CN218172634U - Inorganic curing device for space capsule - Google Patents
Inorganic curing device for space capsule Download PDFInfo
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- CN218172634U CN218172634U CN202222157473.5U CN202222157473U CN218172634U CN 218172634 U CN218172634 U CN 218172634U CN 202222157473 U CN202222157473 U CN 202222157473U CN 218172634 U CN218172634 U CN 218172634U
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Abstract
The application provides an inorganic curing device for a space capsule, which comprises a gas storage tank, a gas control module, a space capsule body and an exhaust assembly which are sequentially connected; the outer space cabin comprises a cabin outer wall and a cabin inner wall, a closed cabin wall cavity is formed between the cabin outer wall and the cabin inner wall, inorganic powder materials with gas are filled in the cabin wall cavity, and the cabin inner wall is wrapped to form a middle cavity; the outer space cabin body is provided with a cabin body air inlet which is connected with the middle cavity, the gas control module is connected with the cabin body air inlet, and the gas control module controls the gas storage tank to supply gas for the middle cavity; the outer wall of the cabin body is provided with a cabin wall vent hole, and the exhaust assembly is connected with the cabin wall vent hole; the inner wall of the cabin body is provided with a heating film which heats the inorganic powder material. Through the processing scheme, the capsule is stably inflated and unfolded and reliably runs for a long time under the complex and severe environment of the outer space.
Description
Technical Field
The application relates to the technical field of spaceflight, in particular to an inorganic curing device for a space capsule.
Background
There are also deficiencies in the current technology of building space capsules. Taking an international space capsule as an example, the capacity and the diameter of the rocket are limited, the rocket can be spliced only by being launched for multiple times, the volume and the space of the space are yet to be further expanded, the construction time is long, new materials and design methods are urgently needed to further improve various technical properties of the space capsule, the size of the space capsule can be furthest expanded by an inflation unfolding mode, and the method is an important technical means for developing the construction of a large space capsule.
The inflatable expansion type space capsule BEAM developed by the American Biglow company adopts a space capsule made of aluminum and flexible composite materials, and although the structural rigidity is solved in a certain bearing, the expansion and the construction of the space capsule with larger size are difficult to realize; the other types of inflatable space capsule bodies with the expansion schemes need to comprise metal frameworks, because although the completely flexible capsule body expands to the required shape under air pressure, in order to ensure the stability of the whole capsule body in the space environment, the space capsule needs to have high rigidity so as to ensure the stability and the non-deformation of the whole structure, and the metal frameworks are added to be not beneficial to the expansion of the capsule body in a larger-size space. Therefore, how to stably and reliably realize the space expansion of the structure becomes one of the key points of the development of the inflation expansion mode.
In addition, the main body of the curing material adopted by the existing inflatable expansion structure is an organic material, and although the organic material can effectively realize the construction of various ultra-large space structures and space cabins, the service life of the organic material is inevitably shortened due to the influence of complex and severe environment in the space.
Therefore, in the prior art, how to prepare a space capsule with more excellent long-term on-orbit operation stability becomes a core technical problem which needs to be solved urgently.
SUMMERY OF THE UTILITY MODEL
In view of this, the embodiment of the present application provides an inorganic curing device for a capsule, which can realize inflation and deployment of a large-size capsule, and the main material of the capsule is an inorganic powder material, so that the requirement of long-term, stable and reliable operation of the capsule in a complex and severe environment in the outer space can be realized.
The embodiment of the application provides an inorganic curing device for a space capsule, which comprises a gas storage tank, a gas control module, a space capsule body and an exhaust assembly which are sequentially connected;
the outer space capsule comprises a capsule outer wall and a capsule inner wall, a closed capsule wall cavity is formed between the capsule outer wall and the capsule inner wall, inorganic powder materials with gas are filled in the capsule wall cavity, and the capsule inner wall is wrapped to form a middle cavity;
the outer space cabin body is provided with a cabin body air inlet, the cabin body air inlet is connected with the middle cavity, the gas control module is connected with the cabin body air inlet, and the gas control module controls the gas storage tank to supply gas for the middle cavity;
the outer wall of the cabin body is provided with a cabin wall vent hole, the exhaust assembly is connected with the cabin wall vent hole, and the exhaust assembly is used for exhausting gas in the cabin wall cavity;
and a heating film is arranged on the inner wall of the cabin body and is used for heating the inorganic powder material.
According to a specific implementation manner of the embodiment of the application, the exhaust assembly comprises a one-way valve and exhaust holes, the exhaust holes are symmetrically arranged at the air outlet end of the one-way valve, and the number of the exhaust holes is even; a filter member is provided in the check valve for preventing leakage of the inorganic powder material.
According to a concrete implementation mode of this application embodiment, be equipped with one-way adjusting part in the gas control module, one-way adjusting part is used for controlling gaseous one-way inflow in the gas holder middle cavity.
According to a concrete implementation mode of the embodiment of the application, a plurality of hollow upright posts are arranged between the outer wall of the cabin body and the inner wall of the cabin body, one ends of the hollow upright posts are connected with the outer wall of the cabin body, and the other ends of the hollow upright posts are connected with the inner wall of the cabin body.
According to a concrete implementation mode of this application embodiment, the outer wall of cabin body the inner wall of cabin body with the cavity stand all sets up to the fibre and weaves the structure, the sealing layer has all been laid to the surface of the outer wall of cabin body with the internal surface of the inner wall of cabin body.
According to a specific implementation of the embodiments of the present application, the gas in the inorganic powder material is air or an inert gas.
According to a specific implementation manner of the embodiment of the application, the working temperature range of the heating film is 35-80 ℃.
According to a specific implementation manner of the embodiment of the application, the gas control module is further connected with the outer wall of the cabin body, and the gas control module controls the gas storage tank to supply gas to the cabin wall cavity in a single direction; and the air outlet end of the exhaust assembly is connected with a vacuumizing assembly.
According to a concrete mode of realization of the embodiment of this application, the gas control module with pass through intake-tube connection between the outer wall of cabin body, be equipped with the pipeline check valve in the intake pipe, the pipeline check valve is used for controlling gaseous one-way inflow in the gas storage tank the bulkhead cavity.
Advantageous effects
The inorganic curing device for the space capsule in the embodiment of the application can realize the inflation and expansion of a large-size space capsule, and the main material of the space capsule is an inorganic powder material, so that the requirement of long-term, stable and reliable operation of the space capsule in a complex and severe environment of the outer space can be met.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic view of an inorganic curing apparatus for a space capsule according to an embodiment of the present invention;
FIG. 2 isbase:Sub>A sectional view taken along line A-A in FIG. 1;
fig. 3 is a schematic cross-sectional axial view of an inorganic curing apparatus for a space capsule according to an embodiment of the present invention;
fig. 4 is a schematic view of a space capsule according to an embodiment of the present invention;
fig. 5 is a schematic view of an area of inorganic powder material according to an embodiment of the present invention;
FIG. 6 is a schematic structural view of a flexible part of a space capsule according to an embodiment of the present invention;
fig. 7 is a schematic structural view of an exhaust assembly according to an embodiment of the present invention;
fig. 8 is a flow chart of an inorganic curing method for a space capsule according to an embodiment of the present invention;
fig. 9 is a cross-sectional view of an inorganic curing apparatus for a space capsule according to another embodiment of the present invention;
fig. 10 is a schematic cut-away axial view of an inorganic curing apparatus for a space capsule according to another embodiment of the present invention;
fig. 11 is a flow chart of an inorganic curing method for a space capsule according to another embodiment of the present invention.
In the figure: 1. a space capsule body; 1-1, outer wall of the cabin body; 1-2, hollow upright posts; 1-3, inner wall of the cabin body; 1-4, inorganic powder material; 1-5, a middle cavity; 1-6, cabin air inlet; 1-7, bulkhead cavity; 1-8, bulkhead vent holes; 1-9, upper surface layer; 1-10, lower surface layer; 2. a gas storage tank; 3. a gas control module; 4. a one-way valve; 5. an exhaust hole; 6. heating the film; 7. an air inlet pipe; 8. pipeline check valve.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
The following description of the embodiments of the present application is provided by way of specific examples, and other advantages and effects of the present application will be readily apparent to those skilled in the art from the disclosure herein. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The present application is capable of other and different embodiments and its several details are capable of modifications and/or changes in various respects, all without departing from the spirit of the present application. It is to be noted that the features in the following embodiments and examples may be combined with each other without conflict. 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.
It is noted that various aspects of the embodiments are described below within the scope of the appended claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art should appreciate that one aspect described herein may be implemented independently of any other aspects and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. Additionally, such an apparatus may be implemented and/or such a method may be practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.
It should be noted that the drawings provided in the following embodiments are only for illustrating the basic idea of the present application, and the drawings only show the components related to the present application rather than the number, shape and size of the components in actual implementation, and the type, amount and ratio of the components in actual implementation may be changed arbitrarily, and the layout of the components may be more complicated.
In addition, in the following description, specific details are provided to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that aspects may be practiced without these specific details.
In the research of the applicant, the prior art relates to a truss type rigidizable inflatable solar cell array, wherein the inflatable structure is composed of a gas isolation layer, an electrothermal layer, a cured layer and other multi-layer structures, the electrothermal layer provides heat required by curing organic materials of the cured layer, and the design can realize irreversible curing of the structure. The inflatable structure adopts a circumferential folding mode to realize the unfolding and the unfolding of the structure and realize the construction of a large-size space structure. And another inflatable curing chamber structure having a series of frame members made of fiber and resin that are inflated by inflation to a desired shape to effect deployment of the structure, the external influence rigidizing the structure. However, since the bulk materials of the above prior art are mainly organic materials, the ability to be stably allowed in space for a long period of time is desired to be further improved. Therefore, the applicant has conducted long-term experiments to overcome the problems of the prior art and to prepare an inorganic curing device for a space capsule, which can be operated stably and reliably for a long period of time, and the following detailed description is made with reference to the accompanying drawings.
The embodiment of the application provides an inorganic curing device for a space capsule, referring to fig. 1 to 3, the inorganic curing device comprises a gas storage tank 2, a gas control module 3, a space capsule 1 and an exhaust assembly which are sequentially connected, wherein the gas storage tank 2 and the gas control module 3 are gas sources in the device and are used for providing pressure-regulated gas for the interior of the space capsule 1 and inflating and unfolding the space capsule 1 into a preset shape. The gas control module 3 can control the pressure regulation and the on-off of the gas in the gas storage tank 2. The gas in the gas storage tank 2 is air, and the gas storage tank 2 is formed by winding carbon fibers and curing resin. The gas storage tank 2 and the gas control module 3 can be arranged in the uninflated and unfolded space capsule 1 or arranged outside the uninflated and unfolded space capsule 1, the work cycle is that the space capsule 1 is prepared to be unfolded under the condition that the outer space is positioned at a preset track and posture until the space capsule is cured and molded and the posture is adjusted again to finish a set task, and then the gas storage tank 2 and the gas control module 3 are only used for supplementing a small amount of leaked air in the space capsule 1 and are not used for inflating and supporting the cured space capsule 1. The gas control module 3 is internally provided with a one-way adjusting component which is used for controlling the gas in the gas storage tank 2 to flow into the middle cavities 1-5 in a one-way manner, and the air can not enter the gas storage tank 2 from the space capsule body 1 through the structure.
Referring to fig. 4, a space capsule 1 is described in detail, the space capsule 1 comprises an outer capsule wall 1-1 and an inner capsule wall 1-3, a closed bulkhead cavity 1-7 is formed between the outer capsule wall 1-1 and the inner capsule wall 1-3, the bulkhead cavity 1-7 is filled with inorganic powder materials 1-4 with gas, and the inner capsule wall 1-3 is wrapped to form an intermediate cavity 1-5. The capsule wall has the advantages that the inorganic powder materials 1-4 are adopted to fill the capsule wall cavities 1-7, the capsule wall has the advantages that the inorganic powder materials 1-4 can keep the stability of performance in a complex universe environment, and the requirement of long-term, stable and reliable operation of a capsule structure in space can be met.
The outer space capsule body 1 is provided with capsule body air inlets 1-6, the capsule body air inlets 1-6 are connected with the middle cavities 1-5, the gas control module 3 is connected with the capsule body air inlets 1-6, and the gas control module 3 controls the gas storage tank 2 to supply gas for the middle cavities 1-5.
As the cabin body structure is filled with the inorganic powder materials 1-4, the problems of gas content in the filling space and the flowability of the inorganic powder materials 1-4 need to be solved. If the filling space is free of gas, the frictional forces between the inorganic powder materials 1-4 are significantly increased, which interferes with a stable and reliable deployment of the entire structure. Because the inorganic powder is solidified in a mode of internal heating, if the filling space contains gas, the efficiency of transferring heating energy to the inorganic powder materials 1-4 is obviously affected, so that the inorganic powder materials 1-4 cannot be effectively solidified, and the final solidification quality of the whole structure is affected. Therefore, the outer wall 1-1 of the cabin body is provided with a cabin wall vent hole 1-8, and the exhaust assembly is connected with the cabin wall vent hole 1-8 and used for exhausting gas in the inorganic powder material 1-4. The inner wall 1-3 of the cabin body is provided with a heating film 6, and the heating film 6 is used for heating and curing the inorganic powder material 1-4.
In the above embodiment, the part of the intermediate cavity 1-5 is an effective working space of the outer space capsule 1, and the effective load and the space life facility can be arranged in the space. The bulkhead cavity 1-7 is filled with inorganic powder material 1-4, the inorganic powder material 1-4 contains gas inside before the bulkhead vent 1-8 is opened, and the gas inside is cleaned by the vent assembly after the bulkhead vent 1-8 is closed.
In practical use, the bulkhead cavities 1-7 in the space capsule 1 are internally filled with gas before the space capsule 1 is inflated and unfolded, so that the inorganic powder materials 1-4 have certain fluidity, and the space capsule 1 has certain flexibility and can be folded to reduce the total volume. The air in the bulkhead cavity 1-7 in the space cabin body 1 is exhausted out of the device, so that the bulkhead cavity 1-7 can avoid the bulging state caused by the gas in the bulkhead cavity 1-7, the inorganic powder material 1-4 in the bulkhead cavity is tightly gathered, and the precondition is provided for the reaction, solidification and hardening of the subsequent inorganic powder material 1-4. After the outer space capsule 1 is inflated and unfolded, the exhaust assembly is opened, the air in the bulkhead cavities 1-7 in the outer space capsule 1 leaks into the vacuum environment along the exhaust assembly, and the exhaust assembly is closed after a certain time.
Further, a plurality of hollow upright columns 1-2 are arranged between the outer wall 1-1 of the cabin body and the inner wall 1-3 of the cabin body, one end of each hollow upright column 1-2 is connected with the outer wall 1-1 of the cabin body, and the other end of each hollow upright column 1-2 is connected with the inner wall 1-3 of the cabin body. The outer wall 1-1 of the cabin body is connected with the inner wall 1-3 of the cabin body through a hollow upright post 1-2, and a closed cabin wall cavity 1-7 space is formed.
In one embodiment, the outer wall 1-1 of the cabin body, the hollow upright post 1-2 and the inner wall 1-3 of the cabin body are all formed by weaving special fibers in a three-dimensional way, and the special fibers can be carbon fibers or mixed fibers of the carbon fibers and other fibers; the hollow upright posts 1-2 are of a flexible fiber weaving structure.
In order to ensure the sealing property, sealing layers are respectively paved on the outer surface of the outer wall 1-1 of the cabin body and the inner surface of the inner wall 1-3 of the cabin body, referring to fig. 6, the sealing layers are respectively an upper surface layer 1-9 and a lower surface layer 1-10, which can ensure the space isolation, wherein the upper surface layer 1-9 is mainly used for sealing the outer surface of the space cabin body 1, and the lower surface layer 1-10 is mainly used for sealing the surface of the internal middle cavity 1-5 of the space cabin body 1. The lower surface layers 1-10 are positioned inside the space capsule body 1, cannot be influenced by the severe vacuum environment of the space and are made of organic materials. The upper surface layers 1-9 are also made of organic materials to finish the forming of the flexible sealing surfaces, but because the inorganic powder materials 1-4 are changed from powder materials into hard block materials in the space, the internal structure of the space capsule body 1 is not influenced even if the materials of the upper surface layers 1-9 age, and the sealing of the whole space capsule body 1 is completely finished by the sealing structures of the lower surface layers 1-10 positioned in the space capsule body 1, so that the long-term operation stability and reliability of the whole space capsule structure are ensured.
Referring to the schematic diagram of the inorganic powder material region shown in fig. 5, the inorganic powder materials 1-4 in the bulkhead cavities 1-7 are in the form of flowable inorganic powder materials before entering the space, and after entering the space and being heated by the heating film 6, the flowable inorganic powder materials undergo physicochemical changes to form hard inorganic bulk materials. Because the material is composed of inorganic matters, the long-term reliable operation can be realized in the outer space without aging, and the structural rigidity is higher, the shape structure of the outer space capsule body 1 can be supported, so that the problems that the air storage tank 2 is required to continuously supply air and the flexible outer space capsule body 1 is required to be maintained are solved, and the long-term operation reliability of the whole device structure is further improved.
In one embodiment, the exhaust assembly forms an exhaust part of the bulkhead cavities 1-7 of the space capsule 1, the exhaust assembly comprises a one-way valve 4 and exhaust holes 5, referring to fig. 7, the exhaust holes 5 are symmetrically arranged at the air outlet end of the one-way valve 4, and the number of the exhaust holes 5 is even; the check valve 4 is provided therein with a filter member for preventing leakage of the inorganic powder materials 1 to 4. The filtering component in the one-way valve can prevent the inorganic powder material 1-4 in the chamber wall cavity 1-7 from escaping into the vacuum environment along with the gas during the gas releasing process. The one-way valve 4 has on-off functions and can realize the on-off of an airflow channel.
In this embodiment, the number of the exhaust holes 5 is 2, and the exhaust holes are symmetrically arranged, and two exhaust ports in opposite directions are designed, so that the structure does not generate additional moment, and the interference to the attitude and the orbit of the space capsule body 1 in the gas release process can be avoided.
As will be described in detail below with respect to the heating film 6, the reaction and hardening of the inorganic powder materials 1-4 requires the heating film 6 to provide a heat input. After gas in the bulkhead cavity 1-7 of the outer space capsule body 1 leaks to the outer space vacuum environment through the vent hole 5 and the one-way valve 4 is closed, power is supplied to the heating film 6, the working temperature range of the heating film 6 is between 35 ℃ and 80 ℃, the heating film 6 is closed when the inorganic powder material 1-4 in the bulkhead cavity 1-7 of the outer space capsule body 1 is heated, and the heating process is not less than half an hour after the inorganic powder material 1-4 is reacted and hardened. The heating film 6 is arranged at the position of the outer space capsule body 1 which needs the heat source input most, the position is determined after the overall heat transfer simulation of the outer space capsule body 1, the inorganic powder materials 1-4 in the bulkhead cavity 1-7 of the outer space capsule body 1 can be uniformly heated through the design of the heating film 6, the working temperature of the heating film 6 can be within 35-80 ℃, and the phenomenon of nonuniform reaction and solidification caused by excessively low local working temperature is avoided.
In any of the above embodiments, the gas in the inorganic powder materials 1-4 may be air or an inert gas.
The curing method of the inorganic curing device for a space capsule of any of the above embodiments is described in detail below, and with reference to fig. 8, the method includes:
step 101, the inorganic curing device is sent into the outer space, the position and the posture are adjusted on a preset track, and the inorganic curing device is positioned in the vacuum environment of the outer space;
step 102, opening the gas control module 3, supplying gas to the intermediate cavities 1-5 through the gas storage tank 2, so that the space cabin body is changed from a folded state to an inflated state, keeping the state for a period of time, and the internal gas pressure of the intermediate cavities 1-5 is not lower than 1.2MPa;
step 103, opening the vent assembly, leaking the gas in the bulkhead cavity 1-7 through the bulkhead vent port 1-8 into the space vacuum environment, and closing the vent assembly. Specifically, the one-way valve 4 is opened, the gas in the bulkhead cavities 1-7 of the outer space cabin 1 is leaked to the outer space vacuum environment through the bulkhead vent holes 1-8, and the one-way valve 4 is closed.
Step 104, opening the heating film 6, heating the inorganic powder materials 1-4 in the bulkhead cavities 1-7, and closing the heating film 6 after the inorganic powder materials 1-4 react and harden;
105, adjusting the internal air pressure of the intermediate cavity 1-5 to be less than 1.2MPa, and testing the curing effect of the outer space capsule body 1;
and 106, curing and molding the space capsule body 1, and adjusting the posture of the inorganic curing device again to complete a set task.
In one embodiment, in order to make the bulkhead cavity 1-7 of the space capsule 1 in a vacuum state before entering the space, the inorganic curing device for the space capsule is modified, referring to fig. 9 and 10, a vacuum-pumping assembly is connected to the air outlet end of the exhaust assembly, and the vacuum-pumping assembly performs vacuum-pumping on the bulkhead cavity 1-7; the gas control module 3 is also connected with the outer wall 1-1 of the cabin body, and the gas control module 3 controls the gas storage tank 2 to supply gas for the cabin wall cavity 1-7 in a one-way mode.
Specifically, the gas control module 3 is connected with the outer wall 1-1 of the cabin body through a gas inlet pipe 7, a pipeline one-way valve 8 is arranged on the gas inlet pipe 7, and the pipeline one-way valve 8 is used for controlling the gas in the gas storage tank 2 to flow into the cabin wall cavity 1-7 in a one-way mode.
The following describes a curing method of the inorganic curing device for a space capsule of this embodiment, and with reference to fig. 11, the method specifically includes:
step 201, pumping out the gas in the bulkhead cavities 1-7 through the exhaust assembly, and loading the vacuumized inorganic curing device into a carrier. Specifically, inorganic powder materials 1-4 are filled in a bulkhead cavity 1-7 of an inorganic curing device, the inorganic curing device filled with powder is folded, the gas in the bulkhead cavity 1-7 is pumped out through a one-way valve 4 and a vacuumizing assembly, and then the inorganic curing device is loaded into a carrier;
step 202, the inorganic curing device is sent into the outer space, the position and the posture are adjusted on a preset track, and the inorganic curing device is positioned in the vacuum environment of the outer space;
step 203, opening the gas control module 3, and filling gas into the bulkhead cavity 1-7 through the gas storage tank 2, the gas inlet pipe 7 and the pipeline one-way valve 8 to enable the air pressure in the bulkhead cavity 1-7 to be not lower than 0.01MPa;
step 204, opening the gas control module 3, supplying gas to the intermediate cavity 1-5 through the gas storage tank 2, so that the space cabin body 1 is changed from a folded state to an inflated state, keeping the state for a period of time, and the internal gas pressure of the intermediate cavity 1-5 is not lower than 1.2MPa;
step 205, opening a one-way valve 4 in the exhaust assembly, leaking gas in the bulkhead cavities 1-7 into the space vacuum environment through the bulkhead exhaust holes 1-8, and closing the one-way valve 4;
step 206, opening the heating film 6, heating the inorganic powder materials 1-4 in the bulkhead cavities 1-7, and closing the heating film 6 after the inorganic powder materials 1-4 react and harden;
step 207, adjusting the internal air pressure of the intermediate cavity 1-5 to be less than 1.2MPa, and testing the curing effect of the outer space capsule body 1;
and step 208, curing and molding the outer space capsule body 1, and adjusting the posture of the inorganic curing device again to complete the set task.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (9)
1. An inorganic curing device for a space capsule is characterized by comprising a gas storage tank, a gas control module, a space capsule body and an exhaust assembly which are sequentially connected;
the outer space capsule comprises a capsule outer wall and a capsule inner wall, a closed capsule wall cavity is formed between the capsule outer wall and the capsule inner wall, inorganic powder materials with gas are filled in the capsule wall cavity, and the capsule inner wall is wrapped to form a middle cavity;
the space cabin body is provided with a cabin body air inlet which is connected with the middle cavity body, the gas control module is connected with the cabin body air inlet, and the gas control module controls the gas storage tank to supply gas for the middle cavity body;
the outer wall of the cabin body is provided with a cabin wall vent hole, the exhaust assembly is connected with the cabin wall vent hole, and the exhaust assembly is used for exhausting gas in the cabin wall cavity;
and a heating film is arranged on the inner wall of the cabin body and is used for heating the inorganic powder material.
2. The inorganic curing device for the space capsule as recited in claim 1, wherein the exhaust assembly comprises a one-way valve and an exhaust hole, the exhaust hole is symmetrically arranged at the air outlet end of the one-way valve, and the number of the exhaust holes is even; a filter member is provided in the check valve for preventing leakage of the inorganic powder material.
3. The inorganic solidification device for a space capsule of claim 1, wherein a unidirectional adjustment component is disposed in the gas control module, and the unidirectional adjustment component is used for controlling the unidirectional flow of the gas in the gas tank into the intermediate cavity.
4. The inorganic curing device for the space capsule as claimed in claim 1, wherein a plurality of hollow upright posts are arranged between the outer wall and the inner wall of the capsule, one end of each hollow upright post is connected with the outer wall of the capsule, and the other end of each hollow upright post is connected with the inner wall of the capsule.
5. The inorganic curing device for the space capsule as claimed in claim 4, wherein the outer wall of the capsule body, the inner wall of the capsule body and the hollow upright post are all arranged in a fiber woven structure, and sealing layers are respectively paved on the outer surface of the outer wall of the capsule body and the inner surface of the inner wall of the capsule body.
6. The inorganic curing apparatus for a space capsule of claim 1, wherein the gas in the inorganic powder material is air or an inert gas.
7. The inorganic curing apparatus for a space capsule according to claim 1, wherein the operating temperature of the heating film is in a range of 35 ℃ to 80 ℃.
8. The inorganic solidification apparatus for a space capsule of any one of claims 1 to 7, wherein the gas control module is further connected to an outer wall of the capsule body, the gas control module controls the gas storage tank to supply gas to the capsule wall cavity in one direction; and the air outlet end of the exhaust assembly is connected with a vacuumizing assembly.
9. The inorganic curing device for the space capsule as claimed in claim 8, wherein the gas control module is connected with the outer wall of the capsule body through a gas inlet pipe, and a pipeline check valve is arranged on the gas inlet pipe and used for controlling the gas in the gas storage tank to flow into the bulkhead cavity in a one-way mode.
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| CN202222157473.5U CN218172634U (en) | 2022-08-17 | 2022-08-17 | Inorganic curing device for space capsule |
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| CN202222157473.5U CN218172634U (en) | 2022-08-17 | 2022-08-17 | Inorganic curing device for space capsule |
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