Design method of cryogenic cabin for satellite

Abstract

The application provides a design method of a low-temperature cabin for a satellite, comprising the following steps: step S1: selecting a cabin section as a low-temperature cabin of the satellite, and the rest as non-low-temperature cabins; step S2: analyzing satellite cabin plates involved in an outer envelope of the low-temperature cabin, and disconnecting the satellite cabin plates at a boundary between the low-temperature cabin and the non-low-temperature cabins; step S3: counting total heat consumption of single machines in the low-temperature cabin, calculating a required heat dissipation area of the low-temperature cabin according to an energy balance equation, and opening a heat dissipation surface on a surface of a cabin plate on a side of the low-temperature cabin facing a cold space; and step S4: coating a multi-layer thermal insulation assembly on a side of a cabin plate of the low-temperature cabin facing the non-low-temperature cabin, and spraying a thermal control coating on a surface of the heat dissipation surface. The application insulates heat exchange between the low-temperature cabin and other areas of the satellite and opens the heat dissipation surface, so that the low-temperature cabin becomes an independent and stable low-temperature environment cabin section, the single machines with a lower working temperature on the satellite can work normally, the waste of the cabin plate area is small, and the adaptability to different satellites is high.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control technology, and more specifically, to a design method for a cryogenic chamber for spacecraft. Background Technology

[0002] A unit is a module on a satellite with a specific function. Different units have different operating temperature ranges, and the task of the satellite thermal control subsystem is to maintain the temperature of all units within the specified range. On some satellites, due to the high power consumption of the entire satellite, the internal ambient temperature is high, and some units that need to operate at low temperatures cannot adapt to this.

[0003] A Chinese patent with publication number CN110920937A discloses a high-heat-dissipation, high-density payload cabin for geosynchronous orbit satellites, belonging to the field of payload cabin design. It includes a cabin body and a cable laying channel. The cabin body is a hollow cuboid structure. The cable laying channel is arranged in a shrub-like pattern inside the cabin body. The cable laying channel is laid along a vertical plane. External equipment is placed inside the cabin body. The cabin's interior cavity is divided into two symmetrical areas of the same size, designated as a first area and a second area. Both areas are used to house external equipment. The space of the first area is vertically divided into a frequency conversion area and a first isothermal low-temperature area. The space of the second area is vertically divided into a high-temperature area and a second isothermal low-temperature area. External equipment is initially placed inside the cabin according to the area divisions. The center of gravity is adjusted, and the installation of the external equipment is finally completed.

[0004] Traditional thermal control methods involve placing units that require low-temperature operation in different areas of the satellite module when installing individual units on the module, in order to reduce the impact of heat conduction and radiation. The drawbacks of this approach are that large gaps must be left between the units, resulting in wasted heat dissipation area on the satellite module. Furthermore, when the satellite's heat dissipation is excessive, the temperature in all areas within the entire satellite becomes high.

[0005] Therefore, there is a need to provide a design method for a cryogenic chamber for spacecraft to solve the above problems. Summary of the Invention

[0006] In view of the deficiencies in the prior art, the purpose of this invention is to provide a design method for a cryogenic chamber for space use.

[0007] A design method for a cryogenic chamber for space use according to the present invention includes the following steps: Step S1: Based on the single-unit layout on the satellite, select one module as the satellite's cryogenic module, and the rest are non-cryopreservative modules. Step S2: Analyze the satellite panels involved in the outer envelope of the cryogenic chamber, and disconnect the satellite panels at the interface between the cryogenic chamber and the non-cryocyst chamber. Step S3: Calculate the total heat consumption of a single unit in the cryogenic chamber, calculate the required heat dissipation area of ​​the cryogenic chamber according to the energy balance equation, and open a heat dissipation surface on the side of the cryogenic chamber facing the cold space. Step S4: Cover the side of the cryogenic chamber facing the non-cryogenic chamber with a multi-layer heat insulation component and spray a thermal control coating on the heat dissipation surface.

[0008] Preferably, in step S1, the external heat flow of the satellite is analyzed, and the section with low solar radiation intensity and low influence from Earth's infrared radiation is selected as the satellite's cryogenic chamber.

[0009] Preferably, when the entire star is a cube, the front side is the +X face, the right side is the +Y face, and the top face is the +Z face; In step S1, when the satellite is a geostationary orbit satellite or a sun-synchronous orbit satellite, the cryogenic chamber is set in the +Y or -Y plane; when the satellite is an inclined orbit satellite, the cryogenic chamber is not set in the +Z plane.

[0010] Preferably, in step S2, the satellite module has two rows of embedded parts on its layer, which are used to install the non-cryo-temperature module and the cryogenic module respectively.

[0011] Preferably, in step S3, the total heat consumption of a single unit within the cryogenic chamber is calculated. This paper analyzes the external heat flow received by each panel of the cryogenic chamber. Assume the cryogenic chamber has n panels, where n is a positive integer. The panels are ordered in ascending order of external heat flow, designated as the first panel, second panel, and so on up to the nth panel. Their external heat flows are as follows: , to The areas of the cabin panels are respectively , to Starting from the first compartment, we sequentially determine whether the heat dissipation capacity is greater than the input heat, and then decide the area of ​​the heat dissipation surface to be opened on the compartment.

[0012] Preferably, step S3 includes the following steps: Step S31: Analyze whether the first compartment can meet the heat dissipation requirements, that is, determine whether the following formula is true; ; In the formula It is the Stephen-Boltzmann constant. T represents the infrared emissivity of the thermal control coating sprayed on the heat dissipation surface, and T represents the high temperature index of the single unit. If the above formula holds true, then only compartment 1 needs to be provided as a heat dissipation surface, and the heat dissipation area provided by compartment 1 is... Determined by the following formula; ; If the above equation is not true, proceed to the next step; Step S32: Analyze whether the first and second compartments can meet the heat dissipation requirements, that is, determine whether the following formula is true; ; If the above formula holds true, then only the first and second compartment plates need to be provided as heat dissipation surfaces. All surfaces of the first compartment plate should have heat dissipation surfaces, and the heat dissipation area of ​​the second compartment plate should be... Determined by the following formula; ; If the above equation is not true, proceed to the next step; Step S33: For the m-th compartment plate, analyze whether the first compartment plate, the second compartment plate, and so on up to the m-th compartment plate m can meet the requirements, that is, determine whether the following formula is true; ; If the above formula holds true, then only the first compartment plate 1, the second compartment plate to the m-th compartment plate need to be provided as heat dissipation surfaces. All surfaces of the first compartment plate 1, the second compartment plate to the (m-1)-th compartment plate are provided with heat dissipation surfaces, and the heat dissipation area provided by the m-th compartment plate is... Determined by the following formula; .

[0013] Preferably, in step S4, the multilayer heat insulation component comprises, from the inside out: one 25μm thick polyimide film, 15 heat insulation layers, and one 16μm thick double-sided aluminized polyester film. Each heat insulation layer is composed of one layer of polyester mesh T-20 and one 6μm thick double-sided aluminized polyester film.

[0014] Preferably, in step S4, the thermal control coating includes OSR or thermal control white paint.

[0015] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention creates an independent and stable low-temperature environment inside the satellite by separating the cryogenic chamber from the non-cryo chamber through a panel, thus isolating them in terms of heat conduction. The cryogenic chamber panel is covered with multiple layers of heat insulation components facing the non-cryo chamber, thus isolating them in terms of heat radiation. This provides a suitable placement location for individual units that need to work at low temperatures. 2. By isolating the cryogenic chamber from heat exchange with other areas of the satellite and opening a heat dissipation surface on the side of the cryogenic chamber facing the cold space, this invention ensures that the cryogenic chamber becomes an independent and stable cryogenic environment section, enabling individual units on the satellite with low operating temperatures to work normally, minimizing waste of chamber area, and providing strong adaptability to different satellites. Attached Figure Description

[0016] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a flowchart illustrating the design method of a cryogenic chamber for spacecraft, which is the main feature of this invention. Figure 2 This is a schematic diagram illustrating the location of the cryogenic chamber, which is the main feature of this invention. Figure 3 This is a schematic diagram illustrating the structure of each compartment panel of the cryogenic chamber, which is the main feature of this invention.

[0017] The diagram shows: cryogenic chamber 1, non-cryore chamber 2, +Y panel 11, +X panel 12, -X panel 13, platform lower chamber floor 14, bulkhead 15, and platform upper chamber top 16. Detailed Implementation

[0018] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0019] like Figures 1 to 3 As shown, a design method for a cryogenic chamber for spacecraft according to the present invention includes the following steps: Step S1: Based on the existing single-unit layout on the satellite, select one section as the satellite's cryogenic chamber 1 to house the single units that need to work at low temperatures, and the rest are non-cryo-temperature chambers 2. Step S2: Analyze the satellite panels involved in the outer envelope of cryogenic chamber 1, and break the original whole satellite panel at the interface between cryogenic chamber 1 and non-cryocystorhinos 2, thereby generating a high-temperature chamber panel and a cryogenic chamber panel. Step S3: Calculate the total heat consumption of the single unit that needs to work at low temperature in the cryogenic chamber 1, and analyze and calculate the heat dissipation area required by the cryogenic chamber 1 according to the energy balance equation. On the side of the cryogenic chamber 1 facing the cold space, open a heat dissipation surface on the surface of the chamber plate. Step S4: Cover the side of the cryogenic chamber 1 facing the non-cryogenic chamber 2 with a multi-layer heat insulation component to isolate the heat exchange between the cryogenic chamber 1 and the non-cryogenic chamber 2, and spray a heat control coating on the heat dissipation surface.

[0020] More specifically, in step S1, the external heat flow of the satellite is analyzed, and the section that is less affected by solar radiation and less affected by Earth's infrared radiation is selected as the satellite's cryogenic chamber 1.

[0021] When the entire module is a cube, the front side is the +X surface, the right side is the +Y surface, and the top surface is the +Z surface. In step S1, when the satellite is a geostationary orbit satellite or a sun-synchronous orbit satellite, the area with less external heat flow is generally the module section close to the +Y or -Y surface of the entire satellite, that is, the cryogenic module is set on the +Y or -Y surface. When the satellite is an inclined orbit satellite, the area with less external heat flow generally needs to avoid the +Z surface, that is, the cryogenic module is not set on the +Z surface.

[0022] In step S2, after a high-temperature cabin panel and a low-temperature cabin panel are generated on the satellite cabin panel, two rows of embedded parts need to be set on the layer of the satellite cabin panel, which are used to install the non-low-temperature cabin 2 panel and the low-temperature cabin 1 panel respectively.

[0023] In step S3, based on the total heat consumption of the single unit and the external heat flux of each compartment, it is necessary to determine whether the heat dissipation capacity of each compartment is greater than the input heat, thereby determining the area of ​​the heat dissipation surface to be opened on the compartment. Priority should be given to selecting compartments with smaller external heat flux for heat dissipation. The total heat consumption of the single unit in cryogenic chamber 1 is then calculated. Analyze the external heat flow received by each panel of cryogenic chamber 1. Assume cryogenic chamber 1 has n panels, where n is a positive integer, ordered by external heat flow from smallest to largest as panel 1, panel 2 to panel n, and their external heat flows are respectively... , to The areas of the cabin panels are respectively , to Starting from the first compartment, we sequentially determine whether the heat dissipation capacity is greater than the input heat, and then decide the area of ​​the heat dissipation surface to be opened on the compartment.

[0024] Step S3 includes the following steps: Step S31: Analyze whether the first compartment can meet the heat dissipation requirements, that is, determine whether the following formula is true; ; In the formula This is the Stephen-Boltzmann constant, typically taking the value of [value missing]. , The infrared emissivity of the thermal control coating sprayed on the heat dissipation surface is generally 0.8 for OSR-type thermal control coatings commonly used on satellites and 0.9 for white paint-type thermal control coatings commonly used on satellites. T is the high temperature index of the single unit that needs to operate at low temperature. If the above formula holds true, then only compartment 1 needs to be provided as a heat dissipation surface, and the heat dissipation area provided by compartment 1 is... Determined by the following formula; ; If the above equation is not true, proceed to the next step; Step S32: Analyze whether the first and second compartments can meet the heat dissipation requirements, that is, determine whether the following formula is true; ; If the above formula holds true, then only the first and second compartment plates need to be provided as heat dissipation surfaces. All surfaces of the first compartment plate should have heat dissipation surfaces, and the heat dissipation area of ​​the second compartment plate should be... Determined by the following formula; ; If the above equation is not true, proceed to the next step; Step S33: Repeat the above steps. For the m-th compartment plate, analyze whether the first compartment plate, the second compartment plate, and up to the m-th compartment plate m can meet the requirements, that is, determine whether the following formula is true. ; If the above formula holds true, then only the first compartment plate 1, the second compartment plate to the m-th compartment plate need to be provided as heat dissipation surfaces. All surfaces of the first compartment plate 1, the second compartment plate to the (m-1)-th compartment plate are provided with heat dissipation surfaces, and the heat dissipation area provided by the m-th compartment plate is... Determined by the following formula; .

[0025] In step S4, the multi-layer heat insulation component can effectively isolate the radiative heat exchange between the cryogenic chamber 1 and the non-cryo-temperature chamber 2. The multi-layer heat insulation component includes, from the inside out: a 25μm thick polyimide film, 15 heat insulation layers, and a 16μm thick double-sided aluminized polyester film. Each heat insulation layer is composed of a layer of polyester mesh T-20 and a 6μm thick double-sided aluminized polyester film.

[0026] In step S4, the thermal control coating needs to have the characteristics of low solar absorptivity and high infrared emissivity. In the field of satellite thermal control, commonly used thermal control coatings include OSR or thermal control white paint.

[0027] This application will be described in detail using the following examples: Step S1: On a certain satellite, five individual units need to operate in an environment below 20°C, while the overall thermal environment temperature of the satellite is 40°C. Therefore, a cryogenic chamber 1 needs to be designed to house the five individual units. Analysis shows that the external heat flux of the lower +Y side compartment of the satellite is relatively small; therefore, the lower +Y side compartment is selected as the cryogenic chamber 1 of the satellite. Step S2: The outer envelope of the satellite's +Y side lower compartment involves a total of 6 panels, namely +Y panel 11, +X panel 12, -X panel 13, platform lower compartment bottom plate 14, bulkhead 15, and platform lower compartment top plate 16. Among them, +Y panel 11, +X panel 12, and -X panel 13 span the cryogenic compartment 1 and the non-cryo ... Step S3: The total heat consumption of the 5 individual units is 310W. Analysis shows that among the 6 panels enclosing the cryogenic chamber, bulkhead 15 and the lower platform top plate 16 do not directly face the cold space and therefore cannot dissipate heat. The external heat flux of the remaining 4 panels, from smallest to largest, is as follows: +Y panel 11: 112W, +X panel 12: 259W, -X panel 13: 259W, and lower platform bottom plate 14: 282W. The panel areas are 1.02m² respectively. 2 0.96m 2 0.96m 2 2.46m 2 In this embodiment, the thermal control coating sprayed on the heat dissipation surface is an OSR type thermal control coating with a solar absorptivity of 0.2 and an infrared emissivity of [missing value]. The value is 0.8. Step S31: Analyze whether the +Y compartment can meet the heat dissipation requirements. ; Calculations show that the left side of the inequality is 424.24 and the right side is 340.99, therefore the inequality is invalid. Thus, all heat dissipation surfaces are opened on the +Y compartment 11, and the next compartment with a smaller external heat flow is selected to open heat dissipation surfaces. Step S32: The external heat flow of +X compartment 12 and -X compartment 13 is the same, so they can be analyzed as a single plate. Analyze whether +X compartment 12 and -X compartment 13 can meet the heat dissipation requirements. ; Calculations show that the left side of the inequality is 921.52 and the right side is 982.86, therefore the inequality holds. Thus, the +Y compartment 11 has all its heat dissipation surfaces, while the +X and -X compartments 12 and 13 have partial heat dissipation surfaces, which can meet the heat dissipation requirements of the cryogenic compartment 1. The heat dissipation areas of the +X and -X compartments are calculated using the following formula: ; Substitute into the calculation to obtain It is 1.1m 2 In this embodiment, the +X compartment 12 and the -X compartment 13 each have a 0.55m opening. 2 Size of heat dissipation surface; Step S4: The compartment panels facing the non-cryogenic compartment 2 of the cryogenic compartment 1 have a partition 15 and a platform under-compartment top plate 16. Therefore, multiple layers of heat insulation components are covered on the surface of these two compartment panels to isolate the heat exchange between the cryogenic compartment 1 and the high-temperature compartment. The compartment panels facing the cold space of the cryogenic compartment 1 have a +Y compartment panel 11, a +X compartment panel 12, a -X compartment panel 13, and a platform under-compartment bottom plate 14. An OSR type thermal control coating is sprayed on the surface of the +Y compartment panel 11, the +X compartment panel 12, and the -X compartment panel 13 to achieve the purpose of opening heat dissipation surfaces.

[0028] This application creates an independent and stable low-temperature environment inside the satellite by separating the cryogenic chamber 1 from the non-cryo-temperature chamber 2 through a panel, thus isolating them in terms of heat conduction. The panel of the cryogenic chamber 1 is covered with multiple layers of heat insulation components facing the non-cryo-temperature chamber 2, thus isolating them in terms of heat radiation. This provides a suitable placement location for individual units that need to operate at low temperatures.

[0029] This application ensures that the cryogenic chamber 1 becomes an independent and stable cryogenic environment section by isolating the cryogenic chamber 1 from heat exchange with other areas of the satellite and opening a heat dissipation surface on the side of the cryogenic chamber 1 facing the cold space. This allows the single unit on the satellite with a low operating temperature to work normally, minimizes the waste of the chamber area, and has strong adaptability to different satellites.

[0030] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0031] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A design method for a cryogenic chamber for space applications, characterized in that, Includes the following steps: Step S1: Based on the existing single-unit layout on the satellite, select one section as the cryogenic chamber (1) of the satellite, and the rest are non-cryo-temperature chambers (2). Step S2: Analyze the satellite panels involved in the outer envelope of the cryogenic chamber (1) and disconnect the satellite panels at the interface between the cryogenic chamber (1) and the non-cryocystorhinos (2); Step S3: Calculate the total heat consumption of a single unit in the cryogenic chamber (1), calculate the required heat dissipation area of ​​the cryogenic chamber (1) according to the energy balance equation, and open a heat dissipation surface on the side of the cryogenic chamber (1) facing the cold space. Step S4: Cover the side of the cryogenic chamber (1) facing the non-cryogenic chamber (2) with a multi-layer heat insulation component and spray a heat control coating on the heat dissipation surface.

2. The design method for a cryogenic chamber for spacecraft as described in claim 1, characterized in that, In step S1, the external heat flow of the satellite is analyzed, and the section with less solar radiation intensity and less influence from Earth's infrared radiation is selected as the satellite's cryogenic chamber (1).

3. The design method for a cryogenic chamber for spacecraft as described in claim 1, characterized in that, When the entire compartment is a cube, the front side is the +X face, the right side is the +Y face, and the top face is the +Z face; In step S1, when the satellite is a geostationary orbit satellite or a sun-synchronous orbit satellite, the cryogenic chamber (1) is set in the +Y or -Y plane. When the satellite is an inclined orbit satellite, the cryogenic chamber (1) is not set in the +Z plane.

4. The design method for a cryogenic chamber for spacecraft as described in claim 1, characterized in that, In step S2, two rows of embedded parts are provided on the satellite module, which are used to install the non-cryogenic module (2) module and the cryogenic module (1) module respectively.

5. The design method for a cryogenic chamber for spacecraft as described in claim 1, characterized in that, In step S3, the total heat consumption of a single unit inside the cryogenic chamber (1) is calculated. Analyze the external heat flow received by each panel of the cryogenic chamber (1). Assume that the cryogenic chamber (1) has n panels, where n is a positive integer, and they are ordered in ascending order of external heat flow as the first panel, the second panel, to the nth panel, with their external heat flows being respectively... , to The areas of the cabin panels are respectively , to Starting from the first compartment, we sequentially determine whether the heat dissipation capacity is greater than the input heat, and then decide the area of ​​the heat dissipation surface to be opened on the compartment.

6. The design method for a cryogenic chamber for space use as described in claim 5, characterized in that, Step S3 includes the following steps: Step S31: Analyze whether the first compartment can meet the heat dissipation requirements, that is, determine whether the following formula is true; ； In the formula It is the Stephen-Boltzmann constant. T represents the infrared emissivity of the thermal control coating sprayed on the heat dissipation surface, and T represents the high temperature index of the single unit. If the above formula holds true, then only compartment 1 needs to be provided as a heat dissipation surface, and the heat dissipation area provided by compartment 1 is... Determined by the following formula; ； If the above equation is not true, proceed to the next step; Step S32: Analyze whether the first and second compartments can meet the heat dissipation requirements, that is, determine whether the following formula is true; ； If the above formula holds true, then only the first and second compartment plates need to be provided as heat dissipation surfaces. All surfaces of the first compartment plate should have heat dissipation surfaces, and the heat dissipation area of ​​the second compartment plate should be... Determined by the following formula; ； If the above equation is not true, proceed to the next step; Step S33: For the m-th compartment plate, analyze whether the first compartment plate, the second compartment plate, and so on up to the m-th compartment plate m can meet the requirements, that is, determine whether the following formula is true; ； If the above formula holds true, then only the first compartment plate 1, the second compartment plate to the m-th compartment plate need to be provided as heat dissipation surfaces. All surfaces of the first compartment plate 1, the second compartment plate to the (m-1)-th compartment plate are provided with heat dissipation surfaces, and the heat dissipation area provided by the m-th compartment plate is... Determined by the following formula; 。 7. The design method for a cryogenic chamber for spacecraft as described in claim 1, characterized in that, In step S4, the multi-layer heat insulation component comprises, from the inside out: a 25μm thick polyimide film, 15 heat insulation layers, and a 16μm thick double-sided aluminized polyester film. Each heat insulation layer is composed of a layer of polyester mesh T-20 and a 6μm thick double-sided aluminized polyester film.

8. The design method for a cryogenic chamber for spacecraft as described in claim 1, characterized in that, In step S4, the thermal control coating includes OSR or thermal control white paint.

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