of heating part or equipment component of airplane - Google Patents

Abstract

A method for spraying and burning warning signs on the surface of aircraft heating parts or equipment components, comprising the following steps: 1) treating the surface of the aircraft on which the warning signs are to be sprayed, so as to form a glyph surface on the surface of the aircraft, and A plurality of colored depressions are formed on the surface of the glyph; 2) spraying encapsulated reversible thermochromic pigments on the surface of the glyph, so that the encapsulated pigment capsule particles are filled in the colored depressions on the surface of the glyph; 3) sintering the font surface; 4) after sintering, coat the protective film layer on the font surface; 5) carry out secondary sintering to the font surface, after the secondary sintering, apply the coated The glyph surface of the cover is smoothed. The warning words sprayed by the method can directly reflect the surface temperature state of the heating part of the aircraft or equipment components, thereby preventing operators from being scalded.

Description

Method of spraying warning signs on aircraft heating part or equipment component surface

technical field

The invention relates to a warning sign on the surface of an aircraft heating part or equipment component, in particular to a heat-sensitive warning sign on an aircraft pitot tube, and the warning sign can be used to display the surface temperature state of the pitot tube.

Background technique

Some equipment components of the aircraft, such as the pitot tube, are equipped with an anti-icing heating device, which plays a heating and anti-icing function during the flight of the aircraft. When the aircraft is on the ground, or before the aircraft takes off, or when the aircraft is inspected on the ground, the pitot tube of the aircraft needs to be heated. The surface temperature of the heated pitot tube can reach above 200°C.

When the pitot tube is heated on the ground, its surface temperature will become very high, and if the operator is not careful, it will cause accidental burns to the operator. In addition, too high surface temperature of the pitot will cause the pitot protective cover to be burned, or the pitot adapter to be burned during the atmospheric test.

In the prior art, warning signs such as "heating probe" are usually written on the skin next to the pitot tube. However, such a warning label cannot directly reflect the surface temperature state of the pitot tube. This will make the operator overly careful to operate when the pitot surface is not heated, but be careless when the pitot surface is heated and be accidentally burned.

Contents of the invention

The purpose of the present invention is to provide a method for spraying warning signs on the surface of aircraft heating parts or equipment parts, the warning signs sprayed by this method can directly reflect the temperature state of the surface to be sprayed.

In order to achieve the above object, the present invention provides a method for spraying and burning warning signs on the surface of aircraft heating parts or equipment parts, the method comprises the following steps:

1) Treat the surface of the heating part or equipment part of the aircraft on which the warning signs are to be sprayed, so as to form a glyph surface on the surface of the aircraft, and form a plurality of colored depressions on the glyph surface;

2) spraying the encapsulated reversible thermochromic pigment on the surface of the glyph, so that the capsule particles of the encapsulating pigment are filled in the colored depressions on the surface of the glyph;

3) sintering the font surface;

4) after sintering, coat the protective film layer on the surface of the font;

5) Carrying out secondary sintering on the surface of the font, and grinding the coated font surface after the secondary sintering.

Particularly, in the step 1), after forming the glyph surface, an inner groove structure is opened in the cross section of the glyph, and a plurality of colored depressions are formed at the bottom of the inner groove structure. Through such a structural setting, after the outermost protective film layer is solidified, it and the warning signs can be more firmly embedded in the interior of the surface to be sprayed, so as to better overcome the wear of high-speed airflow.

In particular, in the step 2), before the color-changing pigment is sprayed, an auxiliary agent is added to the reversible thermochromic pigment and the protective film layer. More particularly, the auxiliary agents are leveling agents, defoamers and curing agents.

In particular, after the above step 3) is completed, thermal conductive silica gel is coated on the bottom of the inner tank structure. The role of thermal silica gel is to transfer the heat from the temperature measuring surface to the heat-sensitive color-changing coating more evenly, and act as a heat conduction buffer, and the temperature sensitivity can be adjusted by changing the thickness and composition of thermal silica gel.

In particular, the protective film layer is a composite protective film layer. More particularly, the composite protective film layer is made of epoxy polyester resin. More particularly, ceria and/or neodymium oxide are added to the epoxy polyester resin.

In particular, the color-changing pigment is methenamine, xylene (chemically pure), alkyd varnish or pyrophyllite powder.

In particular, the capsule particles are spherical.

In particular, the warning sign is a warning word, a warning graphic and/or a warning symbol.

The warning sign manufactured by the method of the present invention can directly reflect the temperature state of the aircraft surface through the reversible thermochromic pigment therein, because the selected reversible thermochromic pigment corresponds to the temperature condition that the aircraft surface needs to be in an alarm state. Therefore, when the surface temperature of the aircraft heating part or equipment part is high enough to warn, the warning sign will change color, thereby reminding the operator, thereby preventing the operator from being scalded, the protective cover being burned, and the pitot tube being damaged during the atmospheric test. The adapter was burned.

Description of drawings

Fig. 1 is a schematic diagram of the use of the warning sign of the present invention;

Fig. 2 is a schematic diagram of the font surface of the warning sign of the present invention;

Fig. 3 is a schematic diagram of the font cross-section of the warning sign of the present invention, at this moment, the warning sign has been sprayed and burned on the surface of the aircraft.

Detailed ways

The warning sign described in the present invention may be a warning word, a warning figure or a warning symbol, or a combination of these kinds of warning signs. The warning sign 1 can be sprayed and burned on the surface of aircraft heating parts or equipment parts. As shown in FIG. On the surface of the heating part of the pitot tube.

In a method embodiment of the present invention, the aircraft heating equipment part is the pitot tube of the aircraft, and the method for spraying and burning the warning sign includes the following steps:

1) process the aircraft pitot surface 2 on which the warning sign is to be sprayed, to form a glyph surface 12 on the aircraft pitot surface 2, and form a plurality of colored depressions 11 on the glyph surface;

2) Spraying the reversible thermochromic pigment 3 of spherical capsules on the surface 2 of the font, so that the capsule particles 8 of the wrapped pigment are filled in the colored depressions 11 on the surface of the font, wherein the The color-changing pigment 3 can be urotropine, xylene (chemically pure), alkyd varnish or pyrophyllite powder;

3) sintering the font surface 12;

4) after sintering, coat the protective film layer 4 on the font surface 12;

5) Carrying out secondary sintering on the surface 12 of the font, and grinding the coated surface 12 of the font after the secondary sintering.

In another method embodiment of the present invention, its steps are basically the same as the previous embodiment, but, in said step 1), after forming said glyph surface 12, an inner groove structure 5 is opened in the glyph cross section , and a plurality of colored depressions 11 are formed at the bottom of the inner groove structure 5 . Coat the bottom of the inner tank structure with heat-conducting silica gel 6 .

In the step 2), before the color-changing pigment 3 is sprayed, an auxiliary agent is added to the reversible thermochromic pigment 3 and the protective film layer 4 . More particularly, the auxiliary agents are leveling agents, defoamers and curing agents.

In another method embodiment of the present invention, the protective film layer 4 is a composite protective film layer, and the composite protective film layer is made of epoxy polyester resin. Also, ceria and/or neodymium oxide are added to the epoxy polyester resin.

Fig. 3 shows an embodiment of the warning sign of the present invention. In this embodiment, an inner groove structure 5 is opened in the cross-section of the warning sign, and a temperature-changing pigment layer 7 is arranged at the bottom of the inner groove structure 5 . The temperature-changing pigment layer includes a plurality of colored depressions 11, each of which is filled with spherical capsule particles 8 containing a reversible thermochromic pigment 3.

As shown in FIG. 2 , in another embodiment of the present invention, a heat conducting layer is further provided at the bottom of the inner tank structure. The heat conduction layer is made of heat conduction silicone. A protective film layer is also coated on the temperature-changing pigment layer.

In another embodiment of the warning sign of the present invention, the protective film layer 4 is a composite protective film layer, and the composite protective film layer is made of epoxy polyester resin. Also, ceria and/or neodymium oxide are added to the epoxy polyester resin. In addition, the color-changing pigment can be methenamine, xylene (chemically pure), alkyd varnish or pyrophyllite powder.

The technical content and technical characteristics of the present invention have been disclosed above, but it can be understood that under the creative idea of the utility model, those skilled in the art can make various changes and improvements to the above structure, but all belong to the protection scope of the present invention. The description of the above embodiments is illustrative rather than restrictive, and the protection scope of the present invention is determined by the claims.

Claims (12)

1. A method for spraying and burning warning signs on the surface of aircraft heating parts or equipment parts, is characterized in that, comprises the steps: 1) Treat the surface of the aircraft heating part or equipment part on which the warning signs are to be sprayed, so as to form a glyph surface on the surface of the aircraft heating part or equipment part, and form a plurality of colored depressions on the glyph surface; 2) Spraying the encapsulated reversible thermochromic pigment on the surface of the glyph, so that the capsule particles that wrap the pigment are filled in the colored depressions on the surface of the glyph; 3) sintering the font surface; 4) after sintering, coat the protective film layer on the surface of the font; 5) Carrying out secondary sintering on the surface of the font, and grinding the coated font surface after the secondary sintering. 2. method as claimed in claim 1, is characterized in that, in described step 1) in, after forming described glyph surface, in glyph section, be provided with inner groove structure, and form at the bottom of this inner groove structure Multiple colored depressions. 3. The method according to claim 1, characterized in that, in the step 2), before the color-changing pigment is sprayed, an auxiliary agent is added to the reversible thermochromic pigment and the protective film layer. 4. method as claimed in claim 3, is characterized in that, described auxiliary agent is leveling agent, defoamer and curing agent. 5. The method according to claim 2, characterized in that, after step 3) is completed, thermal conductive silica gel is coated on the bottom of the inner tank structure. 6. The method according to any one of claims 1-5, wherein the protective film layer is a composite protective film layer. 7. The method of claim 6, wherein the composite protective film layer is made of epoxy polyester resin. 8. The method according to claim 7, characterized in that ceria and/or neodymium oxide are added to the epoxy polyester resin. 9. The method according to any one of claims 1-5, wherein the color-changing pigment is urotropine, xylene (chemically pure), alkyd varnish or pyrophyllite powder. 10. The method according to any one of claims 1-4, wherein the capsule particles are spherical. 11. The method according to any one of claims 1-4, characterized in that the equipment component is a pitot tube of an aircraft. 12. The method according to any one of claims 1-4, wherein the warning identifier is a warning word and/or a warning symbol.

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