Astronavigation branch channel heat pipe suitable for multi-heat-source temperature equalization

Abstract

The invention provides an astronavigation branch channel heat pipe suitable for multi-heat-source temperature equalization, the heat pipe comprises a shell, channels and a supporting column, the shell comprises a connecting section and branch sections, the multiple branch sections communicate with the connecting section, and the connecting section and the multiple branch sections are connected with different heat sources; the channels are formed in the inner side wall of the shell, the channels comprise a side channel, a top channel and a bottom channel, the side channel is arranged along the side contour line of the shell to form a communication loop communicated with all the branch sections, and any branch section is communicated with the connecting section through the top channel and the bottom channel. Working medium conveying channels among multiple heat sources are established through the annular through channels in the inner wall of the heat pipe, efficient heat transfer among multiple branches of the heat pipe can be achieved, and therefore temperature equalization of the multiple heat sources is achieved; the heat sources are connected through the independent branches, so that the temperature equalizing speed is high, and the temperature equalizing temperature difference is small; the structure is compact, the weight is light, and temperature equalization of multiple heat sources in a small space can be achieved.

Description

Technical Field

[0001] The present invention relates to the field of aerospace thermal control technology, and in particular to an aerospace branch channel heat pipe suitable for temperature uniformity of multiple heat sources. Background Art

[0002] With the miniaturization and integration of spacecraft, the distribution of heat sources in spacecraft has become more and more complex. How to achieve uniform temperature of complex distributed heat sources in a small space has become a difficult problem for spacecraft thermal control.

[0003] Heat pipes are highly efficient passive thermal control products that use phase change of working fluid to achieve heat transfer. They have the advantages of high heat transfer efficiency, high heat transfer power, and compact structure, and are widely used in spacecraft. At present, the research on temperature equalization of multiple heat sources in spacecraft mainly focuses on multi-evaporator loop heat pipes and temperature equalization plates. However, multi-evaporator loop heat pipes have many components and complex structures; temperature equalization plates require a large installation space and are heavy.

[0004] The existing Chinese patent with publication number CN103344144A discloses a composite groove heat pipe, which belongs to the field of heat pipe technology. The heat pipe comprises an evaporation section, an insulation section and a condensation section, and the evaporation section, the insulation section and the condensation section are all in the shape of a circular tube, and the three sections are of equal diameter and coaxial. The capillary wick structure is a composite groove. The composite groove is formed by connecting a V-shaped groove and a circular groove through a slit.

[0005] Due to the limitations of bending radius and manufacturing process, traditional slot heat pipes cannot simultaneously average the temperature of multiple complexly distributed heat sources, and cannot be installed in complex small spaces. Therefore, there is an urgent need to develop a new type of slot heat pipe that can average the temperature of multiple heat sources in a limited space. Summary of the invention

[0006] In view of the defects in the prior art, an object of the present invention is to provide an aerospace branch channel heat pipe suitable for equalizing the temperature of multiple heat sources.

[0007] According to the present invention, an aerospace branch slot heat pipe suitable for equalizing the temperature of multiple heat sources is provided. The heat pipe comprises: a shell, a slot and a support column. A hollow cavity is formed inside the shell, and the inside of the hollow cavity is filled with a gaseous working medium. The shell comprises a connecting section and a branch section. A plurality of the branch sections are respectively connected to the connecting section. The connecting section and the plurality of the branch sections are respectively connected to different heat sources. A plurality of the support columns are arranged inside the connecting section. A mounting hole connected to the outside is opened inside the support column. The heat pipe is fastened to the heat source through the mounting hole.

[0008] The groove is arranged on the inner wall of the shell, and the groove is filled with liquid working medium. The groove includes a side groove, a top groove and a bottom groove. The side groove is arranged along the side contour line of the shell to form a connecting circuit connecting all branch segments. Any branch segment is connected to the connecting segment through the top groove and the bottom groove.

[0009] Preferably, the cross-section of the groove of the channel is Ω-shaped, the top is a narrow slit that draws the condensed liquid working medium into the bottom of the groove by capillary force, the width of the narrow slit is 0.2-0.4mm, the depth is 0.5-0.7mm, and the bottom of the groove is a cylindrical cavity with a diameter of 0.8-1.2mm.

[0010] Preferably, the grooves of the channel include parallel grooves, and the distance between two adjacent grooves is 1.2-1.6 mm.

[0011] Preferably, the liquid working medium in the channel includes ammonia.

[0012] Preferably, the upper and lower surfaces of the shell are both planes, and the flatness is better than 100mm×100mm:0.1mm.

[0013] Preferably, the support column is cylindrical with a diameter of 9-11 mm.

[0014] Preferably, the bending radius of the branch segment is less than 5 times the side length of the outer contour of the cross section of the branch segment.

[0015] Preferably, the number of the branch segments matches the number of heat sources, the direction of the branch segments can be adjusted according to the distribution of the heat sources and the installation space, and the size can be adjusted according to the power of the heat sources.

[0016] Preferably, the heat pipe is made by a metal additive manufacturing method, and is sealed by welding after the working fluid is filled.

[0017] Preferably, the heat pipe is fastened to the heat source by means of screws and the mounting holes, and thermally conductive silicone rubber is coated on the mounting surface of the heat pipe before installation.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] The present invention connects multiple heat sources through branches of the groove heat pipe, and establishes a working fluid transport channel between the multiple heat sources through the annular groove on the inner wall of the heat pipe, so as to achieve efficient heat transfer between the multiple branches of the heat pipe, thereby achieving temperature equalization of the multiple heat sources; each heat source is connected by an independent branch, so the temperature equalization speed is fast and the temperature difference is small; it overcomes the shortcomings of traditional temperature equalizing plates, such as large installation space and heavy weight, has a compact structure, light weight, and can achieve temperature equalization of multiple heat sources in a small space. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0021] Figure 1 The present invention mainly embodies a schematic diagram of an aerospace branch channel heat pipe suitable for equalizing the temperature of multiple heat sources;

[0022] Figure 2 The cross-sectional view of the aerospace branch channel heat pipe mainly embodies the present invention and is suitable for equalizing the temperature of multiple heat sources;

[0023] Figure 3 It is a cross-sectional view of the groove which mainly embodies the present invention.

[0024] As shown in the figure:

[0025] Connecting section 1 Branch section 2 Shell 3

[0026] Channel 4 Support column 5 Mounting hole 6

[0027] Side channel 7 Top channel 8 Bottom channel 9 DETAILED DESCRIPTION

[0028] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0029] like Figure 1-3 As shown, according to the present invention, an aerospace branch groove heat pipe suitable for uniform temperature of multiple heat sources is provided, the heat pipe comprises: a shell 3, a groove 4 and a support column 5, a hollow cavity is formed inside the shell 3, the hollow cavity is filled with a gaseous working medium, the shell 3 comprises a connecting section 1 and a branch section 2, a plurality of branch sections 2 are respectively connected to the connecting section 1, the connecting section 1 and the plurality of branch sections 2 are respectively connected to different heat sources, a plurality of support columns 5 are arranged inside the connecting section 1, a mounting hole 6 connected to the outside is opened inside the support column 5, and the heat pipe is fastened to the heat source through the mounting hole 6; the groove 4 is arranged on the inner side wall of the shell 3, the groove 4 is filled with a liquid working medium, the groove 4 comprises a side groove 7, a top groove 8 and a bottom groove 9, the side groove 7 is arranged along the side contour line of the shell 3, forming a connecting circuit connecting all the branch sections 2, and any branch section 2 is connected to the connecting section 1 through the top groove 8 and the bottom groove 9.

[0030] The shell 3 includes multiple branch sections 2 for connecting multiple heat sources; the groove 4 is located on the side wall, top surface and bottom surface of the shell 3; the groove 4 is annular on the side wall, and a liquid suction reflux channel for the working fluid between the branches is established through the groove 4 to achieve uniform temperature or heat dissipation of multiple heat sources; the support column 5 is located at the connecting section 1 of the heat pipe to ensure the structural strength of the heat pipe, and the mounting hole 6 is located at the center of the support column 5 for mounting and fixing the heat source and the heat pipe.

[0031] The cross-section of the groove 4 is Ω-shaped, and the top is a narrow slit that absorbs the condensed liquid working medium into the bottom of the groove by capillary force. To ensure that the groove has sufficient liquid absorption capacity, the narrow slit should have a smaller width and a larger depth. The width of the narrow slit is 0.2-0.4mm and the depth is 0.5-0.7mm. The bottom of the groove is a cylindrical cavity for storing liquid working medium and transporting the working medium to the evaporation section. To ensure that the groove has sufficient liquid delivery capacity, the cavity should have a larger diameter. The diameter of the cylindrical cavity is 0.8-1.2mm.

[0032] The grooves of the channel 4 are preferably parallel grooves, and the distance between two adjacent grooves is 1.2-1.6 mm. The liquid working medium in the channel 4 includes ammonia.

[0033] The upper and lower surfaces of the shell 3 are both flat, with a flatness better than 100mm×100mm:0.1mm, for installing a heat source that requires uniform temperature and reducing contact thermal resistance.

[0034] The support column 5 is cylindrical and located in the connecting section 1. It is used to increase the structural strength of the aerospace branch channel heat pipe and to ensure the safety of the heat pipe when it is in a high temperature condition. The diameter is 9-11 mm. The mounting hole 6 is located at the center of the support column 5, and a screw can be installed to facilitate the installation and fixation between the heat pipe and the heat source.

[0035] The bending radius of the branch segment 2 may be less than 5 times the characteristic dimension, that is, the side length of the outer contour of the cross section of the branch segment 2 .

[0036] The number of branch segments 2 matches the number of heat sources. The direction of the branch segments 2 can be adjusted according to the distribution of the heat sources and the installation space, and the size can be adjusted according to the power of the heat sources.

[0037] The heat pipe is made by metal additive manufacturing method, and is sealed by welding after the working fluid is filled. The heat pipe and the heat source are fastened together by screws and mounting holes 6, and the mounting surface of the heat pipe is coated with thermal conductive silicone rubber before installation.

[0038] The present application is a channel heat pipe with multiple branch sections 2. Through the connection of the branch sections 2, a heat transfer channel between any heat sources can be established to achieve uniform temperature of any distributed heat sources. The channel 4 forms a connecting loop along the side contour line of the heat pipe. The liquid working medium circulates in the loop of the side channel 7. Through the connection of the side wall annular channel, a liquid suction reflux channel between the branch sections is established to achieve heat transfer between the branch sections; through the connection of the top surface channel 8 and the bottom surface channel 9, a liquid suction reflux channel between the branch section and the connecting section is established to achieve heat transfer between the branch section and the connecting section.

[0039] This application is further described by taking the following data as an example.

[0040] The branch section 2 includes 3 branches, and together with the connecting section 1, it can simultaneously equalize the temperature or dissipate heat for 4 heat sources. The narrow slit width of the groove 4 is preferably 0.3mm, the groove depth is preferably 0.6mm, and the diameter of the cylindrical cavity at the bottom of the groove is preferably 1.0mm. The support column 5 support column diameter is preferably 10mm, and the mounting hole 6 is preferably 4.3mm in diameter for installing M4 screws. The side groove 7 forms a ring loop along the side contour of the heat pipe to connect the branch section 2 and the branch section 2 to realize the transport of the working fluid between the branch section 2 and the branch section 2. The top surface groove 8 and the bottom surface groove 9 are used to connect the branch section 2 and the connecting section 1 to realize the transport of the working fluid between the branch section 2 and the connecting section 1. Considering the heat transfer capacity and processing difficulty, the groove spacing is preferably 1.4mm. The aerospace branch groove heat pipe is processed by metal 3D printing technology. In order to ensure that the heat pipe has good thermal conductivity and structural strength, the 3D printing material is AlSi10Mg. The thermal resistance between branch section 2 and connection section 1 of the aerospace branch channel heat pipe is 0.15K / W, and the thermal resistance between branch section 2 and branch section 2 is 0.17K / W. The maximum thermal resistance is 16% lower than that of the traditional temperature equalizer of the same weight. The heat transfer performance is good and can meet the thermal control requirements of spacecraft. The maximum temperature difference of the aerospace branch channel heat pipe is 0.9℃ under the heating of heat sources with powers of 4W, 8W, 12W and 16W respectively, which is 13% lower than that of the traditional temperature equalizer of the same weight. The temperature equalization performance is good and can meet the thermal control requirements of spacecraft.

[0041] The present application can achieve temperature equalization of multiple heat sources with complex distribution in a small space of a spacecraft through multiple branch sections 2 and connecting sections 1. The present application uses the branches of the slotted heat pipe to connect multiple heat sources, and establishes a working fluid transport channel between multiple heat sources through the annular slots that penetrate the inner wall of the heat pipe, which can achieve efficient heat transfer between multiple branches of the heat pipe, thereby achieving temperature equalization of multiple heat sources; each heat source is connected by an independent branch, so the temperature equalization speed is fast and the temperature difference is small. The present application overcomes the shortcomings of the traditional temperature equalization plate, which requires a large installation space and is heavy. It has a compact structure and is light in weight, and can achieve temperature equalization of multiple heat sources in a small space.

[0042] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0043] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. An aerospace branch channel heat pipe suitable for equalizing the temperature of multiple heat sources, characterized in that: The heat pipe comprises: a shell (3), a groove (4) and a support column (5); a hollow cavity is formed inside the shell (3); the hollow cavity is filled with a gaseous working medium; the shell (3) comprises a connecting section (1) and a branch section (2); a plurality of branch sections (2) are respectively connected to the connecting section (1); the connecting section (1) and a plurality of branch sections (2) are respectively connected to different heat sources; a plurality of support columns (5) are arranged inside the connecting section (1); a mounting hole (6) connected to the outside is opened inside the support column (5); the heat pipe is fixedly connected to the heat source through the mounting hole (6); The groove (4) is arranged on the inner side wall of the shell (3), and the groove (4) is filled with a liquid working medium. The groove (4) comprises a side groove (7), a top groove (8) and a bottom groove (9). The side groove (7) is arranged along the side contour line of the shell (3) to form a connecting loop connecting all the branch sections (2). Any branch section (2) is connected to the connecting section (1) through the top groove (8) and the bottom groove (9).

2. The aerospace branch channel heat pipe suitable for temperature uniformity of multiple heat sources as claimed in claim 1, characterized in that: The cross section of the groove of the channel (4) is Ω-shaped, the top is a narrow slit for sucking the condensed liquid working medium into the bottom of the groove by capillary force, the width of the narrow slit is 0.2-0.4 mm, the depth is 0.5-0.7 mm, and the bottom of the groove is a cylindrical cavity with a diameter of 0.8-1.2 mm.

3. The aerospace branch channel heat pipe suitable for temperature uniformity of multiple heat sources as claimed in claim 1, characterized in that: The grooves of the channel (4) include parallel grooves, and the distance between two adjacent grooves is 1.2-1.6 mm.

4. The aerospace branch channel heat pipe suitable for multi-heat source temperature uniformity according to claim 1, characterized in that: The liquid working medium in the channel (4) includes ammonia.

5. The aerospace branch channel heat pipe suitable for equalizing the temperature of multiple heat sources as claimed in claim 1, characterized in that: The upper and lower surfaces of the shell (3) are both flat, with a flatness better than 100 mm×100 mm: 0.1 mm.

6. The aerospace branch channel heat pipe suitable for equalizing the temperature of multiple heat sources as claimed in claim 1, characterized in that: The support column (5) is cylindrical and has a diameter of 9-11 mm.

7. The aerospace branch channel heat pipe suitable for equalizing the temperature of multiple heat sources as claimed in claim 1, characterized in that: The bending radius of the branch segment (2) is less than 5 times the side length of the outer contour of the cross section of the branch segment (2).

8. The aerospace branch channel heat pipe suitable for equalizing the temperature of multiple heat sources as claimed in claim 1, characterized in that: The number of the branch segments (2) matches the number of heat sources; the direction of the branch segments (2) can be adjusted according to the distribution of the heat sources and the installation space; and the size can be adjusted according to the power of the heat sources.

9. The aerospace branch channel heat pipe suitable for equalizing the temperature of multiple heat sources as claimed in claim 1, characterized in that: The heat pipe is made by a metal additive manufacturing method and is sealed by welding after the working fluid is filled.

10. The aerospace branch channel heat pipe suitable for equalizing the temperature of multiple heat sources as claimed in claim 1, characterized in that: The heat pipe and the heat source are fastened together by means of screws and the mounting holes (6), and before mounting, thermally conductive silicone rubber is coated on the mounting surface of the heat pipe.

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