CN115231000A - Heat insulation method for space carrier - Google Patents
Heat insulation method for space carrier Download PDFInfo
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- CN115231000A CN115231000A CN202211140560.8A CN202211140560A CN115231000A CN 115231000 A CN115231000 A CN 115231000A CN 202211140560 A CN202211140560 A CN 202211140560A CN 115231000 A CN115231000 A CN 115231000A
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- 238000009413 insulation Methods 0.000 title claims abstract description 139
- 238000000034 method Methods 0.000 title claims abstract description 49
- 239000010410 layer Substances 0.000 claims abstract description 136
- 239000003292 glue Substances 0.000 claims abstract description 34
- 239000000853 adhesive Substances 0.000 claims abstract description 12
- 230000001070 adhesive effect Effects 0.000 claims abstract description 12
- 239000011248 coating agent Substances 0.000 claims abstract description 12
- 238000000576 coating method Methods 0.000 claims abstract description 12
- 239000011247 coating layer Substances 0.000 claims abstract description 11
- 239000003973 paint Substances 0.000 claims abstract description 9
- 238000005507 spraying Methods 0.000 claims abstract description 9
- 239000002184 metal Substances 0.000 claims description 37
- 229910052751 metal Inorganic materials 0.000 claims description 37
- 239000011324 bead Substances 0.000 claims description 5
- 238000007789 sealing Methods 0.000 claims description 5
- 238000004026 adhesive bonding Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 125000006850 spacer group Chemical group 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 abstract description 15
- 239000012790 adhesive layer Substances 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 239000007799 cork Substances 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 229910001220 stainless steel Inorganic materials 0.000 description 3
- 239000010935 stainless steel Substances 0.000 description 3
- 239000011521 glass Substances 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000011152 fibreglass Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000010453 quartz Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- NDKWCCLKSWNDBG-UHFFFAOYSA-N zinc;dioxido(dioxo)chromium Chemical compound [Zn+2].[O-][Cr]([O-])(=O)=O NDKWCCLKSWNDBG-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Health & Medical Sciences (AREA)
- Critical Care (AREA)
- Emergency Medicine (AREA)
- General Health & Medical Sciences (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Thermal Insulation (AREA)
Abstract
The embodiment of the application provides a spacecraft heat insulation method and a spacecraft, wherein the spacecraft heat insulation method comprises the following steps: spraying primer on the surface of the cabin shell to form a primer layer; spraying antistatic paint on the primer layer to form an antistatic paint layer; coating adhesive glue on the antistatic coating layer to form an adhesive glue layer; and bonding a heat insulation blanket on the bonding glue layer to form a heat insulation felt layer. According to the heat insulation method for the spacecraft and the spacecraft, the multilayer structure of the heat insulation felt layer and the anti-static layer is adopted, so that the adaptability of the heat insulation structure is improved, and the effect of multilayer heat protection is achieved.
Description
Technical Field
The application relates to the technical field of space vehicles, in particular to a heat insulation method for a space vehicle and the space vehicle.
Background
The tail engine of the carrier rocket can cause the bottom of the rocket to bear severe thermal environment during combustion, and in order to ensure the working environment of internal instruments of the rocket body structure and avoid the reduction of material performance caused by temperature rise, thermal protection measures need to be taken on the outer side of the rocket body structure.
The conventional thermal protection measures usually adopt coating spraying or cork thermal protection, and are mainly applied to large carrier rocket fairing, the cork thermal protection structure needs to be divided into smaller blocks for pasting when being installed, the process is complex, the requirement on the smoothness of the outer surface of the cabin section is high, and if the bolt head protrusion needs special treatment, the cork thermal protection structure has poor adaptability.
Disclosure of Invention
In order to solve one of the technical defects, the embodiment of the application provides an aerospace vehicle and an insulation method thereof.
According to a first aspect of embodiments of the present application, there is provided a method of insulating an aerospace vehicle, comprising: spraying primer on the surface of the cabin shell to form a primer layer; spraying an antistatic coating on the primer layer to form an antistatic coating layer; coating adhesive glue on the antistatic coating layer to form an adhesive glue layer; and bonding a heat insulation blanket on the bonding glue layer to form a heat insulation felt layer.
By adopting the heat insulation method for the spacecraft, provided by the embodiment of the application, the heat insulation felt layer is of a flexible structure by adopting the heat insulation structure of the multilayer structure based on the heat insulation felt layer, so that the adaptability of the heat insulation structure is improved, and the effect of multilayer heat protection is achieved.
In the above technical solution, the spacecraft thermal insulation method further comprises: arranging a connecting hole on the heat insulation felt layer; and a fastener penetrates through the connecting hole to connect the heat insulation felt layer and the shell.
In the above technical solution, the method for insulating heat of a spacecraft further comprises: laying metal pressing strips on the edges of the heat insulation felt layer; and a fastener penetrates through the connecting hole to connect the metal pressing strip, the heat insulation felt layer and the shell.
In the above technical solution, the method for insulating heat of a spacecraft further comprises: and coating waterproof and heat-proof glue on the outer surfaces of the fastening piece and the metal pressing strip.
In the above technical solution, the spacecraft thermal insulation method further includes: a gasket is disposed on the fastener such that the gasket compresses the insulation blanket.
In the above technical solution, the distance between two adjacent connection holes is 250 mm to 350 mm.
In the above technical solution, the spacecraft thermal insulation method further includes: an avoidance gap is formed in the heat insulation felt layer; laying a metal pressing strip on the edge of the avoiding notch; laying a gasket on the metal pressing strip; the gasket, the metal bead, the heat insulating felt layer and the outer shell are connected by a fastener.
In the above technical solution, the method for insulating the space vehicle further includes: arranging avoidance holes on the heat insulation felt layer; and performing edge sealing or gluing treatment on the avoiding hole.
In the above technical solution, the method for insulating heat of a spacecraft is characterized by further comprising: before the thermal insulation blanket is bonded on the bonding glue layer, the thermal insulation blanket is soaked in waterproof glue to form a waterproof layer on the surface of the thermal insulation blanket.
According to a second aspect of embodiments herein there is provided an aerospace vehicle comprising: a deck section housing; and carrying out heat insulation treatment on the cabin shell by adopting any one of the heat insulation methods of the space carrier, so that a heat insulation structure formed on the cabin shell comprises a primer layer, an anti-static coating layer, a bonding glue layer and a heat insulation felt layer which are sequentially attached to each other.
Adopt the space carrier that provides in this application embodiment, through adopting space carrier thermal insulation structure, through adopting the multilayer structure's that can prevent static thermal insulation structure based on thermal insulation felt layer, thermal insulation felt layer is flexible structure, has improved thermal insulation structure's adaptability, has played the effect of multilayer thermal protection.
Drawings
The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the application and together with the description serve to explain the application and not to limit the application. In the drawings:
FIG. 1 is a flow chart of a method of insulating an aerospace vehicle according to an embodiment of the present application;
FIG. 2 is a flow chart of a method of insulating an aerospace vehicle as provided herein based on the embodiment of FIG. 1;
FIG. 3 is a flow chart of a method of insulating an aerospace vehicle according to another embodiment of the disclosure;
FIG. 4 is a flow chart of a method of insulating an aerospace vehicle according to yet another embodiment of the present application;
FIG. 5 is a flow chart of a method of insulating an aerospace vehicle according to yet another embodiment of the present application;
FIG. 6 is a schematic longitudinal cross-sectional structural view of an aerospace vehicle insulation structure provided in accordance with an embodiment of the present application;
FIG. 7 is a schematic illustration of a top view of an aerospace vehicle insulation provided in accordance with an embodiment of the disclosure;
fig. 8 is a schematic top view of an aerospace vehicle insulation structure according to another embodiment of the present disclosure.
Description of reference numerals:
1. a primer layer; 2. an antistatic coating layer; 3. a heat insulating felt layer; 4. a second waterproof layer; 5. pressing metal strips; 6. a gasket 7, a heat-proof plate; 8. avoiding the notch; 9. avoiding holes; 10. a deck section housing; 11. a bonding glue layer; 12. a first waterproof layer.
Detailed Description
In order to make the technical solutions and advantages of the embodiments of the present application more apparent, the following further detailed description of the exemplary embodiments of the present application with reference to the accompanying drawings makes it clear that the described embodiments are only a part of the embodiments of the present application, and are not exhaustive of all embodiments. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
Exemplary spacecraft insulation Structure
Fig. 1 is a flowchart of a method for insulating an aerospace vehicle according to an embodiment of the present application, and as shown in fig. 1, the method for insulating an aerospace vehicle includes the following steps:
step S101: spraying primer on the surface of the cabin shell to form a primer layer 1;
step S103: spraying antistatic paint on the primer layer 1 to form an antistatic paint layer 2;
step S105: coating adhesive glue on the antistatic coating layer 2 to form an adhesive glue layer 11;
step S107: and bonding a heat insulation blanket on the bonding glue layer 11 to form the heat insulation felt layer 3.
The aerospace vehicle comprises a cabin shell 10, wherein primer is sprayed on the surface of the cabin shell 10 of the cabin of the aerospace vehicle to form a primer layer 1, the primer can comprise zinc yellow primer, then antistatic paint is sprayed on the primer layer 1 to form an antistatic paint layer 2, then adhesive glue is coated on the antistatic paint layer 2 to form an adhesive glue layer 11, and the heat-proof glue is adopted for integral bonding, so that the bonding property of the heat-insulating felt layer 3 and the arrow wall can be ensured, and the heat-proof effect is ensured. Wherein, the adhesive can be manually brushed. Therefore, the base coat layer 1, the antistatic coating layer 2, the adhesive layer 11 and the heat insulation felt layer 3 which are mutually attached are sequentially arranged on the cabin shell 10 from inside to outside, and the heat insulation felt layer 3 is adhered on the outer surface of the cabin shell 10 of the cabin, so that the multilayer structure based on the flexible heat insulation felt has a multilayer heat protection effect. Wherein the primer layer 1 is applied to a cabin shell 10 of the spacecraft.
The thickness of the primer layer 1 may be 0.05 mm, the thickness of the antistatic coating may be 0.1 mm, the thickness of the adhesive layer 11 may be 0.3 mm, the thickness of the heat insulation felt layer 3 may be 10 mm, and the waterproof coating penetrates into the heat insulation felt layer 3 without counting the thickness, which is specifically shown in fig. 1. The thickness of the heat insulation felt layer 3 is selected within an optional range, the thickness of the adhesive layer 11 can be 0.2 mm to 0.8 mm, and the bonding effect of the heat insulation felt layer 3 can be ensured. The total range of material thickness deviation of the other layers is controlled within 0.1 mm.
Further, the spacecraft thermal insulation method also comprises the following steps: before the thermal insulation blanket is bonded to the bonding adhesive layer 11, the thermal insulation blanket is soaked in a waterproof adhesive to form a waterproof layer on the surface of the thermal insulation blanket.
The heat-insulating felt layer 3 is soaked in the waterproof glue, so that the outer surfaces of the heat-insulating felt layer 3 are coated with a waterproof coating, wherein the two opposite outer surfaces of the heat-insulating felt layer 3 form a first waterproof layer 12 and a second waterproof layer 4 respectively. The heat insulation felt layer 3 soaked with the waterproof glue is adhered to the outer surface of the cabin section shell 10 of the cabin section, so that the heat insulation structure adopts a multi-layer structure based on flexible heat insulation felts, the adaptability of the heat insulation structure is improved, and the effect of multi-layer heat protection is achieved.
Further, fig. 2 is a flowchart of a method for insulating an aerospace vehicle according to the embodiment of fig. 1, where as shown in fig. 2, the method for insulating an aerospace vehicle further includes:
step S201: a connecting hole is arranged on the heat insulation felt layer 3;
step S203: the fastener is adopted to penetrate through the connecting hole to connect the heat insulation felt layer 3 and the shell.
The fastening piece sequentially penetrates through the second waterproof layer, the heat insulation felt layer 3, the first waterproof layer 12, the bonding glue layer 11, the anti-static coating layer 2 and the primer layer 1 and is connected with the cabin section shell 10. The fastening member is used to fasten the heat insulation felt 3 to the outer shell to solve the problem that the heat insulation felt 3 is easily detached as a flexible heat insulation structure. Specifically, the insulation structure of the spacecraft is easy to separate from the bonding connection of the cabin shell 10 in aerodynamic and aerodynamic thermal environments, and the insulation felt layer 3 and the cabin shell 10 can be connected by using a stainless steel fastener every 250 mm to 350 mm in order to avoid the insulation felt layer 3 from debonding from the cabin shell 10 in aerodynamic and aerodynamic thermal environments.
Still further, fig. 3 is a flow chart of a method for insulating an aerospace vehicle according to another embodiment of the present application, where as shown in fig. 3, the method for insulating an aerospace vehicle further includes:
step S301: laying a metal pressing strip 5 on the edge of the heat insulation felt layer 3;
step S303: the metal pressing strip 5, the heat insulation felt layer 3 and the shell are connected through a fastener penetrating through the connecting hole.
The metal pressing strip 5 is arranged at the edge of the second waterproof layer, and the metal pressing strip 5 covers the outer surface of the second waterproof layer. Wherein the fastening member presses the metal bead 5. The metal pressing strip 5 is strip-shaped, the metal pressing strip 5 has a certain width, the metal pressing strip 5 covers the edge of the heat insulation felt layer 3, and a waterproof layer is formed on the outer surface of the heat insulation felt layer 3 after the heat insulation felt layer is immersed in waterproof glue, so that the metal pressing strip 5 covers a second waterproof layer which is far away from the bonding glue layer 11. Because the metal pressing strip 5 also needs to have waterproof performance, the metal pressing strip 5 can be made of stainless steel, the waterproof effect can be guaranteed, certain weight is achieved, the heat insulation felt layer 3 can be compressed, and the situation that the heat insulation felt layer 3 is torn from the edge is avoided. Therefore, the edge of the heat insulation felt layer 3 can adopt a metal pressing strip 5 made of stainless steel for pressing, and the heat insulation failure caused by that the heat insulation felt is torn from the edge in the flying process can be avoided.
Still further, the spacecraft thermal insulation method further comprises: and coating waterproof and heat-proof glue on the outer surfaces of the fastening piece and the metal pressing strip.
The outer surfaces of the fastening piece and the metal pressing strip 5 are coated with high-temperature glue layers. The high-temperature glue layer coated on the outer surfaces of the fastening piece and the metal pressing strip 5 can be waterproof and heat-proof, and the heat-proof effect can be ensured through the waterproof and heat-proof high-temperature glue layer.
Still further, the spacecraft thermal insulation method further comprises: a spacer 6 is arranged on the fastening element such that the spacer 6 presses against the insulation felt 3.
As shown in fig. 7, the fastening member includes a gasket 6, and a screw or a bolt, the gasket 6 is disposed on the outer surface of the second waterproof layer 4 and the outer surface of the metal bead 5, and the screw or the bolt penetrates through the gasket 6. By adding the self-made gasket 6 under the screw or the bolt, the pressing area can be increased, and the fastener is prevented from being separated. Screws or bolts may be used as fasteners to facilitate the attachment of the insulation blanket 3 to the deck section shell 10. The gasket 6 can be a circular sheet structure, and a round hole is formed in the middle of the gasket 6, so that a screw or a bolt can conveniently penetrate through the round hole.
Still further, fig. 4 is a flow chart of a method for insulating an aerospace vehicle according to yet another embodiment of the present application, where as shown in fig. 4, the method for insulating an aerospace vehicle further includes:
step S401: an avoidance gap 8 is formed in the heat insulation felt layer 3;
step S403: laying a metal pressing strip 5 on the edge of the avoidance notch 8;
step S405: laying a gasket 6 on the metal pressing strip 5;
step S407: the gasket 6, the metal bead 5, the heat insulating felt 3 and the outer shell are connected by fasteners.
The cabin shell 10 is provided with the protrusions of the connecting pieces such as rivets and bolts, and the avoidance gap 8 is arranged on the heat insulation felt layer 3, so that the accommodating space of the protrusions can be formed, and the heat-proof problem of local dense protrusions is solved. Fig. 8 is a schematic top view of an insulation structure of an aerospace vehicle according to another embodiment of the present application, and as shown in fig. 8, an avoidance gap 8 is formed in the insulation felt layer 3; wherein, the edge of the avoiding gap 8 is provided with a metal pressing strip 5 and a fastening piece. Aiming at typical cabin section openings such as a long row cover opening, a metal pressing strip 5 made of metal materials is needed to be adopted around the avoiding gap 8 for carrying out a pressing measure, so that large-area debonding of the edge is avoided, a part of free edges of the heat insulation felt layer 3 can be reserved to cover on structures such as the long row cover, and heat leakage is avoided.
Still further, the spacecraft thermal insulation method further comprises: laying heat-proof boards 7 on the end frames and the butt joint surfaces of the cabin sections, and enabling the heat-proof boards 7 to be matched with the heat-insulating felt layers 3 for heat insulation.
As shown in fig. 7, the heat-proof plate 7 is coated on the edge of the second waterproof layer. The cabin end frame and the butt joint face of the aerospace carrier need thermal protection, and the thermal insulation felt layer 3 is of a flexible structure, so that the application of the pre-tightening force of the main bearing bolt at the end frame part can be influenced, the thermal insulation felt is not suitable for directly and simply adopting thermal insulation, and the thermal insulation plate 7 made of glass fiber reinforced plastic materials or other thermal protection structures can be adopted in a targeted mode. The heat-proof plate 7 can be a split glass steel plate formed by high-strength glass cloth compression molding, and the heat-proof felt layer 3 is compressed by the heat-proof plate 7, so that the heat-proof failure of the end frame with large heat flow can be avoided.
Still further, fig. 5 is a flowchart of a method for insulating an aerospace vehicle according to yet another embodiment of the present application, where as shown in fig. 5, the method for insulating an aerospace vehicle further includes:
step S501: the heat insulation felt layer 3 is provided with avoidance holes;
step S503: and sealing or gluing the avoiding hole.
The cabin shell 10 of the cabin structure is provided with smaller circular holes such as a heat flow sensor and a lifting hole, as shown in fig. 8, the heat insulation felt layer 3 is provided with an avoiding hole 9, and the inner wall of the avoiding hole 9 is provided with a sealing edge. By forming the avoidance holes 9 in the heat-insulating felt layer 3 and performing edge sealing or gluing treatment on the quartz fiber yarns scattered on the inner walls of the avoidance holes 9, local edge scattering can be avoided.
The space vehicle is particularly suitable for the space vehicle cabin section with a large number of rivet bulges or moderate screw bulges and adopts an inner stringer structure, and special treatment is not needed when the flexible heat insulation structure is arranged on the outer wall of the cabin section structure. The heat insulation structure is wide in application range, can be used on most of rocket body structures needing heat insulation measures, and is provided with a large-area flexible heat insulation structure on the surface, so that the heat insulation requirement of the cabin structure is met, and the expected heat insulation effect is achieved.
Exemplary spacecraft
An aerospace vehicle, comprising: the cabin shell 10 is subjected to heat insulation treatment by adopting any heat insulation method of the spacecraft, so that a heat insulation structure is formed on the cabin shell 10, the spacecraft comprises the cabin shell 10, and the heat insulation structure comprises a primer layer 1, an anti-static coating layer 2, a bonding adhesive layer 11 and a heat insulation felt layer 3 which are sequentially attached to one another.
The heat insulation structure of the spacecraft is arranged on the cabin shell 10, so that the spacecraft has a good heat insulation effect. In particular, the thermal insulation felt layer 3 is adhered to the outer surface of the cabin shell 10 of the cabin, so that the multilayer structure based on the flexible thermal insulation felt has the effect of multilayer thermal protection. Wherein the primer layer 1 is applied to a cabin shell 10 of a spacecraft. Fig. 6 is a schematic longitudinal sectional structural view of an insulation structure of an aerospace vehicle according to an embodiment of the present application, and as shown in fig. 6, an insulation felt layer 3 is adhered to an outer surface of a cabin shell 10 of a cabin, so that a multi-layer structure based on a flexible insulation felt has an effect of multi-layer thermal protection. Wherein the primer layer 1 is applied to a cabin shell 10 of a spacecraft.
The application has the following advantages:
1. by adhering the heat insulation felt layer 3 to the outer surface of the cabin shell 10 of the cabin, a multi-layer structure based on the flexible heat insulation felt is formed, and a multi-layer heat protection effect is achieved.
2. The problem that the heat insulating felt 3 is easily separated as a flexible heat insulating structure can be solved by fastening the heat insulating felt 3 to the housing with a fastening member.
3. The fastener includes gasket 6, can increase the area that compresses tightly, avoids the fastener to deviate from.
4. By providing the metal battens 5 at the edges of the insulation felt layer 3 for pressing, thermal failure due to the insulation felt being torn from the edges during flight can be avoided.
5. The adaptability of the heat insulation structure can be improved by arranging the avoidance notch 8, and the metal pressing strips 5 are adopted around the avoidance notch 8 for carrying out pressing measures, so that large-area debonding of the edge can be avoided.
6. The high-temperature glue layer brushed on the outer surface of the fastening piece and the metal pressing strip 5 can prevent water and heat, and the heat-proof effect can be ensured through the high-temperature glue layer integrating water resistance and heat resistance.
7. By adopting the heat-proof plate 7 to compress the heat-insulating felt layer 3, the heat-proof failure of the end frame with larger heat flow can be avoided.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and thus should not be considered as limiting the present application.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless explicitly specified otherwise.
In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections, removable connections, or integral parts; may be mechanically, electrically or otherwise in communication with each other; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art as appropriate.
While the preferred embodiments of the present application have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all alterations and modifications as fall within the scope of the application.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. A heat insulation method for a space vehicle is characterized in that,
spraying a primer on the surface of the cabin shell to form a primer layer (1);
spraying antistatic paint on the primer layer (1) to form an antistatic paint layer (2);
coating adhesive glue on the antistatic coating layer (2) to form an adhesive glue layer (11);
and bonding a heat insulation blanket on the bonding glue layer (11) to form a heat insulation felt layer (3).
2. A method of insulating an aerospace vehicle according to claim 1, further comprising: a connecting hole is formed in the heat insulation felt layer (3);
and a fastener is adopted to penetrate through the connecting hole to connect the heat insulation felt layer (3) and the shell.
3. A method of insulating an aerospace vehicle according to claim 2, further comprising: laying a metal pressing strip (5) on the edge of the heat insulation felt layer (3);
the metal pressing strip (5), the heat insulation felt layer (3) and the shell are connected through fasteners penetrating through the connecting holes.
4. A method of insulating an aerospace vehicle according to claim 3, further comprising: and coating waterproof and heat-proof glue on the outer surfaces of the fastener and the metal pressing strip.
5. A method of insulating an aerospace vehicle according to any of claims 2-4, further comprising:
a spacer (6) is arranged on the fastening element in such a way that the spacer (6) presses the heat insulation felt layer (3).
6. Process for insulating an aerospace vehicle according to any one of claims 2-4, wherein heat protection panels (7) are laid over the tank section end frames and the butt surfaces, and wherein the heat protection panels (7) are fitted with the insulation felt layer (3) for insulation.
7. A method of insulating an aerospace vehicle according to any one of claims 1-4, further comprising:
an avoidance gap (8) is formed in the heat insulation felt layer (3);
laying a metal pressing strip (5) on the edge of the avoiding gap (8);
laying a gasket (6) on the metal pressing strip (5);
connecting the gasket (6), the metal bead (5), the heat insulating felt layer (3) and the housing by fasteners.
8. A method of insulating an aerospace vehicle according to any of claims 1-4, further comprising: a dodging hole is formed in the heat insulation felt layer (3); and performing edge sealing or gluing treatment on the avoiding hole.
9. A method of insulating an aerospace vehicle according to any of claims 1-4, further comprising:
before the thermal insulation blanket is bonded on the bonding glue layer (11), the thermal insulation blanket is soaked in waterproof glue to form a waterproof layer on the surface of the thermal insulation blanket.
10. An aerospace vehicle, comprising: a cabin shell (10);
-subjecting the deck shell (10) to a thermal insulation process according to any one of claims 1 to 9, such that a thermal insulation structure is formed on the deck shell (10), the thermal insulation structure comprising a primer layer (1), an antistatic coating layer (2), a bondline (11) and a thermal insulation felt layer (3) applied to one another in this order.
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| CN202211140560.8A CN115231000A (en) | 2022-09-20 | 2022-09-20 | Heat insulation method for space carrier |
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| CN202211140560.8A CN115231000A (en) | 2022-09-20 | 2022-09-20 | Heat insulation method for space carrier |
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Application publication date: 20221025 |