Structural thermal control integrated load-bearing parts

Abstract

The present application relates to the field of aerospace technology, specifically, to a structural thermal control integrated load-bearing component, comprising a liquid injection end cover and a main body, wherein a plurality of thermal control working fluid channels arranged parallel to each other are formed in the main body, and a port on one side of each thermal control working fluid channel is sealed in a first direction, and a port on the other side of each thermal control working fluid channel is sealed and connected to the liquid injection end cover so as to inject thermal control working fluid into each thermal control working fluid channel through the liquid injection end cover, wherein the main body has a mounting surface, the first direction is parallel to the mounting surface, and the distribution direction of each thermal control working fluid channel is parallel to the mounting surface, the first direction is the length direction of the thermal control working fluid channel, and the distribution direction of each thermal control working fluid channel is a second direction. The purpose of the present application is to provide a structural thermal control integrated load-bearing component in response to at least one technical problem involved in the background technology.

Description

Technical Field

[0001] The present application relates to the field of aerospace technology, and in particular to a structural thermal control integrated load-bearing component. Background Art

[0002] Generally speaking, a spacecraft can be divided into two major components: the payload and the spacecraft platform. The spacecraft platform typically includes the attitude and orbit control subsystem, the structure and mechanical subsystem, the thermal control subsystem, the power supply subsystem, and the measurement, control, and data management subsystem. Each subsystem is typically developed by a different research and development unit, with the top-level design of the spacecraft platform being led by the system, mechanical, and electrical engineering departments.

[0003] In existing non-integrated spacecraft structure-thermal control systems, the thermal control subsystem designs thermal control devices such as heat pipes, temperature evaporators, fluid circuits, or phase change energy storage plates based on the temperature control requirements of each subsystem, and proposes layout requirements for the thermal control devices. The mechanical system completes the spacecraft configuration and layout design based on the layout requirements proposed by the thermal control subsystem and other subsystems. The structure and mechanism subsystem then completes the detailed structural design based on the configuration and layout design, combined with mechanical performance requirements. This non-integrated spacecraft structure-thermal control system can meet the requirements of structure, thermal control functions, and performance indicators, but its disadvantage is that it increases contact thermal resistance. Specifically, in existing non-integrated spacecraft structure-thermal control systems, the thermal control device is installed between the spacecraft structure and the equipment. Heat generated by the equipment is first transferred from the individual equipment to the thermal control device, and then from the thermal control device to the spacecraft structure. There is contact thermal resistance between the stand-alone equipment and the thermal control device, and between the thermal control device and the spacecraft structure, that is, there are two contact thermal resistances, which leads to an increase in the temperature difference between the stand-alone equipment and the spacecraft structure, thereby increasing the heat dissipation area requirement of the spacecraft system and increasing the thermal compensation heating power requirement. Summary of the Invention

[0004] The purpose of this application is to provide a structural thermal control integrated load-bearing component in response to at least one technical problem involved in the background technology.

[0005] In order to achieve the above objectives, this application adopts the following technical solutions:

[0006] The present application provides a structural thermal control integrated load-bearing component, including a liquid injection end cover and a main body, wherein one or more thermal control working fluid channels with a length direction in a first direction are formed in the main body, and a side port of each thermal control working fluid channel is sealed in the first direction, and the other side port of each thermal control working fluid channel is sealed with the liquid injection end cover so that thermal control working fluid can be added to each thermal control working fluid channel through the liquid injection end cover. The main body has a mounting surface, the first direction is parallel to the mounting surface, and the distribution direction of each thermal control working fluid channel is parallel to the mounting surface, and the distribution direction of each thermal control working fluid channel is a second direction.

[0007] Optionally, the thermal control working medium channel includes a main channel portion and a plurality of capillaries, the cross-section of the main channel portion is circular, and the capillaries are evenly distributed around the circumference of the main channel portion. The thermal control working medium channel also includes a plurality of connecting slits connected to the main channel portion, and each connecting slit is connected to each capillary tube in a one-to-one correspondence.

[0008] The beneficial effect of this technical solution is that the capillary tube provides a driving force for the flow of the liquid thermal control medium, allowing the liquid thermal control medium to flow within the channel, thereby enhancing the heat transfer capacity of the structural thermal control integrated load-bearing component. Optionally, the liquid injection end cover includes a cover plate portion and a liquid injection tube fixed to the cover plate portion, with a liquid injection hole formed on the cover plate portion. The length of the liquid injection tube is parallel to the first direction, and the cover plate portion is sealed to each of the thermal control medium channels;

[0009] The injection end cover includes a plurality of injection tubes, and a plurality of injection holes are formed on the cover plate portion, each of the injection holes is arranged in the second direction, and each of the injection holes is connected to each of the thermal control medium channels, and each of the injection tubes is installed in a one-to-one correspondence with each of the injection holes; or,

[0010] The injection end cover includes an injection tube. A injection hole is formed on the cover plate portion. The injection hole is communicated with the thermal control medium channel. The injection tube is installed in the injection hole.

[0011] The beneficial effect of this technical solution is that, when multiple thermal control working fluid grooves are provided, multiple injection pipes and multiple injection holes are provided, the thermal control working fluid can be respectively added to each thermal control working fluid groove through each injection pipe; when only one thermal control working fluid groove is provided, the thermal control working fluid can be added to the thermal control working fluid groove through one injection pipe and one injection hole.

[0012] Optionally, the structural thermal control integrated load-bearing component provided in the present application further includes a protective cap provided at the port of the liquid injection tube, and the protective cap is used to prevent the port of the liquid injection tube from directly colliding with the outside world.

[0013] The beneficial effect of this technical solution is that after the thermal control medium is filled into the thermal control medium channel through the injection pipe, the injection pipe is protected by a protective cap to prevent the injection pipe from being damaged and causing the thermal control medium to flow out of the injection pipe.

[0014] Optionally, the structural thermal control integrated load-bearing component provided in the present application further includes a reinforcing plate frame portion, wherein the reinforcing plate frame portion includes a base plate, and a plurality of longitudinal ribs and a plurality of transverse ribs all vertically fixed to the base plate, the base plate is arranged parallel to the mounting surface, and one side surface of the main body is fixedly connected to the base plate in the second direction, the transverse ribs extend in the second direction, the transverse ribs are fixedly connected to the main body, the longitudinal ribs extend in the first direction, and the ends of the transverse ribs away from the main body are fixedly connected to the longitudinal ribs.

[0015] The beneficial effect of this technical solution is that: by setting up a reinforced plate frame part, the strength of the structural thermal control integrated load-bearing member is further improved, and by connecting the main body and the bottom plate, the structural thermal control integrated load-bearing member is unfolded in a plate shape as a whole, thereby adapting to specific working conditions. Through the longitudinal reinforcement and multiple transverse reinforcements, the strength of the structural thermal control integrated load-bearing member is improved from multiple directions, so that the structural thermal control integrated load-bearing member has higher reliability.

[0016] Optionally, the structural thermal control integrated load-bearing component provided in the present application includes two reinforcing plate frame portions, and the two reinforcing plate frame portions are respectively located on opposite sides of the main body in the second direction.

[0017] The beneficial effect of this technical solution is that by setting two reinforced plate frame parts, the area that the structural thermal control integrated load-bearing component can cover as a plate-like structure as a whole is increased, thereby improving the ability of the structural thermal control integrated load-bearing component to reinforce the equipment structure, and further improving the strength and reliability of the structural thermal control integrated load-bearing component.

[0018] Optionally, the structural thermal control integrated load-bearing component provided in the present application further includes a honeycomb core, a mounting groove is provided on the honeycomb core, the main body is provided in the mounting groove, and the main body and the honeycomb core are bonded by structural adhesive.

[0019] The beneficial effect of this technical solution is that the main body and the honeycomb core together form a honeycomb-shaped load-bearing structure, so that the structural thermal control integrated load-bearing parts have strong load-bearing capacity and good thermal control performance. In addition, the advantage of the honeycomb sandwich structure is that the surface-to-mass ratio is high, the mass for the same area is lighter, and the launch cost is saved.

[0020] Optionally, the structural thermal control integrated load-bearing component provided in the present application further includes an upper skin and a lower skin, the honeycomb core is plate-shaped, the mounting groove passes through the honeycomb core in a direction perpendicular to the honeycomb core, the upper skin covers the top surface of the honeycomb core and the mounting surface, and the lower skin covers the bottom surface of the honeycomb core and the plate surface of the main body set away from the mounting surface.

[0021] The beneficial effect of this technical solution is that: in this way, the structural thermal control integrated load-bearing member forms a honeycomb sandwich structure as a whole, which has good load-bearing capacity and thermal control capabilities, and is more suitable for the installation of equipment with a plate-shaped bottom surface.

[0022] Optionally, the structural thermal control integrated load-bearing component provided in the present application further includes a bracket fixedly connected to the main body, the main body is located above the bracket, the mounting surface is a plane on the main body that is away from the bracket, a weight-reducing groove is formed on the bracket, and the liquid injection end cover and the weight-reducing groove are located on the same side of the main body in the first direction.

[0023] Optionally, in the first direction, the mounting surface gradually slopes downward from one end close to the liquid injection end cover to the other end of the mounting surface.

[0024] The beneficial effect of this technical solution is that the inclination of the mounting surface can adapt to the equipment of the corresponding structure, thereby meeting the installation angle requirements of the structure or equipment.

[0025] The technical solution provided by this application can achieve at least one of the following beneficial effects:

[0026] The structural thermal control integrated load-bearing member provided in the present application, as the spacecraft structure itself or a part of the spacecraft structure, is used to install equipment. The heat generated by the equipment is directly transferred to the structural thermal control integrated load-bearing member, without the need to set up a separate thermal control device between the spacecraft structure and the equipment. As a result, there is only one contact thermal resistance between the equipment and the spacecraft structure, making it difficult to increase the temperature difference between a single device and the spacecraft structure, thereby reducing the heat dissipation area requirement of the spacecraft system and reducing the thermal compensation heating power requirement.

[0027] The additional technical features and advantages of this application will be more clearly explained in the following description, or can be understood through the specific practice of this application. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] To more clearly illustrate the technical solutions of the specific embodiments of this application, the following briefly introduces the drawings required for describing the specific embodiments. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be derived from these drawings without inventive effort.

[0029] Figure 1 A schematic diagram of the three-dimensional structure of an embodiment of a structural thermal control integrated load-bearing member provided in an embodiment of the present application;

[0030] Figure 2 A schematic diagram of the exploded structure of an embodiment of the structural thermal control integrated load-bearing member provided in an embodiment of the present application;

[0031] Figure 3 A schematic diagram of the three-dimensional structure of another embodiment of the structural thermal control integrated load-bearing member provided in an embodiment of the present application;

[0032] Figure 4 A schematic diagram of an exploded structure of another embodiment of the structural thermal control integrated load-bearing member provided in an embodiment of the present application;

[0033] Figure 5 A schematic diagram of a partially exploded structure of another embodiment of the structural thermal control integrated load-bearing member provided in an embodiment of the present application;

[0034] Figure 6 A schematic diagram of the three-dimensional structure of a third embodiment of the structural thermal control integrated load-bearing member provided in an embodiment of the present application;

[0035] Figure 7 This is a schematic diagram of the exploded structure of the third embodiment of the structural thermal control integrated load-bearing member provided in the embodiments of the present application;

[0036] Figure 8 A partial three-dimensional structural diagram of an implementation scheme of the main body provided in an embodiment of the present application.

[0037] Reference numerals:

[0038] 01. Liquid injection end cap; 02. Main body;

[0039] 03. Transverse reinforcement; 04. Longitudinal reinforcement;

[0040] 05. Bottom plate; 06. Sealing end cover;

[0041] 07. Thermal control medium channel; 08. Liquid injection pipe;

[0042] 09. Cover plate; 10. Liquid injection hole;

[0043] 11. Mounting hole; 12. Upper skin;

[0044] 13. Honeycomb core; 14. Lower skin;

[0045] 16. Embedded parts; 17. Mounting slot;

[0046] 18. Mounting surface; 19. Bracket;

[0047] 20. Weight reduction groove; 21. Capillary tube;

[0048] 22. Main channel; 23. Connecting seam. DETAILED DESCRIPTION

[0049] The following will clearly and completely describe the technical solution of this application in conjunction with the accompanying drawings. Obviously, the embodiments described are only part of the embodiments of this application, not all of them. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making any creative efforts are within the scope of protection of this application.

[0050] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate the description of this application and simplify the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on this application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0051] In the description of this application, it should be noted that, unless otherwise expressly specified or limited, the terms "mounted," "connected," and "connected" should be understood in a broad sense. For example, they can refer to fixed connections, detachable connections, or integral connections; mechanical connections or electrical connections; direct connections or indirect connections through an intermediate medium; and internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in this application based on the specific circumstances.

[0052] The embodiments of the present invention will be described in detail below with reference to specific examples.

[0053] Example 1

[0054] like Figures 1 to 2 As shown, the present application provides a structural thermal control integrated load-bearing member, including a liquid injection end cover 01 and a main body 02, and one or more thermal control working fluid channels 07 with a length direction in a first direction are formed in the main body 02, and a side port of each thermal control working fluid channel 07 is sealed in the first direction, and the other side port of each thermal control working fluid channel 07 is sealed and connected to the liquid injection end cover 01, so as to add thermal control working fluid into each thermal control working fluid channel 07 through the liquid injection end cover 01, and the main body 02 has a mounting surface 18, the first direction is parallel to the mounting surface 18, and the distribution direction of each thermal control working fluid channel 07 is parallel to the mounting surface 18, and the distribution direction of each thermal control working fluid channel 07 is a second direction.

[0055] In the embodiment of the present application, the number of the thermal control medium channels 07 is preferably 1 to 10, for example, it can be 4, 5, 6, 7, 8 or 9, preferably 8. In the embodiment of the present application, preferably, the main body of the structural thermal control integrated bearing member is manufactured by casting, 3D printing or milling with a shallow depth. At this time, the thermal control medium channel 07 is directly manufactured to be sealed away from the port of the injection end cover. Of course, the sealing end cover 06 can also be used to seal the thermal control medium channel 07, and the sealing end cover 06 and the injection end cover 01 are welded and sealed with the main body 02; the mechanical loads borne by the structural thermal control integrated bearing member include: at least one of static load, periodic vibration load, transient vibration load, impact load and random vibration load; a mounting hole 11 for connecting to the equipment and to the adjacent structure is provided on the main body 02.

[0056] The structural thermal control integrated load-bearing member provided in the present application, as the spacecraft structure itself or a part of the spacecraft structure, is used to install equipment. The heat generated by the equipment is directly transferred to the structural thermal control integrated load-bearing member, without the need to set up a separate thermal control device between the spacecraft structure and the equipment. As a result, there is only one contact thermal resistance between the equipment and the spacecraft structure, making it difficult to increase the temperature difference between a single device and the spacecraft structure, thereby reducing the heat dissipation area requirement of the spacecraft system and reducing the thermal compensation heating power requirement.

[0057] Alternatively, as Figure 8 As shown, the thermal control medium channel 07 includes a main channel portion 22 and a plurality of capillaries 21. The cross section of the main channel portion 22 is circular, and the capillaries 21 are evenly distributed around the circumference of the main channel portion 22. The thermal control medium channel 07 also includes a plurality of connecting slits 23 that are connected to the main channel portion 22, and each connecting slit 23 is connected to each capillary 21 in a one-to-one correspondence. The capillary 21 provides a driving force for the flow of the liquid thermal control medium, so that the liquid thermal control medium can flow in the thermal control medium channel 07, thereby enhancing the heat transfer capacity of the structural thermal control integrated load-bearing member. In the embodiment of the present application, the capillary 21 refers to a tube that can produce an obvious capillary phenomenon. The capillary phenomenon refers to the phenomenon that the liquid on the inside of a thin tubular object overcomes gravity and rises or falls due to the difference between cohesion and adhesion. In the embodiment of the present application, the number of the capillaries 21 can be 10 to 20, for example, 12, 14, 16 or 18, and preferably 14.

[0058] Optionally, the injection end cover 01 includes a cover portion 09 and an injection tube 08 fixed to the cover portion 09, an injection hole 10 is formed on the cover portion 09, the length direction of the injection tube 08 is parallel to the first direction, and the cover portion 09 is sealed and connected to each of the thermal control medium channels 07;

[0059] The injection end cover 01 includes a plurality of injection pipes 08. A plurality of injection holes 10 are formed on the cover plate portion 09. The injection holes 10 are arranged in the second direction and communicate with the thermal control medium channels 07. The injection pipes 08 are installed in a one-to-one correspondence with the injection holes 10.

[0060] or,

[0061] The injection end cover 01 includes an injection pipe 08 . A injection hole 10 is formed on the cover plate portion 09 . The injection hole 10 is connected to the thermal control medium channel 07 . The injection pipe 08 is installed in the injection hole 10 .

[0062] In this way, when multiple thermal control working fluid grooves 07 are provided, multiple injection pipes 08 and multiple injection holes 10 are provided, thermal control working fluid can be added to each thermal control working fluid groove 07 through each injection pipe 08; when only one thermal control working fluid groove 07 is provided, thermal control working fluid can be added to the thermal control working fluid groove 07 through one injection pipe 08 and one injection hole 10.

[0063] In the embodiment of the present application, each of the injection holes 10 and each of the thermal control medium channels 07 can be connected in a one-to-one correspondence, or each of the thermal control medium channels 07 can be divided into several groups, wherein each of the thermal control medium channels 07 in the group is partially connected, and each of the thermal control medium channels 07 in each group shares a common injection pipe 08, for example, Figure 2 As shown, the eight thermal control medium channels 07 can be divided into four groups, and four injection pipes 08 are provided accordingly. The thermal control medium channels 07 in each group are partially connected, and the thermal control medium channels 07 in the group share one injection pipe 08 .

[0064] Optionally, the structural thermal control integrated load-bearing member provided in the embodiment of the present application further includes a protective cap provided at the port of the injection tube 08, and the protective cap is used to prevent the port of the injection tube 08 from directly colliding with the outside world. After the thermal control working medium is added to the thermal control working medium channel through the injection tube 08, the injection tube 08 is protected by the protective cap to prevent the injection tube 08 from being damaged and causing the thermal control working medium to flow out of the injection tube 08. In the embodiment of the present application, when there are multiple injection tubes 08, the protective cap is mainly provided to protect the port of the injection tube 08 that is at risk of collision. Of course, when there is no risk of structural interference, the protective cap may not be provided.

[0065] Optionally, the structural thermal control integrated load-bearing member provided in the embodiment of the present application further includes a reinforcing plate frame portion, the reinforcing plate frame portion includes a base plate 05, and a plurality of longitudinal ribs 04 and a plurality of transverse ribs 03 all vertically fixed to the base plate 05, the base plate 05 is arranged parallel to the mounting surface 18, and one side surface of the main body 02 is fixedly connected to the base plate 05 in the second direction, the transverse ribs 03 extend in the second direction, the transverse ribs 03 are fixedly connected to the main body 02, the longitudinal ribs 04 extend in the first direction, and the ends of the transverse ribs 03 away from the main body 02 are fixedly connected to the longitudinal ribs 04. In the embodiment of the present application, several refers to one or more. It can be understood that when there are multiple transverse ribs 03, each of the transverse ribs 03 is arranged in the first direction. In this way, the strength of the structural thermal control integrated load-bearing component is further improved by setting up a reinforced plate frame part, and the structural thermal control integrated load-bearing component is connected to the base plate 05 through the main body 02, so that the structural thermal control integrated load-bearing component is unfolded in a plate shape as a whole, thereby adapting to specific working conditions. Through a number of longitudinal ribs 04 and a number of transverse ribs 03, the strength of the structural thermal control integrated load-bearing component is improved from multiple directions, so that the structural thermal control integrated load-bearing component has higher reliability.

[0066] Optionally, the structural thermal control integrated load-bearing member provided in the embodiment of the present application includes two of the reinforcing plate frame parts, and the two reinforcing plate frame parts are respectively located on opposite sides of the main body 02 in the second direction. By providing two reinforcing plate frame parts, the area that the structural thermal control integrated load-bearing member as a whole can cover as a plate-like structure is increased, thereby improving the ability of the structural thermal control integrated load-bearing member to reinforce the equipment structure, and further improving the strength and reliability of the structural thermal control integrated load-bearing member. In the embodiment of the present application, the thickness of the transverse ribs 03 and the longitudinal ribs 04 are preferably 1.5 mm. Preferably, the main body 02 is formed by milling, and the material is magnesium alloy. Different working fluids are added to each adjacent thermal control working fluid groove 07. For example, if ammonia is added to one thermal control working fluid groove 07, then n-hexadecane (paraffin type) is added to the other thermal control working fluid groove 07, and the n-hexadecane (paraffin type) working fluid is preferably a mixed expanded graphite thermal conductive reinforcement material.

[0067] Example 2

[0068] like Figures 3 to 5As shown, the structural thermal control integrated load-bearing member provided in this embodiment is similar to that of Example 1, except that this embodiment further includes a honeycomb core 13, a mounting groove 17 provided on the honeycomb core 13, the main body 02 disposed within the mounting groove 17, and the main body 02 is fixedly connected to the honeycomb core 13. Thus, the main body 02 and the honeycomb core 13 together form a honeycomb-shaped load-bearing structure, giving the structural thermal control integrated load-bearing member both a strong load-bearing capacity and excellent thermal control performance. Furthermore, the honeycomb sandwich structure has the advantage of a high surface-to-mass ratio, resulting in a lighter mass per unit area, thus saving launch costs.

[0069] Optionally, the structural thermal control integrated load-bearing member provided in the embodiment of the present application further includes an upper skin 12 and a lower skin 14, the honeycomb core 13 is plate-shaped, the mounting groove 17 passes through the honeycomb core 13 in a direction perpendicular to the honeycomb core 13, the upper skin 12 covers the top surface of the honeycomb core 13 and the mounting surface 18, and the lower skin 14 covers the bottom surface of the honeycomb core 13 and the plate surface of the main body 02 that is set away from the mounting surface 18. In this way, the structural thermal control integrated load-bearing member forms a honeycomb sandwich structure as a whole (which can be flat or curved), which has good load-bearing capacity and thermal control capabilities, and is more suitable for the installation of equipment with a plate-shaped bottom surface. In the embodiment of the present application, the honeycomb core 13, each skin and the main body 02 are bonded by structural adhesive, and the embedded parts 16 are used to provide mounting holes for installing equipment or assembling structures. In the embodiment of the present application, preferably, mounting holes and mounting surfaces are provided on both the upper and lower surfaces of the main body 02. In the embodiment of the present application, the "upper" and "lower" in the upper skin 12 and lower skin 14 refer to the upper and lower positions during the processing of the sandwich structure, in which the lower skin 14 is first placed on the processing tooling, the honeycomb core is then laid on the lower skin 14, the honeycomb core is opened with holes to place embedded parts, and then the skin 12 is covered. This is the upper and lower position relationship during the processing. Preferably, the main body 02 has a wall thickness of 1mm and a 1mm thick reinforcement structure is provided inside. The main body 02 is formed by milling, and the main body 02 is made of aluminum alloy. Of course, the mounting groove 17 can also be a non-through groove, that is, there is a thinned honeycomb core 13 below the mounting groove 17. This form can be used when heat transfer from one side of the upper skin 12 or the lower skin 14 to the other side is not required. In this way, the honeycomb core 13 is lighter.

[0070] Example 3

[0071] like Figures 6 and 7As shown, the structural thermal control integrated load-bearing member provided in this embodiment refers to Example 1, with the difference being that this embodiment does not use an ordinary sealing end cap 06 to reduce leakage through the sealing end cap 06, that is, to achieve the purpose of reducing leakage rate, increasing service life and reliability. This embodiment also includes a bracket 19 fixedly connected to the main body 02, the main body 02 is located above the bracket 19, the mounting surface 18 is a plane on the main body 02 that is disposed away from the bracket 19, a weight reduction groove 20 is formed on the bracket 19, and the liquid injection end cap 01 and the weight reduction groove 20 are located on the same side of the main body 02 in the first direction. In the embodiment of the present application, preferably, the weight reduction groove 20 passes through the bracket 19. Optionally, in the first direction, the mounting surface 18 gradually tilts downward from one end close to the liquid injection end cap 01 to the other end of the mounting surface 18. The tilting of the mounting surface 18 can adapt to the equipment of the corresponding structure, thereby meeting the installation angle requirements of the structure or equipment. In the embodiment of the present application, the wall thickness of the bracket 19 is preferably 5 mm, the main body 02 is formed by casting, the main body 02 material is aluminum alloy, and polyethylene glycol working fluid is added. The polyethylene glycol working fluid is preferably a mixed foam copper thermal conductive enhanced material.

[0072] Compared with the existing non-integrated spacecraft structure-thermal control system, the structural thermal control integrated load-bearing parts provided in the embodiments of the present application are responsible for providing sealing performance and meeting mechanical requirements at the same time, so only a part of the structural weight exists, which will not lead to an increase in the weight of the spacecraft system.

[0073] Compared with the existing non-integrated spacecraft structure-thermal control system, the structural thermal control integrated load-bearing component provided in the embodiment of the present application, in addition to avoiding the increase in thermal compensation heating power caused by the increase in contact thermal resistance as mentioned above, can utilize the heat storage function of the structural thermal control integrated load-bearing component to reduce the impact of fluctuations in the space thermal environment on the temperature stability of equipment such as star sensors, without increasing the heat dissipation surface of the equipment, and will not lead to an increase in compensation heating power at low temperatures.

[0074] Compared with the existing non-integrated spacecraft structure-thermal control system, the structural thermal control integrated load-bearing parts provided in the embodiments of the present application only need to ensure equipment installation space, and will not cause the envelope size of the spacecraft system to increase.

[0075] The structural thermal control integrated load-bearing component provided in the embodiment of the present application has a main body 02 wall and reinforcing rib thickness of 0.5 mm to 7 mm.

[0076] The structural thermal control integrated load-bearing component provided in the embodiment of the present application has a main body 02 formed by at least one of milling, gluing, riveting, screwing, casting, and additive manufacturing.

[0077] The structural thermal control integrated load-bearing component provided in the embodiment of the present application has a main body 02 made of at least one of aluminum alloy, magnesium alloy, titanium alloy, steel, magnesium-lithium alloy, and aluminum-lithium alloy.

[0078] The structural thermal control integrated load-bearing component provided in the embodiment of the present application has a main body 02 and a liquid injection end cover 01 sealed by welding, one or more thermal control working fluids are added and the liquid injection end cover 01 is sealed to form a sealing structure required for the thermal control function.

[0079] The structural thermal control integrated load-bearing component provided in the embodiment of the present application has a sealing structure designed as a pressure vessel, which can adapt to the pressure difference between the inside and outside of the sealing structure in the ground environment and the on-orbit vacuum environment.

[0080] The structural thermal control integrated load-bearing member provided in the embodiment of the present application, wherein the thermal control working fluid is at least one of helium, hydrogen, neon, nitrogen, oxygen, ammonia, freon, water, mercury, cesium, potassium, sodium, lithium, silver, methane, ethane, pentane, heptane, propylene, acetone, methanol, ethanol, ethylene glycol, ethylene glycol aqueous solution, perfluorotriethylamine, crystalline hydrated salt, molten salt, paraffin, organic acid, organic acid amide, organic ester and organic polymer.

[0081] The structural thermal control integrated load-bearing component provided in the embodiment of the present application is characterized in that the material used in the sealing structure meets the compatibility requirements of the thermal control working medium.

[0082] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some or all of the technical features therein. These modifications or replacements do not deviate the essence of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present application.

Claims

1. Structural thermal control integrated load-bearing component, characterized in that: The invention comprises a liquid injection end cover and a main body, wherein one or more thermal control medium channels are formed in the main body, and the length direction of each thermal control medium channel is in a first direction. A port on one side of each thermal control medium channel is sealed in the first direction, and a port on the other side of each thermal control medium channel is sealed and connected to the liquid injection end cover so that the thermal control medium is injected into each thermal control medium channel through the liquid injection end cover. The main body has a mounting surface, the first direction is parallel to the mounting surface, and the distribution direction of each thermal control medium channel is parallel to the mounting surface, and the distribution direction of each thermal control medium channel is in a second direction. The thermal control medium channel includes a main channel portion and a plurality of capillaries. The cross section of the main channel portion is circular, and the capillaries are evenly distributed around the circumference of the main channel portion. The thermal control medium channel also includes a plurality of communication slits connected to the main channel portion, and each communication slit is connected to each capillary tube in a one-to-one correspondence. The injection end cover includes a cover plate portion and an injection tube fixed to the cover plate portion, wherein an injection hole is formed on the cover plate portion, and the length direction of the injection tube is parallel to the first direction, and the cover plate portion is sealed and connected to each of the thermal control medium channels; The injection end cover includes a plurality of injection tubes, and a plurality of injection holes are formed on the cover plate portion, each of the injection holes is arranged in the second direction, and each of the injection holes is connected to each of the thermal control medium channels, and each of the injection tubes is installed in a one-to-one correspondence with each of the injection holes; or, The injection end cover includes an injection tube. A injection hole is formed on the cover plate portion. The injection hole is communicated with the thermal control medium channel. The injection tube is installed in the injection hole.

2. The structural thermal control integrated bearing member according to claim 1, characterized in that: It also includes a protective cap arranged on the port of the liquid injection tube, and the protective cap is used to prevent the port of the liquid injection tube from directly colliding with the outside world.

3. The structural thermal control integrated bearing member according to claim 1 or 2, characterized in that: It also includes a reinforcing plate frame portion, which includes a bottom plate, and longitudinal and transverse ribs that are vertically fixed to the bottom plate. The bottom plate is arranged parallel to the mounting surface, and one side surface of the main body is fixedly connected to the bottom plate in the second direction. The transverse ribs extend in the second direction, and the transverse ribs are fixedly connected to the main body. The longitudinal ribs extend in the first direction, and the ends of the transverse ribs away from the main body are fixedly connected to the longitudinal ribs.

4. The structural thermal control integrated bearing member according to claim 3, characterized in that: The two reinforcing plate frame parts are included, and the two reinforcing plate frame parts are respectively located on two opposite sides of the main body in the second direction.

5. The structural thermal control integrated bearing member according to claim 1 or 2, characterized in that: It also includes a honeycomb core, a mounting groove is provided on the honeycomb core, the main body is provided in the mounting groove, and the main body is fixedly connected to the honeycomb core.

6. The structural thermal control integrated bearing member according to claim 5, characterized in that: It also includes an upper skin and a lower skin. The honeycomb core is plate-shaped. The mounting groove passes through the honeycomb core in a direction perpendicular to the honeycomb core. The upper skin covers the top surface of the honeycomb core and the mounting surface. The lower skin covers the bottom surface of the honeycomb core and the plate surface of the main body that is set away from the mounting surface.

7. The structural thermal control integrated bearing member according to claim 1 or 2, characterized in that: It also includes a bracket fixedly connected to the main body, the main body is located above the bracket, the mounting surface is a plane on the main body that is set away from the bracket, a weight-reducing groove is formed on the bracket, and in the first direction, the liquid injection end cover and the weight-reducing groove are located on the same side of the main body.

8. The structural thermal control integrated bearing member according to claim 7, characterized in that: In the first direction, the mounting surface gradually slopes downward from one end close to the liquid injection end cover to the other end of the mounting surface.

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