阅读说明：本技术 一种空间低温贮箱多重复合绝热层 (Multiple composite heat-insulating layer of space low-temperature storage tank ) 是由 赵积鹏 于斌 马天驹 顾森东 刘志栋 杨文博 赵蕾 王小宁 张海 张建军 张涛 于 2021-09-09 设计创作，主要内容包括：本申请涉及空间贮存技术领域,具体而言,涉及一种空间低温贮箱多重复合绝热层,包括箱体以及壳体,壳体与箱体之间依次设置有纤维缠绕复合层、泡沫绝热层、绝热渐变密度层、蒸汽冷却屏组件以及防辐射遮挡屏。本申请在满足重量和外形尺寸等技术指标的前提下,最大限度的减少了空间低温贮箱的漏热现象,实现了低蒸发损耗或零蒸发宇航长期在轨的服役要求,采用了薄壁壳体复合材料结构、优化的变密度多层绝热结构以及主动换热式蒸汽冷却屏技术,具有绝热效果好、轻质量、低功耗、高效率等优点,满足航天系统对于质量控制、性能指标以及可靠度的高要求。(The utility model relates to a space stores technical field, particularly, relates to a space low temperature storage tank multiple compound heat insulation layer, including box and casing, set gradually fibre winding composite bed, foam heat insulation layer, adiabatic gradual change density layer, steam cooling screen subassembly and radiation protection between casing and the box and shelter from the screen. On the premise of meeting technical indexes such as weight, appearance size and the like, the heat leakage phenomenon of the space low-temperature storage tank is reduced to the maximum extent, the long-term on-orbit service requirement of low-evaporation loss or zero-evaporation aerospace is realized, the thin-wall shell composite material structure, the optimized variable-density multi-layer heat insulation structure and the active heat exchange type steam cooling screen technology are adopted, the heat insulation system has the advantages of good heat insulation effect, light weight, low power consumption, high efficiency and the like, and the high requirements of the aerospace system on quality control, performance indexes and reliability are met.)

1. The utility model provides a space low temperature storage tank multiple composite heat insulation layer which characterized in that, includes box and casing, fibre winding composite bed, foam heat insulation layer, adiabatic gradual change density layer, steam cooling screen subassembly and radiation protection shield screen have set gradually between casing and the box.

2. The multiple composite thermal insulation layer for a space cryogenic tank of claim 1, wherein the shell is a metal lined shell comprising an upper head, a barrel, and a lower head.

3. The multiple composite thermal insulation layer for a space cryogenic tank of claim 2 wherein the material of the shell is a titanium alloy or an aluminum alloy.

4. The multi-composite thermal insulation layer for a spatial cryogenic tank of claim 1 wherein the fiber wound composite layer comprises a hoop fiber wound composite layer and a helical fiber wound composite layer.

5. The multi-composite thermal insulation layer for a space cryogenic tank of claim 4 wherein the filament wound composite layer is comprised of fibers and resin, wherein:

the tensile strength of the fiber is more than or equal to 4500MPa, the modulus is more than or equal to 200GPa, and the elongation is more than or equal to 1.7%;

the tensile strength of the resin is more than or equal to 70MPa, and the elongation is more than or equal to 1.8%.

6. The multi-layer composite insulation for a space cryogenic tank of claim 1 wherein the foam insulation comprises a cushion tie layer, a bulk foam layer, a seal reinforcement layer, and a heat reflection shield.

7. The space cryogenic tank multi-composite thermal insulation layer of claim 6,the foam material is characterized in that the main body foam layer is made of polyurethane foam, and the density of the main body foam layer is 29-47 kg/m³。

8. The space cryogenic tank multi-composite thermal insulation of claim 1 wherein the thermally insulating gradient density layer comprises a low density layer region, a medium high density layer region, and a high density layer region, each density layer region consisting of a distance layer and a radiation protective layer.

9. The multi-composite thermal insulation layer for a spatial cryogenic tank of claim 1 wherein the vapor cooling panel assembly comprises an aluminum alloy panel, a distributed cold pipe, a circulation pump, a refrigerator, and a helium tank.

10. The multiple composite insulation layer for a space cryogenic tank of claim 1 wherein said radiation shield is an ultra thin wall all metal optical shield.

Technical Field

The application relates to the technical field of space storage, in particular to a space low-temperature storage box multiple composite heat-insulating layer.

Background

In the field of space propulsion of satellites and spacecrafts, compared with a normal-temperature propellant, the low-temperature propellant has the advantages of high specific impulse, small volume, large duty ratio, large carrying capacity of the propellant and the like, in the aspect of chemical propulsion, the low-temperature propellant such as liquid hydrogen, liquid oxygen and the like is adopted to replace the normal-temperature propellant such as methylhydrazine, dinitrogen tetroxide and the like, in the aspect of electric propulsion, the low-temperature propellant such as liquid xenon, liquid krypton and the like is adopted to replace the normal-temperature propellant such as normal-temperature high-pressure xenon, krypton and the like, so that the requirements of high-performance and high-reliability space craft tasks are met.

The spacecraft can be influenced by space thermal environments such as solar radiation, earth infrared radiation, planet albedo, black background and the like when flying in space, the space low-temperature storage tank can leak heat through radiation, the problem of low-temperature storage of the spacecraft in different stages such as ground, launching, orbit switching and the like can also exist, and in addition, the low-temperature storage tank also has the problem of low-temperature storage of different heat leakage mechanisms such as convection heat transfer, solid heat conduction, radiation heat transfer and the like in the flying process of the spacecraft.

Disclosure of Invention

The application mainly aims to provide the multiple composite heat insulation layer of the space low-temperature storage tank, which can reduce the problem of heat leakage of the space low-temperature storage tank to the maximum extent and meet the requirements of low evaporation rate indexes on the ground and in the launching stage and zero evaporation indexes in the on-orbit and off-orbit stages.

In order to achieve the purpose, the application provides a space low-temperature storage tank multiple composite heat insulation layer, which comprises a tank body and a shell, wherein a fiber winding composite layer, a foam heat insulation layer, a heat insulation gradient density layer, a steam cooling screen assembly and a radiation-proof shielding screen are sequentially arranged between the shell and the tank body.

Further, the shell is a metal lining shell and comprises an upper end enclosure, a cylinder body and a lower end enclosure.

Further, the shell is made of titanium alloy or aluminum alloy.

Further, the fiber winding composite layer comprises a circumferential fiber winding composite layer and a spiral fiber winding composite layer.

Further, the filament wound composite layer is composed of fibers and resin, wherein: the tensile strength of the fiber is more than or equal to 4500MPa, the modulus is more than or equal to 200GPa, and the elongation is more than or equal to 1.7%; the tensile strength of the resin is more than or equal to 70MPa, and the elongation is more than or equal to 1.8%.

Further, the foam heat insulation layer comprises a buffer bonding layer, a main body foam layer, a sealing reinforcing layer and a heat reflection prevention screen.

Further, the main foam layer is made of polyurethane foam and has the density of 29-47 kg/m³。

Furthermore, the heat-insulating gradient density layer comprises a low-density layer region, a medium-low density layer region, a medium-high density layer region and a high-density layer region, and each density layer region consists of a spacing layer and a radiation-proof layer.

Further, the steam cooling screen assembly comprises an aluminum alloy screen cover, a distributed cold pipe, a circulating pump, a refrigerating machine and a helium tank.

Furthermore, the radiation-proof shielding screen is an ultra-thin-wall all-metal light screen.

The multiple composite heat-insulating layer of the space low-temperature storage tank provided by the invention has the following beneficial effects:

on the premise of meeting technical indexes such as weight, appearance size and the like, the heat leakage phenomenon of the space low-temperature storage tank is reduced to the maximum extent, the long-term on-orbit service requirement of low-evaporation loss or zero-evaporation aerospace is realized, the thin-wall shell composite material structure, the optimized variable-density multi-layer heat insulation structure and the active heat exchange type steam cooling screen technology are adopted, the heat insulation system has the advantages of good heat insulation effect, light weight, low power consumption, high efficiency and the like, and the high requirements of the aerospace system on quality control, performance indexes and reliability are met.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this application, serve to provide a further understanding of the application and to enable other features, objects, and advantages of the application to be more apparent. The drawings and their description illustrate the embodiments of the invention and do not limit it. In the drawings:

FIG. 1 is a schematic view of a multiple composite thermal insulation layer for a space cryogenic tank according to an embodiment of the present application;

FIG. 2 is a schematic cross-sectional view of a multiple composite thermal insulation layer for a space cryogenic tank according to an embodiment of the present application;

in the figure: 1-shell, 11-upper end enclosure, 12-cylinder, 13-lower end enclosure, 2-fiber winding composite layer, 2 l-annular fiber winding composite layer, 22-spiral fiber winding composite layer, 3-foam heat insulation layer, 31-buffer bonding layer, 32-main body foam layer, 33-sealing reinforcing layer, 34-heat-proof reflecting screen, 4-heat insulation gradient density layer, 41-low density layer area, 42-medium and low density layer area, 43-medium density layer area, 44-medium and high density layer area, 45-high density layer area, 5-steam cooling screen component, 51-refrigerator, 52-circulating pump, 53-helium tank, 54-distributed cold pipe, 55-aluminum alloy shield, 6-radiation-proof shield screen and 7-box body.

Detailed Description

In order to make the technical solutions better understood by those skilled in the art, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are only partial embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application.

As shown in fig. 1-2, the application provides a multiple composite heat insulation layer of a space low-temperature storage tank, which comprises a tank body 7 and a shell body 1, wherein a fiber winding composite layer 2, a foam heat insulation layer 3, a heat insulation gradient density layer 4, a steam cooling screen assembly 5 and a radiation-proof shielding screen 6 are sequentially arranged between the shell body 1 and the tank body 7.

Specifically, the multiple composite heat insulation layers of the spatial low-temperature storage tank provided by the embodiment of the application belong to a passive heat protection technology, the spatial low-temperature storage tank mainly takes convection heat exchange as a main part in the ground and launching stages, and mainly takes radiation heat exchange and solid heat conduction as main parts in the orbit and orbit changing stages, so that the spatial low-temperature storage tank needs to maintain a lower evaporation rate index requirement in the ground and launching stages, and needs to ensure a zero evaporation index requirement in the orbit and orbit changing stages, in order to realize the index requirements, the embodiment of the application provides a foam layer with a 4-layer composite structure, a variable-density multilayer heat insulation structure with 5 density zones distributed, an active heat exchange type steam cooling screen assembly 5 with a plurality of distributed cold pipe circulation loops and a multiple-component structure combination and function coupling heat insulation layer of a radiation-proof shielding screen 6, wherein a shell 1 and a fiber winding composite layer 2 are used as main bodies of integral structural strength and rigidity bearing force, and can also play the role of fixed support; the foam heat insulation layer 3 mainly plays a heat insulation role in the ground and the launching stage, and a high-heat-resistance foam material is used for preventing heat leakage of a space low-temperature storage box mainly based on convection heat transfer, so that a lower evaporation rate index is ensured; the heat-insulation gradient density layer 4 mainly plays a heat insulation role in the stages of track and track transfer, adopts a radiation-proof screen with higher reflectivity to prevent the heat leakage of a space low-temperature storage box mainly based on radiation and solid conduction, and reduces the heat leakage to the maximum extent on the premise of meeting the technical indexes such as weight, appearance size and the like; the steam cooling screen assembly 5 adopts an active heat exchange type and is mainly used for reducing the interlayer temperature gradient, the heat flux density and the like of a plurality of layers of heat-insulating materials, so that the heat flux density of the space low-temperature storage tank is reduced, and heat leakage is reduced; the radiation-proof shielding screen 6 is mainly used for eliminating the influence of space thermal environments such as solar radiation, earth infrared radiation, planet back illumination, black background and the like.

Further, the shell 1 is a metal lining shell 1, and comprises an upper end enclosure 11, a cylinder 12 and a lower end enclosure 13. In the embodiment of the application, the box body 7 of the space low-temperature storage box is preferably a spherical head cylindrical structure, the shell 1 is arranged inside the box body 7 and is a metal lining shell 1, and the metal lining shell 1 comprises a metal air port head, a cylinder body 12 and a liquid port head, and the metal air port head, the cylinder body and the liquid port head are welded to form the lining shell 1.

Further, the material of the housing 1 is titanium alloy or aluminum alloy. When the shell 1 is made of aluminum alloy materials, the end socket adopts a die-free spinning process, the cylinder body 12 adopts a strong spinning thinning process, the connection adopts a friction stir welding process, and the welding line coefficient is more than or equal to 0.8; when the shell 1 is made of titanium alloy material, the end socket is made of plate clamping plates through hot stamping and machining, the cylinder body 12 is made of ring material through machining, the wall thickness of the thin film area of the end socket and the cylinder body 12 is 0.8mm, and the end socket and the cylinder body are integrally connected through electron beam welding.

Further, the fiber-wound composite layer 2 includes a hoop fiber-wound composite layer 21 and a spiral fiber-wound composite layer 22. The fiber winding composite layer 2 is of a composite layer structure formed by alternately winding hoop fibers and spiral fibers, and the composite layer and the outermost layer close to the metal lining shell 1 are hoop fiber winding composite layers 21.

Further, the filament winding composite layer 2 is composed of fibers and resin, wherein: the tensile strength of the fiber is more than or equal to 4500MPa, the modulus is more than or equal to 200GPa, and the elongation is more than or equal to 1.7%; the tensile strength of the resin is more than or equal to 70MPa, and the elongation is more than or equal to 1.8%. The fiber winding composite layer 2 is composed of T800S carbon fiber and low temperature resistant epoxy resin, parameters of the fiber and the resin are selected according to actual conditions, the whole wet winding process of a hoop winding and spiral alternate winding line type is adopted, the hoop fiber winding composite layer 21 is preferably 14 layers, the spiral fiber winding composite layer 22 is preferably 12 layers, and the total thickness of the composite layer is preferably 4.2 mm.

Further, the foam insulation layer 3 includes a cushion adhesive layer 31, a main foam layer 32, a sealing reinforcement layer 33, and a heat reflection preventing screen 34. In the present embodiment, the total thickness of the foamed heat insulating layer 3 is preferably 10mm, and the overall thermal conductivity is preferably 8.66 × 10^-4W/(m.K), by cold junction to hot junction in proper order for buffering tie coat 31, main part foam layer 32, sealed back up coat 33 and heat reflection screen 34 of preventing, wherein, the effect that the heat insulation layer bonds is mainly played in buffering tie coat 31, and main part foam layer 32 mainly plays the effect of adiabatic main part, and sealed back up coat 33 mainly plays the effect of isolated steam infiltration, and heat reflection screen 34 of preventing mainly plays the effect that reduces the radiation building heat.

Further, the main foam layer 32 is made of polyurethane foam and has a density of 29-47 kg/m³. The main foam layer 32 is preferably made of polyurethane foam, has the advantages of shock resistance, compression resistance, ultralow temperature thermal conductivity, prevention of heat leakage of the space low-temperature storage box mainly based on convection heat transfer, and guarantee of lower evaporation rate index

Further, the heat-insulating gradient density layer 4 comprises a low-density layer area 41, a medium-low density layer area 42, a medium-density layer area 43, a medium-high density layer area 44 and a high-density layer area 45, wherein each density layer area is composed of a spacing layer and a radiation-proof layer.

Specifically, the density of the low-density layer region 41, the medium-low density layer region 42, the medium-density layer region 43, the medium-high density layer region 44 and the high-density layer region 45 is 8 layers/cm, 11 layers/cm, 14 layers/cm, 17 layers/cm and 20 layers/cm in sequence, the total number of layers of the adiabatic gradient density layer 4 is preferably 56 layers, and the total thickness is preferably 40 mm. In addition, the density of the radiation-proof layers of the heat-insulating gradient density layer 4 from the cold end to the hot end is gradually increased, the density of the spacing layers is gradually decreased, at least one spacing layer is arranged between any two radiation-proof layers, the radiation-proof layer is made of a double-sided aluminum-plated polyimide film, the thickness of the film is more than or equal to 6.2 micrometers, the thickness of the aluminum-plated layer is 0.12-0.2 micrometers, the aperture ratio is 2-6%, the spacing layer is made of a polyimide silk screen or a nylon net, the thickness of a single layer is less than or equal to 0.29mm, and the area density is less than or equal to 0.21kg/m²And the spacing layer and the radiation-proof layer are sealed and fixed by polyimide fiber sewing threads.

Further, the vapor cooling panel assembly 5 includes an aluminum alloy panel 55, a distributed cold tube 54, a circulation pump 52, a refrigerator 51, and a helium tank 53. The steam cooling screen assembly 5 adopts an active heat exchange type and is mainly used for reducing interlayer temperature gradient, heat flux density and the like of multiple layers of heat insulation materials, so that the heat flux density of the space low-temperature storage tank is reduced, and heat leakage is reduced, wherein a circulating pump 52 and a refrigerating machine 51 form a low-temperature circulating pipeline, multiple groups of distributed cold pipes 54 are arranged according to actual conditions, multiple groups of distributed cold pipes 54 and aluminum alloy screen covers 55 are arranged between the layers of the heat insulation gradient density layer 4, a refrigerating working medium is helium in a helium bottle 53, the distributed cold pipes 54 and the aluminum alloy screen covers 55 are fixedly connected with a heat insulation supporting structure of the space low-temperature storage tank, the multiple groups of distributed cold pipes 54 and the low-temperature circulating pipeline are connected in parallel to form a loop and are both arranged at the outer side of the space low-temperature storage tank, and the spacing angles are consistent.

Further, the radiation-proof shielding screen 6 is an ultra-thin wall all-metal light screen, and is mainly used for eliminating the influence of space thermal environments such as solar radiation, earth infrared radiation, planet back illumination, black background and the like.

The above description is only a preferred embodiment of the present application and is not intended to limit the present application, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.