CN103496249B - A kind of preparation method of aircraft straining isolated layer - Google Patents
A kind of preparation method of aircraft straining isolated layer Download PDFInfo
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- CN103496249B CN103496249B CN201310456036.6A CN201310456036A CN103496249B CN 103496249 B CN103496249 B CN 103496249B CN 201310456036 A CN201310456036 A CN 201310456036A CN 103496249 B CN103496249 B CN 103496249B
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Abstract
The invention discloses the preparation method of the anti-heat insulation shell of a kind of aircraft multilayer, belong to technical field of composite materials.The method comprises the step of spray primary coat glue, assembling, silicon rubber mixing, injecting glue preparation, injecting glue, sulfuration, the demoulding.The aircraft straining isolated layer that the method is prepared prevents aircraft titanium alloy shell and heat shield from departing from.
Description
Technical field
The invention belongs to technical field of composite materials, be specifically related to the preparation method of the anti-heat insulation shell of a kind of aircraft multilayer.
Background technology
Aircraft carries out maneuvering flight on a large scale in endoatmosphere, and environment when its working environment belongs to comparatively typical middle temperature, length is navigated, large area region temperature, at about 1300 DEG C, therefore, has the anti-thermal insulation layer of one deck at titanium alloy shell outer surface.And the heat shield thermal coefficient of expansion of composite is at high temperature negative value, the linear expansion coefficient of titanium alloy shell be at high temperature on the occasion of, both differences are larger.At high operating temperatures, the differential expansion of bi-material is comparatively large, can there is certain stress, cause titanium alloy shell and heat shield to depart from.
Summary of the invention
The object of the invention is solve the problem and provide a kind of aircraft straining isolated layer that can prevent aircraft titanium alloy shell and heat shield from departing from.
The technical solution adopted in the present invention is:
A preparation method for aircraft straining isolated layer, comprises the following steps:
(1) between aircraft casing outer surface and heat shield inner surface, spray primary coat glue, evenly, spraying number of times is twice, and interval time is 10min ~ 15min in spraying;
(2) described aircraft casing and described heat shield are assemblied on mould, between described aircraft casing and described heat shield, leave gap;
(3) silicon rubber is carried out deaeration process in vacuum drying oven;
(4) silicon rubber step (3) obtained loads in RTM glue-injection machine, is connected by described RTM glue-injection machine with described mould;
(5) under 0.1MPa pressure condition, carry out injecting glue, described silicon rubber is injected into the gap between described aircraft casing and described heat shield;
(6), after injecting glue completes, described mould is separated with described RT glue-injection machine;
(7) described mould is put into baking oven and carry out sulfuration, described sulfuration system is: from room temperature to 100 DEG C in 1h, at 100 DEG C of insulation 2h; 70 DEG C are cooled to from 100 DEG C;
(8) after sulfuration completes, mould is opened, aircraft casing is taken out, and cuts the overlap of silicon rubber 5, obtain aircraft straining isolated layer.
Further, in described step (1), with low-pressure spray gun, described primary coat glue is sprayed between aircraft casing outer surface and heat shield inner surface.
Preferably, the quantity for spray of described primary coat glue is 50g/m
2.
Further, in described step (2), described aircraft casing and described heat shield are assemblied on mould and need sealing.
Further, in described step (4), with RTM glue-injection machine described in connection by metal hose and described mould.
Preferably, the material of described aircraft casing is titanium alloy.
Preferably, the model of described primary coat glue is HS5210.
Preferably, the model of described silicon rubber is HS1213.
The present invention has the following advantages:
The straining isolated layer that the present invention prepares can effectively prevent aircraft titanium alloy shell and heat shield from departing from, the method of one deck elastomeric isolation layer is made between metal shell and heat shield, metal level and heat shield are bonded together, at high temperature by the elastic deformation of straining isolated layer, coordinate the differential expansion of metal shell and heat shield, make both unanimously be in adhering state, ensure that the normal operation circumstances of aircraft.
Accompanying drawing explanation
The structural representation of the preparation method of a kind of aircraft straining isolated layer that Fig. 1 provides for the embodiment of the present invention 1.
Detailed description of the invention
Below in conjunction with drawings and embodiments, the present invention is further detailed explanation.
Embodiment 1
With reference to Fig. 1, present embodiments provide a kind of preparation method of aircraft straining isolated layer, comprise the following steps:
(1) between aircraft casing 1 outer surface and heat shield 2 inner surface, spray primary coat glue with low-pressure spray gun, evenly, spraying number of times is twice, and interval time is 15min, and the quantity for spray of primary coat glue is 50g/m in spraying
2, the material of aircraft casing 1 is titanium alloy, and the model of primary coat glue is HS5210.
(2) aircraft casing 1 and heat shield 2 are assemblied on mould 3, seal between three, between aircraft casing 1 and heat shield 2, leave gap; Leaving gap between aircraft casing 1 and heat shield 2 is to be injected in gap by the silicon rubber 4 of later step.
(3) silicon rubber 4 glue is carried out deaeration process in vacuum drying oven, the model of silicon rubber is HS1213.
(4) silicon rubber 4 that step (3) obtains is loaded in RTM glue-injection machine 5, RTM glue-injection machine 5 is connected with mould 3 metal hose 6; With metal hose 6 connecting mold 3 and RT glue-injection machine 5, can ensure that silicon rubber 4 does not produce corrosion to metal hose 6.
(5) under 0.1MPa pressure condition, carry out injecting glue, silicon rubber 4 is injected into the gap between aircraft casing 1 and heat shield 2.
(6), after injecting glue completes, mould 3 is separated with RT glue-injection machine 5.
(7) mould 3 is put into baking oven and carry out sulfuration, sulfuration system is: from room temperature to 100 DEG C in 1h, at 100 DEG C of insulation 2h; 70 DEG C are cooled to from 100 DEG C; Adopt this step of sulfuration can ensure that the various physics and chemistry parameters of the aircraft straining isolated layer obtained are in.
(8) after sulfuration completes, mould 3 is opened, aircraft casing 1 is taken out, and cut the overlap of silicon rubber 4, obtain aircraft straining isolated layer.
Embodiment 2
Present embodiments provide a kind of preparation method of aircraft straining isolated layer, comprise the following steps:
(1) between aircraft casing 1 outer surface and heat shield 2 inner surface, spray primary coat glue with low-pressure spray gun, evenly, spraying number of times is twice, and interval time is 10min, and the quantity for spray of primary coat glue is 50g/m in spraying
2, the material of aircraft casing 1 is titanium alloy, and the model of primary coat glue is HS5210.
(2) aircraft casing 1 and heat shield 2 are assemblied on mould 3, seal between three, between aircraft casing 1 and heat shield 2, leave gap; Leaving gap between aircraft casing 1 and heat shield 2 is to be injected in gap by the silicon rubber 4 of later step.
(3) silicon rubber 4 glue is carried out deaeration process in vacuum drying oven, the model of silicon rubber is HS1213.
(4) silicon rubber 4 that step (3) obtains is loaded in RTM glue-injection machine 5, RTM glue-injection machine 5 is connected with mould 3 metal hose 6; With metal hose 6 connecting mold 3 and RT glue-injection machine 5, can ensure that silicon rubber 4 does not produce corrosion to metal hose 6.
(5) under 0.1MPa pressure condition, carry out injecting glue, silicon rubber 4 is injected into the gap between aircraft casing 1 and heat shield 2.
(6), after injecting glue completes, mould 3 is separated with RT glue-injection machine 5.
(7) mould 3 is put into baking oven and carry out sulfuration, sulfuration system is: from room temperature to 100 DEG C in 1h, at 100 DEG C of insulation 2h; 70 DEG C are cooled to from 100 DEG C; Adopt this step of sulfuration can ensure that the various physics and chemistry parameters of the aircraft straining isolated layer obtained are in the best.
(8) after sulfuration completes, mould 3 is opened, aircraft casing 1 is taken out, and cut the overlap of silicon rubber 4, obtain aircraft straining isolated layer.
Embodiment 3
Present embodiments provide a kind of preparation method of aircraft straining isolated layer, comprise the following steps:
(1) between aircraft casing 1 outer surface and heat shield 2 inner surface, spray primary coat glue with low-pressure spray gun, evenly, spraying number of times is twice, and interval time is 11min, and the quantity for spray of primary coat glue is 50g/m in spraying
2, the material of aircraft casing 1 is titanium alloy, and the model of primary coat glue is HS5210.
(2) aircraft casing 1 and heat shield 2 are assemblied on mould 3, seal between three, between aircraft casing 1 and heat shield 2, leave gap; Leaving gap between aircraft casing 1 and heat shield 2 is to be injected in gap by the silicon rubber 4 of later step
(3) silicon rubber 4 glue is carried out deaeration process in vacuum drying oven, the model of silicon rubber is HS1213.
(4) silicon rubber 4 that step (3) obtains is loaded in RTM glue-injection machine 5, RTM glue-injection machine 5 is connected with mould 3 metal hose 6; With metal hose 6 connecting mold 3 and RT glue-injection machine 5, can ensure that silicon rubber 4 does not produce corrosion to metal hose 6
(5) under 0.1MPa pressure condition, carry out injecting glue, silicon rubber 4 is injected into the gap between aircraft casing 1 and heat shield 2.
(6), after injecting glue completes, mould 3 is separated with RT glue-injection machine 5.
(7) mould 3 is put into baking oven and carry out sulfuration, sulfuration system is: from room temperature to 100 DEG C in 1h, at 100 DEG C of insulation 2h; 70 DEG C are cooled to from 100 DEG C; Adopt this step of sulfuration can ensure that the various physics and chemistry parameters of the aircraft straining isolated layer obtained are in the best.
(8) after sulfuration completes, mould 3 is opened, aircraft casing 1 is taken out, and cut the overlap of silicon rubber 4, obtain aircraft straining isolated layer.
The straining isolated layer that the present invention prepares can effectively prevent aircraft titanium alloy shell and heat shield from departing from, aircraft casing 1 and heat shield 2 between make the method for one deck elastomeric isolation layer, aircraft casing 1 and heat shield 2 are bonded together, at high temperature by the elastic deformation of straining isolated layer, the differential expansion of coordinated flight device housing 1 and heat shield 2, make both unanimously be in adhering state, ensure that the normal operation circumstances of aircraft.
It should be noted last that, above embodiment is only in order to illustrate technical scheme of the present invention and unrestricted, although with reference to preferred embodiment to invention has been detailed description, those of ordinary skill in the art is to be understood that, can modify to technical scheme of the present invention or equivalent replacement, and not departing from the spirit and scope of technical solution of the present invention, it all should be encompassed in the middle of right of the present invention.
Claims (8)
1. a preparation method for aircraft straining isolated layer, is characterized in that, comprises the following steps:
(1) between aircraft casing outer surface and heat shield inner surface, spray primary coat glue, evenly, spraying number of times is twice, and interval time is 10min ~ 15min in spraying;
(2) described aircraft casing and described heat shield are assemblied on mould, between described aircraft casing and described heat shield, leave gap;
(3) silicon rubber is carried out deaeration process in vacuum drying oven;
(4) silicon rubber step (3) obtained loads in RTM glue-injection machine, is connected by described RTM glue-injection machine with described mould;
(5) under 0.1MPa pressure condition, carry out injecting glue, described silicon rubber is injected into the gap between described aircraft casing and described heat shield;
(6), after injecting glue completes, described mould is separated with described RTM glue-injection machine;
(7) described mould is put into baking oven and carry out sulfuration, described curing temperature is: from room temperature to 100 DEG C in 1h, at 100 DEG C of insulation 2h; 70 DEG C are cooled to from 100 DEG C;
(8) after sulfuration completes, mould is opened, aircraft casing is taken out, and cuts the overlap of silicon rubber, obtain aircraft straining isolated layer.
2. the preparation method of aircraft straining isolated layer according to claim 1, is characterized in that, in described step (1), is sprayed between aircraft casing outer surface and heat shield inner surface by described primary coat glue with low-pressure spray gun.
3. the preparation method of aircraft straining isolated layer according to claim 2, is characterized in that, the quantity for spray of described primary coat glue is 50g/m
2.
4. the preparation method of aircraft straining isolated layer according to claim 1, is characterized in that, in described step (2), described aircraft casing and described heat shield is assemblied on mould and needs sealing.
5. the preparation method of aircraft straining isolated layer according to claim 1, is characterized in that, in described step (4), with RTM glue-injection machine described in connection by metal hose and described mould.
6. the preparation method of aircraft straining isolated layer according to claim 1, is characterized in that, the material of described aircraft casing is titanium alloy.
7. the preparation method of aircraft straining isolated layer according to claim 1, is characterized in that, the model of described primary coat glue is HS5210.
8. the preparation method of aircraft straining isolated layer according to claim 1, is characterized in that, the model of described silicon rubber is HS1213.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310456036.6A CN103496249B (en) | 2013-09-29 | 2013-09-29 | A kind of preparation method of aircraft straining isolated layer |
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| CN201310456036.6A CN103496249B (en) | 2013-09-29 | 2013-09-29 | A kind of preparation method of aircraft straining isolated layer |
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| CN103496249B true CN103496249B (en) | 2015-07-29 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106547965A (en) * | 2016-10-31 | 2017-03-29 | 湖北航天技术研究院总体设计所 | A kind of temperature barrier of hypersonic gliding class aircraft |
| CN112829342B (en) * | 2020-12-31 | 2022-09-13 | 湖北三江航天红阳机电有限公司 | Forming method of aircraft special-shaped cabin heat-proof layer and heat-proof layer |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| DE102007008988A1 (en) * | 2007-02-23 | 2008-08-28 | Airbus Deutschland Gmbh | Hull of an aircraft or spacecraft and a corresponding aerospace vehicle |
| DE102009015590A1 (en) * | 2009-03-30 | 2010-10-07 | Airbus Deutschland Gmbh | Aircraft with an insulation system for heat and sound insulation |
| CN101648598B (en) * | 2009-09-10 | 2011-06-22 | 国营江北机械厂 | Novel inorganic thermal protection structure and manufacturing method thereof |
| CN102519318B (en) * | 2011-12-02 | 2014-09-10 | 国营红阳机械厂 | Molding method for reducing debonding phenomena of composite structure cabin |
| CN202329435U (en) * | 2011-12-04 | 2012-07-11 | 国营红阳机械厂 | Multilayer-structured heat-insulating integrated cabin section |
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