Heat dissipation device based on integrated casting molding satellite
By pasting Class I and Class II heat pipes on the satellite cabin, forming an intersecting network, the problem of heat cannot be transferred in time due to reinforcement ribs is solved, and the isothermalization and high reliability of the satellite cabin are achieved.
Patent Information
- Application Number
- CN202510607040.0
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-05-12
- Publication Date
- 2025-08-08
AI Technical Summary
In the prior art, due to the existence of reinforcement ribs, the integrated cast-formed satellite cabin plate cannot be pre-buried and attached at the same time, and cannot form an effective heat pipe network and cannot effectively dissipate heat.
The heat of a typical single-type equipment and a second-type heat pipe are applied to the satellite cabin through a first-type heat pipe and a second-type heat pipe, and a heat pipe network is formed by crossing it. The reinforcement ribs are used as connection points to solve the problem of limited installation space of the heat pipe.
It realizes isothermalization of satellite cabins, ensures timely heat transfer, the heat pipe network is highly reliable and has no moving parts, avoids system startup and failure, and adapts to different external heat flow conditions.
Smart Images
Figure CN120440316A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to the technical field of spacecraft thermal control, and more particularly to a heat dissipation device based on an integrated casting satellite. Background Art
[0002] New satellite structures not only demand extreme lightweighting, high performance, and functionality, but also require rapid customization of complex structural designs and improved development efficiency. Lightweight, high-performance, and integrated structural and functional design and manufacturing have become an inevitable choice for satellite development. One solution is to use integrated casting for the satellite's main structure, which facilitates mass production, shortens development cycles, and improves constellation networking efficiency.
[0003] Unlike traditional honeycomb panel structures in spacecraft, the cabin panel uses integrated casting technology, which makes it impossible to pre-embed heat pipes inside. A common method for arranging heat pipes is external mounting. There are often a large number of individual units on the inside of the cabin panel. Since heat pipes can only be attached to the outside of the cabin panel, it is impossible to form a heat pipe network by combining pre-embedding and external mounting. In addition, since the thickness of the satellite cabin panel is only 1-2mm, a large number of reinforcing ribs are required to ensure structural strength, and the reinforcing ribs are particularly concentrated near the individual units. The presence of the reinforcing ribs prevents the individual unit and the other side of the cabin panel from being attached to the cabin panel at the same time. The original heat transfer path from the individual unit to the cabin panel and then to the heat pipe is interrupted, making it impossible to dissipate the heat generated by the individual unit.
[0004] Under such conditions, a reasonable heat pipe network layout is needed to effectively solve the problem of satellite heat dissipation.
[0005] Integrated cast satellite cabin panels are a new generation of structural configuration, but the existing technology does not have heat pipe layout methods and heat dissipation devices; common heat pipe layout methods are not suitable for integrated cast satellite cabin panels, and cannot form an effective heat pipe network, and cannot solve the heat dissipation problem of high-power single machines.
[0006] The preceding description is intended to provide general background information and does not necessarily constitute prior art. Summary of the Invention
[0007] The purpose of the present invention is to provide a heat dissipation device based on an integrated cast satellite. The heat dissipation device based on an integrated cast satellite solves the heat dissipation problem of a single-machine device of an integrated cast satellite, and at the same time adapts to the needs under different external heat flow conditions. It has the characteristics of high adaptability, good reliability, and flexible design, and can be expanded to be used in satellites of the same type.
[0008] The present invention provides a heat dissipation device based on an integrated cast satellite, comprising a satellite cabin panel, a typical Class I stand-alone device, a typical Class II stand-alone device, a Class I heat pipe, and a Class II heat pipe; the typical Class I stand-alone device is installed on the inner side of the satellite cabin panel, and the typical Class II stand-alone device is installed on the outer side of the satellite cabin panel; the Class I heat pipe and the Class II heat pipe are attached to the outside of the satellite cabin panel; one end of the Class II heat pipe is connected to the fins on both sides of the typical Class II stand-alone device, and the Class I heat pipe is connected to the typical Class I stand-alone device.
[0009] Furthermore, the satellite cabin panel is an integrally formed structure, and the thickness of the satellite cabin panel is 1-2 mm.
[0010] Furthermore, a plurality of reinforcing ribs are connected to the surface of the satellite cabin panel, and the second type of heat pipes and the first type of heat pipes are both connected to the reinforcing ribs.
[0011] Furthermore, the typical type A stand-alone device includes a first stand-alone device, a second stand-alone device and a third stand-alone device. There are three grooves on the satellite cabin panel, and the first stand-alone device, the second stand-alone device and the third stand-alone device are connected in the grooves accordingly; a cavity is provided on the top of the first stand-alone device, the second stand-alone device and the third stand-alone device, and the type A heat pipe is connected in the cavity, and the cavity is filled where the heat pipe passes.
[0012] Furthermore, the connections between the first-class heat pipe, the second-class heat pipe and the satellite cabin panel are all filled with thermal grease; the connections between the second-class heat pipe and the fins on both sides of the typical second-class stand-alone equipment are all filled with thermal grease.
[0013] Furthermore, the second type of heat pipe has gaps formed at the fins near both sides of the typical second type stand-alone equipment, and the height of the gap is less than the thickness of the first type of heat pipe; when the first type of heat pipe passes through the gap, the second type of heat pipe is tightly pressed against the first type of heat pipe.
[0014] Furthermore, the crimping joints of the second type of heat pipe and the first type of heat pipe are connected by screws and filled with thermal grease.
[0015] Furthermore, the connection between the typical type 1 stand-alone device and the typical type 2 stand-alone device and the satellite cabin panel is filled with thermal grease.
[0016] Furthermore, the typical heat consumption of the first single machine, the second single machine and the third single machine are 50W, 200W and 50W respectively, the second single machine is a high-power single machine, the typical Class II single machine device is a high-power single machine, and the heat consumption of the typical Class II single machine device is 220W.
[0017] Furthermore, the outer surface of the satellite cabin panel, the typical Class II stand-alone equipment, the Class I heat pipe and the Class II heat pipe are sprayed with white paint, and the inner surface of the satellite cabin panel and the typical Class I stand-alone equipment are sprayed with high-emissivity black paint or subjected to black anodizing treatment.
[0018] The heat dissipation device based on the integrated cast satellite provided by the present invention can timely transfer the heat generated by typical Class I single-machine equipment and typical Class II single-machine equipment to the satellite cabin plate via Class I heat pipes and Class II heat pipes. The Class I heat pipes and Class II heat pipes cross each other to effectively form a heat pipe network to isotherm the satellite cabin plate; the heat generated by the single-machine equipment inside and outside the integrated cast satellite is transferred to the heat pipes, and the heat pipes are all installed on the outside of the cabin plate to solve the problem of limited space for heat pipe installation; make full use of the existing single-machine layout, and install the heat pipes in a "layered" manner on the outside to achieve the purpose of combining traditional honeycomb panels with external attachment and pre-embedding to form a heat pipe network; solve the problem that the single-machine heat conduction installation on the integrated cast satellite cabin plate cannot transfer heat to the other side of the external attachment in time due to the presence of reinforcement ribs; the structure of the present invention has high reliability, the entire set of device products has no moving parts, and all are passive thermal control measures, and there are no system startup, termination and failure problems. BRIEF DESCRIPTION OF THE DRAWINGS
[0019] Figure 1 A schematic structural diagram of a heat dissipation device based on an integrated casting satellite provided in an embodiment of the present invention.
[0020] Figure 2 for Figure 1 Enlarged view of part A in .
[0021] Figure 3 for Figure 1 A schematic diagram of the structure of a typical type of stand-alone equipment for heat dissipation devices based on integrated casting satellites.
[0022] Figure 4 The temperature variation curve of the second single unit and typical second type single unit equipment over time.
[0023] The reference numerals and components in the drawings are as follows:
[0024] 100, satellite cabin board 200, typical type 1 stand-alone equipment 210, first stand-alone
[0025] 220, second unit 230, third unit 240, cavity
[0026] 400, Class I heat pipe 300, Typical Class II stand-alone equipment 410, Top Class I heat pipe
[0027] 420, middle type 1 heat pipe 430, lower type 1 heat pipe 500, type 2 heat pipe
[0028] 510, upper end type 2 heat pipe 520, lower end type 2 heat pipe DETAILED DESCRIPTION
[0029] The following embodiments of the present invention are described in further detail with reference to the accompanying drawings and examples. The following examples are used to illustrate the present invention but are not intended to limit the scope of the present invention.
[0030] The terms "first", "second", "third", "fourth", etc. in the description and claims of the present invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence.
[0031] Example 1
[0032] Figure 1 This is a schematic diagram of the structure of a heat dissipation device based on an integrated casting satellite provided by an embodiment of the present invention. Figure 1 The heat dissipation device based on an integrated casting satellite provided by an embodiment of the present invention comprises a satellite cabin panel 100, a typical first-class stand-alone device (200), a typical second-class stand-alone device (300), a first-class heat pipe 400 and a second-class heat pipe 500; the typical first-class stand-alone device 200 is installed on the inner side of the satellite cabin panel 100, and the typical second-class stand-alone device 300 is installed on the outer side of the satellite cabin panel 100; the first-class heat pipe 400 and the second-class heat pipe 500 are attached to the outside of the satellite cabin panel 100; one end of the second-class heat pipe 500 is connected to the fins on both sides of the typical second-class stand-alone device 300, and the first-class heat pipe 400 is connected to the typical first-class stand-alone device (200).
[0033] Specifically, the typical type I stand-alone device 200 is connected to the middle of the satellite cabin board 100, and the typical type II stand-alone device 300 is connected to one side edge of the satellite cabin board 100; the type II heat pipe 500 includes an upper type II heat pipe 510 and a lower type II heat pipe 520, and one end of the upper type II heat pipe 510 and the lower type II heat pipe 520 are respectively connected to the fins on both sides of the typical type II stand-alone device 300, and the typical type I stand-alone device 200 is located between the upper type II heat pipe 510 and the lower type II heat pipe 520; the type I heat pipe 400 includes an upper type I heat pipe 410, a middle type I heat pipe 420 and a lower type I heat pipe 430, and the upper type I heat pipe 410 and One end of the middle Class A heat pipe 420 passes through the bottom of the upper Class B heat pipe 510 and is connected to the side of one end of the upper Class B heat pipe 510; the lower Class A heat pipe 430 is U-shaped, and one side of the lower Class A heat pipe 430 is connected to the typical Class A stand-alone device 200, the bottom edge of the lower Class A heat pipe 430 passes through the lower Class B heat pipe 520, and the other side of the lower Class A heat pipe 430 is located at the edge of the satellite cabin panel 100; the surfaces of the upper Class B heat pipe 510, the lower Class B heat pipe 520, the upper Class A heat pipe 410, the middle Class A heat pipe 420 and the lower Class A heat pipe 430 are all connected to the satellite cabin panel 100.
[0034] Specifically, the satellite cabin panel 100 is an integrally formed structure, and the thickness of the satellite cabin panel 100 is 1-2 mm;
[0035] The heat dissipation device based on an integrated casting satellite provided by the present invention can promptly transfer the heat generated by a typical Class I stand-alone device 200 and a typical Class II stand-alone device 300 to the satellite cabin panel 100 via a Class I heat pipe 400 and a Class II heat pipe 500. The Class I heat pipe 400 and the Class II heat pipe 500 intersect with each other to effectively form a heat pipe network to isothermally maintain the satellite cabin panel 100.
[0036] It should be noted that the heat generated by the single-machine equipment inside and outside the integrated cast satellite is transferred to the heat pipes, and the heat pipes are all installed on the outside of the cabin plate to solve the problem of limited space for heat pipe installation; make full use of the existing single-machine layout, and install the heat pipes in a "layered" manner on the outside to achieve the purpose of combining the external attachment and pre-embedding of traditional honeycomb panels to form a heat pipe network; solve the problem of the single-machine heat conduction installation on the cabin plate of the integrated cast satellite due to the presence of reinforcement ribs. The reliability of the structure of the present invention is high, the whole set of equipment products has no moving parts, and all are passive thermal control measures, and there are no problems with system startup, termination and failure.
[0037] Further references Figure 1In the present invention, a plurality of reinforcing ribs are connected to the surface of the satellite cabin panel 100, and the second type heat pipe 500 and the first type heat pipe 400 are both connected to the reinforcing ribs;
[0038] Specifically, the surface of the satellite cabin panel 100 is connected to a plurality of reinforcing ribs, and the surfaces of the upper second-type heat pipe 510, the lower second-type heat pipe 520, the upper first-type heat pipe 410, the middle first-type heat pipe 420 and the lower first-type heat pipe 430 are all connected to the reinforcing ribs.
[0039] Figure 2 for Figure 1 The enlarged view of part A in Figure 3 for Figure 1 The schematic diagram of the structure of a typical single-unit device based on the heat dissipation device of the integrated casting satellite. Figure 1 、 Figure 2 、 Figure 3 A typical first-class stand-alone device 200 of the present invention includes a first stand-alone device 210, a second stand-alone device 220, and a third stand-alone device 230. There are three grooves on the satellite cabin panel 100, and the first stand-alone device 210, the second stand-alone device 220, and the third stand-alone device 230 are connected to the grooves respectively; a cavity 240 is provided on the top of the first stand-alone device 210, the second stand-alone device 220, and the third stand-alone device 230, and the first-class heat pipe 400 is connected to the cavity 240, and the cavity 240 is filled where the heat pipe passes, ensuring that the heat of the stand-alone device is transferred to the heat pipe in a timely manner.
[0040] Specifically, the lower end of the heat pipe 430 is connected to the cavity 240 and fills the cavity 240.
[0041] Further references Figure 1 The connections between the first type heat pipe 400 of the present invention, the second type heat pipe 500 and the satellite cabin panel 100 are filled with thermal grease; the connections between the second type heat pipe 500 and the fins on both sides of the typical second type stand-alone device 300 are filled with thermal grease;
[0042] Specifically, the connections between the upper Class II heat pipe 510, the lower Class II heat pipe 520, the upper Class I heat pipe 410, the middle Class I heat pipe 420 and the lower Class I heat pipe 430 and the satellite cabin panel 100 are all filled with thermal grease; the connections between the upper Class II heat pipe 510 and the lower Class II heat pipe 520 and the fins on both sides of the typical Class II stand-alone device 300 are all filled with thermal grease; the connection between the lower Class I heat pipe 430 and the typical Class I stand-alone device 200 is filled with thermal grease.
[0043] Further references Figure 1The second type heat pipe 500 of the present invention has gaps formed at the fins on both sides of the typical second type stand-alone device 300. The height of the gaps is less than the thickness of the first type heat pipe 400. When the first type heat pipe 400 passes through the gaps, the second type heat pipe 500 is pressed tightly against the first type heat pipe 400.
[0044] Specifically, the upper second-class heat pipe 510 and the lower second-class heat pipe 520 are formed with gaps at the fins near both sides of the typical second-class stand-alone equipment 300, and the height of the gap is less than the thickness of the upper first-class heat pipe 410, the middle first-class heat pipe 420 and the lower first-class heat pipe 430; when the upper first-class heat pipe 410, the middle first-class heat pipe 420 and the lower first-class heat pipe 430 pass through the gap, the upper second-class heat pipe 510 is pressed tightly against the upper first-class heat pipe 410 and the middle first-class heat pipe 420, and the lower second-class heat pipe 520 is pressed tightly against the lower first-class heat pipe 430.
[0045] Furthermore, the crimping joints of the Class II heat pipe 500 and the Class I heat pipe 400 are connected by screws and filled with thermal grease; specifically, the crimping joints of the upper Class II heat pipe 510 and the upper Class I heat pipe 410 and the middle Class I heat pipe 420 are connected by screws and filled with thermal grease; the crimping joints of the lower Class II heat pipe 520 and the lower Class I heat pipe 430 are connected by screws and filled with thermal grease.
[0046] Furthermore, the connection between the typical type 1 stand-alone device 200 and the typical type 2 stand-alone device 300 of the present invention and the satellite cabin panel 100 is filled with thermal grease, thereby ensuring that heat is transferred to the satellite cabin panel 100 in a timely manner.
[0047] Further references Figure 1 The typical heat consumption of the first single machine 210, the second single machine 220 and the third single machine 230 of the present invention are 50W, 200W and 50W respectively. The second single machine 220 is a high-power single machine. The typical second-class single machine device 300 is a high-power single machine. The heat consumption of the typical second-class single machine device 300 is 220W.
[0048] It should be noted that there are other high-power consumption units on the satellite, all of which use the device of the present invention for heat dissipation, and they will not be described one by one here.
[0049] Further references Figure 1 In the present invention, the outer surface of the satellite cabin panel 100, the typical Class I stand-alone device 200, the typical Class II stand-alone device 300, the Class I heat pipe 400 and the Class II heat pipe 500 are all sprayed with white paint, and the inner surface of the satellite cabin panel 100 and the surface of the typical Class I stand-alone device 200 are sprayed with high-emissivity black paint or subjected to black anodizing treatment.
[0050] It should be noted that the white paint is a high-performance white paint that adapts to complex external heat flow environments, such as KS-1 paint, KS-ZA paint, etc. The inside of the cabin panel and the cabin are sprayed with high-emissivity black paint, such as E51-M, ACR-2, etc.
[0051] Figure 4 This is a graph showing the temperature variation over time for the second stand-alone device and a typical second-class stand-alone device. Figure 4 , the present invention can control the temperature of the second stand-alone device 220 at 36.4-39.1°C under extremely high temperature conditions, and the temperature of the typical second-class stand-alone device 300 (stand-alone device) can be controlled at 28.1-32.5°C. Figure 4 The middle is the temperature change curve with time.
[0052] Based on the above description, it can be seen that the advantages of the present invention are:
[0053] The heat dissipation device based on the integrated cast satellite provided by the present invention can timely transfer the heat generated by typical Class I single-machine equipment and typical Class II single-machine equipment to the satellite cabin plate via Class I heat pipes and Class II heat pipes. The Class I heat pipes and Class II heat pipes cross each other to effectively form a heat pipe network to isotherm the satellite cabin plate; the heat generated by the single-machine equipment inside and outside the integrated cast satellite is transferred to the heat pipes, and the heat pipes are all installed on the outside of the cabin plate to solve the problem of limited space for heat pipe installation; make full use of the existing single-machine layout, and install the heat pipes in a "layered" manner on the outside to achieve the purpose of combining traditional honeycomb panels with external attachment and pre-embedding to form a heat pipe network; solve the problem that the single-machine heat conduction installation on the integrated cast satellite cabin plate cannot transfer heat to the other side of the external attachment in time due to the presence of reinforcement ribs; the structure of the present invention has high reliability, the entire set of device products has no moving parts, and all are passive thermal control measures, and there are no system startup, termination and failure problems.
[0054] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any modifications or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in the present invention should be included in the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be based on the scope of protection of the claims.
Claims
1. A heat dissipation device based on an integrated casting satellite, characterized in that: It includes a satellite cabin panel (100), a typical first-class stand-alone device (200), a typical second-class stand-alone device (300), a first-class heat pipe (400), and a second-class heat pipe (500); The typical first-class stand-alone device (200) is installed on the inner side of the satellite cabin panel (100), and the typical second-class stand-alone device (300) is installed on the outer side of the satellite cabin panel (100); The first-class heat pipe (400) and the second-class heat pipe (500) are externally attached to the satellite cabin panel (100); one end of the second-class heat pipe (500) is connected to the fins on both sides of the typical second-class stand-alone device (300), and the first-class heat pipe (400) is connected to the typical first-class stand-alone device (200).
2. The heat dissipation device based on the integrated casting satellite according to claim 1 is characterized in that: The satellite cabin panel (100) is an integrally formed structure, and the thickness of the satellite cabin panel (100) is 1-2 mm.
3. The heat dissipation device based on the integrated casting satellite according to claim 1 is characterized in that: A plurality of reinforcing ribs are connected to the surface of the satellite cabin panel (100), and the second type of heat pipe (500) and the first type of heat pipe (400) are both connected to the reinforcing ribs.
4. The heat dissipation device based on an integrated casting satellite according to claim 1, characterized in that: The typical first-class stand-alone device (200) includes a first stand-alone device (210), a second stand-alone device (220), and a third stand-alone device (230). Three grooves are provided on the satellite cabin panel (100), and the first stand-alone device (210), the second stand-alone device (220), and the third stand-alone device (230) are connected to the grooves respectively. A concave cavity (240) is provided on each of the first unit (210), the second unit (220) and the third unit (230); the first type of heat pipe (400) is connected to the concave cavity (240), and the concave cavity (240) is filled where the heat pipe passes.
5. The heat dissipation device based on an integrated casting satellite according to claim 1, characterized in that: The connection points between the first type heat pipe (400), the second type heat pipe (500) and the satellite cabin panel (100) are all filled with thermal grease; The connection points between the second-class heat pipe (500) and the fins on both sides of the typical second-class stand-alone device (300) are filled with thermal grease.
6. The heat dissipation device based on an integrated casting satellite according to claim 1, characterized in that: The second-class heat pipe (500) is formed with gaps at the fins near both sides of the typical second-class stand-alone device (300), and the height of the gaps is less than the thickness of the first-class heat pipe (400); When the first type of heat pipe (400) passes through the gap, the second type of heat pipe (500) is pressed tightly against the first type of heat pipe (400).
7. The heat dissipation device based on an integrated casting satellite according to claim 1, characterized in that: The crimping joints of the second type heat pipe (500) and the first type heat pipe (400) are connected by screws and filled with thermal grease.
8. The heat dissipation device based on an integrated casting satellite according to claim 1, characterized in that: The connection points between the typical first-class stand-alone device (200) and the typical second-class stand-alone device (300) and the satellite cabin panel (100) are filled with thermal conductive silicone grease.
9. The heat dissipation device based on an integrated casting satellite according to claim 4, characterized in that: Typical heat consumptions of the first single machine (210), the second single machine (220) and the third single machine (230) are 50W, 200W and 50W respectively; the second single machine (220) is a high-power single machine; the typical second-class single machine device (300) is a high-power single machine; and the heat consumption of the typical second-class single machine device (300) is 220W.
10. The heat dissipation device based on an integrated casting satellite according to claim 1, characterized in that: The outer surface of the satellite cabin panel (100), the surfaces of the typical second-class stand-alone equipment (300), the first-class heat pipe (400), and the second-class heat pipe (500) are sprayed with white paint, and the inner surface of the satellite cabin panel (100) and the surface of the typical first-class stand-alone equipment (200) are sprayed with high-emissivity black paint or subjected to black anodizing treatment.