CN112208802A

CN112208802A - Multilayer heat insulation assembly

Info

Publication number: CN112208802A
Application number: CN202010938866.2A
Authority: CN
Inventors: 隋愿愿; 赵益涛; 张楠; 李子轩; 段友东; 王珏
Original assignee: CASIC Space Engineering Development Co Ltd
Current assignee: CASIC Space Engineering Development Co Ltd
Priority date: 2020-09-09
Filing date: 2020-09-09
Publication date: 2021-01-12
Anticipated expiration: 2040-09-09
Also published as: CN112208802B

Abstract

This scheme discloses a multilayer thermal-insulated subassembly includes: a plurality of stacked thermal insulation assemblies comprising a reflective barrier layer and a spacer layer; the facial masks are coated outside the heat insulation assemblies; and a bottom film disposed at the bottom of the plurality of insulation assemblies; the spacing layers in any two adjacent assemblies extend towards two sides, and the extending parts are positioned on the outer sides of the edges of the spacing layers. This scheme can be not taking too much space, under the condition that does not increase the manufacturing degree of difficulty, make the thermal-insulated subassembly of multilayer have higher product quality, reinforcing maneuverability, installation/dismantlement convenience.

Description

Multilayer heat insulation assembly

Technical Field

The scheme relates to the technical field of spaceflight. And more particularly to a multi-layer insulation assembly.

Background

At present, the aerospace technology is an important means for rapidly acquiring and transmitting information, has wide application requirements in military and commercial fields, and has high requirements on adaptability of aircrafts, aerospace equipment and loads to space thermal environments in severe operating environments. In order to ensure that the temperature level and the stability of the satellite and key equipment thereof meet the normal working requirements, the design of a thermal control system becomes the key of the whole satellite research and development link. The design of the thermal control system comprises an active thermal control design and a passive thermal control design, and the design of the thermal control system of the spacecraft usually adopts a design concept that passive thermal control is used as a main design and active thermal control is used as an auxiliary design due to the limitation of available energy of the spacecraft.

The multilayer heat insulation assembly is a passive heat control assembly (device) which is widely applied, is formed by alternately laminating and sewing a reflecting screen with low emissivity and a spacer layer with low thermal conductivity, has excellent heat insulation function under a vacuum condition, and is shown in figure 1. The relevant terms and definitions are shown in table 1.

TABLE 1 Multi-layer insulation Assembly related terms and definitions

Disclosure of Invention

This scheme aim at provides a multilayer thermal-insulated subassembly.

In order to achieve the purpose, the scheme is as follows:

in a first aspect, the present disclosure provides a multi-layer thermal insulation assembly comprising: a plurality of stacked thermal insulation assemblies comprising a reflective barrier layer and a spacer layer;

the facial masks are coated outside the heat insulation assemblies; and the combination of (a) and (b),

a bottom film disposed at the bottom of the plurality of insulation assemblies;

the spacing layers in any two adjacent assemblies extend towards two sides, and the extending parts are positioned on the outer sides of the edges of the spacing layers.

In a preferred embodiment, the plurality of insulation assemblies are secured by stitching in a direction perpendicular to the spacing layer.

In a preferred embodiment, a fixing binding wire is arranged on the extension part.

In a preferred embodiment, the position where the multi-layer heat insulation assembly is overlapped with the insulated device is provided with a multi-layer overlapping part.

In a preferred embodiment, the multi-layer thermal insulation assembly is provided with a through hole for accommodating a non-planar structure on the equipment.

In a preferred embodiment, the inner edge of the through hole is provided with a plurality of layers of overlapping portions.

The scheme has the following beneficial effects:

this scheme can be not taking too much space, under the condition that does not increase the manufacturing degree of difficulty, make the thermal-insulated subassembly of multilayer have higher product quality, reinforcing maneuverability, installation/dismantlement convenience.

Drawings

In order to illustrate the implementation of the solution more clearly, the drawings that are needed in the description of the embodiments will be briefly described below, it being obvious that the drawings in the following description are only some embodiments of the solution, and that other drawings may be derived from these drawings by a person skilled in the art without inventive effort.

FIG. 1 shows a cross-sectional view of a multi-layer insulation assembly according to the present solution;

FIG. 2 shows a schematic view of one example of a multi-layer insulation assembly according to the present solution;

FIG. 3 shows a schematic view of another example of the multi-layer insulation assembly of the present solution in an expanded configuration;

FIG. 4 shows a schematic view of another example of the multi-layer insulation assembly of the present solution in an expanded configuration;

FIG. 5 shows a schematic view of another example of the multi-layer insulation assembly of the present solution in an expanded configuration;

fig. 6 shows a schematic view of the development of a further example of the multilayer insulation assembly according to the present solution.

Reference numerals

1. A reflective barrier layer; 2. a spacer layer; 3. facial mask; 4. a base film; 5. a suture; 6. fixing the binding wire; 7. a lap joint part.

Detailed Description

Embodiments of the present solution will be described in further detail below with reference to the accompanying drawings. It is clear that the described embodiments are only a part of the embodiments of the present solution, and not an exhaustive list of all embodiments. It should be noted that, in the present embodiment, features of the embodiment and the embodiment may be combined with each other without conflict.

Through research and analysis, the multilayer heat insulation assembly is generally coated on the equipment shell, and the traditional installation and fixing mode comprises the following steps: adhesive tape sticking, nylon string bag binding, nylon hasp lapping, pin pressing (buckling) piece fixing, structural interlayer, metal wire hoop binding and the like. At present, the most common installation and fixation modes of the low-temperature multilayer and the medium-temperature multilayer are nylon fastener tape lapping and pin pressing (buckling) piece fixation, which are respectively shown as a) and b):

a) the GD414 silicon rubber is used for sticking the hook belt of the nylon hasp on the surface of the instrument equipment to be bound, the ring belt of the nylon hasp is sewn at the edge sealing position at the outer side of the multilayer basement membrane 4, and two nylon binding belts are aligned and compressed when multilayer coating is implemented.

b) The pin is adhered to the surface of the instrument to be coated by GD414 silicon rubber glue, the multilayer heat insulation component with the pin hole is sleeved on the pin in a penetrating way, and the pin is fixed by a pressing (buckling) sheet.

The lap joint mode of the nylon fastener has the advantages of simple and convenient manufacture and strong implementation feasibility, and is particularly suitable for fixing the multilayer heat insulation assembly at the window which needs to be disassembled and assembled or opened and closed for many times. However, in a space environment, the multi-layer assembly may be loosened and fall off or performance may be degraded due to the reasons that the fixing member is not firmly adhered and the fixing member is not resistant to irradiation; in addition, the width of the nylon fastener tape is generally 20 mm-30 mm, and the occupied position has great influence on the heat insulation performance of the multi-layer assembly. The relative position precision requirement of the pin pressing (buckling) piece of the pin to the pin holes of the multiple layers is high, and the manufacturing difficulty is increased.

Therefore, the scheme aims to provide the multilayer heat insulation assembly applied to the aerospace instrument and equipment and the manufacturing method thereof, so that the multilayer heat insulation assembly has higher product quality, enhanced operability and convenient installation/disassembly without occupying too much space and increasing the manufacturing difficulty.

Hereinafter, a multi-layered thermal insulation assembly according to the present invention will be described in detail with reference to the accompanying drawings. As shown in FIG. 1, a multi-layer insulation assembly comprises a plurality of insulation assemblies. The insulation assembly is composed of a reflective barrier layer 1 and a spacer layer 2. That is, a multilayer isolation component is formed by alternately stacking the LOCO reflection barrier layers 1 and the spacer layers 2. In this scheme, in order to further improve the performance of multilayer thermal-insulated subassembly, can be with the wall 2 of any two adjacent combinations to extend to both sides, extend to the outside of wall 2 edge, and the extension is located the outside of wall 2 edge.

Specifically, as shown in fig. 2, the spacing layer 2 of any two adjacent heat insulation assemblies is selected to be properly extended, the fixing binding thread 6 is fixed on the extended part by using a sewing material, and finally, the surface film 3 and the bottom film 4 are used for fully coating multiple layers. Wherein, the fixing binding wire 6 of the low-temperature multilayer heat insulation component can use a polyester wire, and the fixing binding wire 6 of the medium-temperature multilayer heat insulation component and the high-temperature multilayer heat insulation component can use a stainless steel wire.

In one embodiment, as shown in fig. 3, the multi-layer boundaries may be connected in a lap joint manner by using a polyimide double-sided tape as the multi-layer lap joint part 7. The fixing binding-wire 6 is sewn in the manner shown in fig. 2, and the position of the fixing binding-wire 6 is shown in fig. 3. The fixed relation of the multilayer heat insulation assembly and the equipment can be carried out in the following modes:

a) the boundary of the multilayer heat insulation assembly forms a box shape through overlapping, and a fixing binding wire 6 and a mounting screw of the coated equipment are wound and fixed;

b) the boundaries of the multi-layer heat insulation assembly are overlapped to form a box shape, and are tightened and fixed through the winding connection between the fixing binding wires 6.

The scheme can be adaptively adjusted according to different shapes of equipment, for example, if the equipment is provided with non-planar structures such as plug-in units, cables and the like, through holes can be formed in the multilayer heat insulation assembly to accommodate the non-planar structures. In one embodiment, as shown in FIG. 4, a through-hole may be provided in the center of the multi-layer insulation assembly. The through hole is connected through the winding between the fixed binding wires 6 to realize the tightening of the through hole, thereby avoiding the occurrence of heat leakage.

In order to further assist the tightening of the through hole in the present solution, a lap joint portion 7 may be added at the edge of the through hole. As shown in fig. 5, a plurality of multi-layered overlapping parts 7 are added to the inner edge of the through hole, and the through hole is tightened and fixed by fixing the winding between the binding wires 6.

In addition, the scheme can also be applied to heat insulation of spherical equipment. As shown in fig. 6, the multi-layer insulation assembly is cut into a leaf shape, and the multi-layer boundary of the spherical device can be connected by polyimide double-sided adhesive tape in an overlapping manner. The position of the fixing binding wire 6 is shown in fig. 6, and the multilayer heat insulation assembly and the spherical equipment are connected in a winding mode through the fixing binding wire 6 to be tightened and fixed.

In addition, as can be seen from the multi-layer sectional view of fig. 2, the extending parts are of a structure with left and right sides, and the middle part is an assembly; fig. 3, 4, 5 and 6 are expanded schematic views illustrating directions perpendicular to the face film de, and thus, only one face film is shown.

In conclusion, the multilayer heat insulation assembly of this scheme's advantage lies in:

1. the material quality related to the novel installation and fixation mode is extremely light, and the multi-layer weight cannot be additionally increased;

2. the related materials are taken from materials commonly used in the multi-layer sewing process, and the stability of the space environment is ensured;

3. the state is stable and reliable in a space environment, and accidents such as multilayer falling-off and the like cannot occur;

4. the manufacturing process does not have higher requirements on the relative position precision of the fixed structure, the process basically follows the traditional multilayer sewing process, and the quality of the sewn multilayer heat insulation assembly is ensured;

5. the fixing structure used in the novel mode hardly occupies extra multilayer space, and the heat insulation performance of any region of multiple layers is not influenced;

6. the novel installation fixing mode is convenient for the cladding and the fixing of the multilayer heat insulation assembly on the instrument and equipment, the operability is strong, and the installation and the disassembly are convenient.

It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.

Claims

1. A multi-layer insulation assembly, comprising: a plurality of stacked thermal insulation assemblies comprising a reflective barrier layer and a spacer layer;

a bottom film disposed at the bottom of the plurality of insulation assemblies;

2. The multi-layer insulation assembly of claim 1, wherein the plurality of insulation packs are secured by stitching in a direction perpendicular to the spacing layer.

3. The multi-layer insulation assembly of claim 1 wherein the extension is provided with a securing tie-wire.

4. The multi-layer insulation assembly of claim 1, wherein a multi-layer lap joint is provided where the multi-layer insulation assembly overlaps the equipment to be insulated.

5. The multi-layer insulation assembly of claim 1 wherein the multi-layer insulation assembly defines a through-hole for receiving a non-planar structure on a piece of equipment.

6. The multilayer thermal insulation assembly of claim 5, wherein the inner edge of the through hole is provided with multiple layers of overlap.