Microgroove phase change vapor chamber

Abstract

The microgroove phase change vapor chamber comprises a capillary phase change heat diffusion plate, fractal gradient heat capacity plates and a heat radiation plate, the fractal gradient heat capacity plates are arranged on the two sides of the heat absorption end of the capillary phase change heat diffusion plate respectively, and the heat radiation plate is arranged at the top of the other heat release end of the capillary phase change heat diffusion plate; the capillary phase change heat diffusion plate comprises a heat dissipation shell, a micro-column structure, a cross-shaped supporting column, a micro-channel structure and a liquid absorption core structure. The fractal gradient heat capacity plate comprises a heat capacity shell and a fractal fin structure. The vapor chamber has the advantages that the vapor chamber can still keep high heat conduction efficiency under instantaneous heat load and has a heat storage function.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of space heat management, in particular to a micro-groove phase change heat plate. BACKGROUND

[0002] Spacecraft often faces extreme temperature fluctuations, due to the influence of solar radiation and earth shadow area, need to have an effective heat management system to keep the internal equipment of spacecraft in a safe working temperature range. With the increasing demand for high power density and high heat flow density heat dissipation in the field of electronic equipment, the heat plate becomes the key component of efficient heat dissipation.

[0003] However, the existing heat plate has the problems of slow thermal response speed and limited heat storage capacity in a dynamic working environment. Therefore, how to design a heat plate that can still maintain high heat conduction efficiency under instantaneous heat load and has heat storage function has become a technical problem to be solved at present. SUMMARY

[0004] The technical problem to be solved by the present application is how to provide a heat plate that can still maintain high heat conduction efficiency under instantaneous heat load and has heat storage function.

[0005] To solve the above technical problems, the present application provides the following technical solutions:

[0006] A micro-groove phase change heat plate, comprising a capillary phase change heat diffusion plate, a fractal gradient heat capacity plate and a heat radiation plate, the capillary phase change heat diffusion plate is provided with a fractal gradient heat capacity plate on both sides of the heat absorption end, and a heat radiation plate is provided on the top of the other heat release end.

[0007] The capillary phase change heat diffusion plate comprises a heat dissipation shell, a micro-column structure, a cross support column, a micro-groove structure and a liquid absorption core structure, the heat dissipation shell is provided with a micro-column structure at the heat absorption end, a plurality of cross support columns are arranged in parallel away from the heat absorption end, a micro-groove structure is arranged between adjacent columns of cross support columns for connecting the heat absorption end and the heat release end, and the liquid absorption core structure is embedded in the micro-column structure, the cross support columns are non-uniformly distributed along the axial extension direction of the micro-column structure, and the axial length of the cross support column is greater than its radial length.

[0008] The fractal gradient heat capacity plate comprises a heat capacity shell and a fractal fin structure, and a plurality of fractal fin structures are arranged on one side of the heat capacity shell close to the capillary phase change heat diffusion plate.

[0009] The part of heat generated by the spacecraft is efficiently transmitted to the heat radiation surface through the capillary phase change heat diffusion plate, and the remaining heat is stored in the fractal gradient heat capacity plate, thereby providing effective heat management capability in extreme space environment, protecting the key equipment of the spacecraft from thermal damage; and the heat transferred in the capillary phase change heat diffusion plate is radiated away by the space low-temperature environment, without additional cooling device, only relying on the self-circulation of the working fluid in the capillary phase change heat diffusion plate to complete the cooling process, improving the reliability and safety of the space mission, and realizing the high heat conduction efficiency and heat storage function under the instantaneous heat load.

[0010] Preferably, the heat dissipation shell comprises a cover body and a bottom plate, the cover body is covered on the bottom plate, the micro column structure, the cross support column, the micro channel structure and the liquid absorption core structure are all arranged on the bottom plate.

[0011] Preferably, the micro column structure is arranged in a plurality of groups of column matrix, and the liquid absorption core structure is arranged between adjacent columns.

[0012] Preferably, the porosity of the liquid absorption core structure is arranged in a continuous gradient from the heat absorption end to the heat release end of the capillary phase change heat diffusion plate.

[0013] Preferably, the fractal fin structure comprises a first fin and a second fin, one end of the first fin is fixed to one side of the heat melting shell close to the capillary phase change heat diffusion plate, and the other end is connected to the second fin.

[0014] Preferably, the first fin is in a strip structure, and the second fin is in a V-shaped structure and its opening direction is away from the first fin.

[0015] Preferably, the length and width of the fractal fin structure satisfy the following relationship:

[0016] L k =L0alpha k k=0,1,...n

[0017] W k =W0alpha -k / Δ k=0,1,...n

[0018] In the formula, L0 and W0 represent the length and width of the first fin respectively, k is the fractal order, alpha represents the length ratio, and delta represents the width fractal dimension.

[0019] Compared with the prior art, the beneficial effects of the present application are:

[0020] The part of heat generated by the spacecraft is efficiently transmitted to the heat radiation surface through the capillary phase change heat diffusion plate, and the remaining heat is stored in the fractal gradient heat capacity plate, thereby providing effective heat management capability in the extreme space environment, protecting the key equipment of the spacecraft from thermal damage; and the heat transferred in the capillary phase change heat diffusion plate is radiated away by the space low temperature environment, without additional cooling device, only relying on the self-circulation of the working fluid in the capillary phase change heat diffusion plate to complete the cooling process, thereby improving the reliability and safety of the space mission. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 It is a structural schematic diagram of an embodiment of the present application.

[0022] Figure 2 It is a partial structural schematic diagram of the capillary phase change heat diffusion plate of an embodiment of the present application.

[0023] Figure 3 It is a partial sectional view of the capillary phase change heat diffusion plate of an embodiment of the present application.

[0024] Figure 4 It is a structural schematic diagram of the fractal gradient heat capacity plate of an embodiment of the present application. DETAILED DESCRIPTION

[0025] In order to facilitate those skilled in the art to understand the technical scheme of the present application, the technical scheme of the present application will be further described in conjunction with the drawings of the specification.

[0026] In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connection", "connecting", "fixing" and the like should be understood in a broad sense, for example, can be fixedly connected, or can be detachably connected, or can be integrated; can be mechanically connected, or can be electrically connected, or can be communicated; can be directly connected, or can be indirectly connected through an intermediate medium; can be the communication or interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0027] In the present application, unless otherwise explicitly specified and limited, the terms "first", "second" are only for the purpose of description, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "multiple" is two or more, unless otherwise explicitly specified and limited.

[0028] Reference Figure 1The embodiment discloses a micro-groove phase change vapor chamber, which comprises a capillary phase change heat diffusion plate 1, a fractal gradient heat capacity plate 2 and a heat radiation plate 3. The capillary phase change heat diffusion plate 1 is divided into a heat absorption end and a heat release end at two ends. The upper end face of the heat absorption end of the capillary phase change heat diffusion plate 1 is used for placing a heat source 4. The fractal gradient heat capacity plate 2 is arranged on the two sides of the heat absorption end of the capillary phase change heat diffusion plate 1. The heat radiation plate 3 is arranged at the top of the heat release end of the capillary phase change heat diffusion plate 1.

[0029] Referring to Figure 2 and Figure 3 The capillary phase change heat diffusion plate 1 comprises a heat dissipation shell 11, a micro-column structure 12, a cross support column 13, a micro-groove structure 14 and a liquid absorption core structure 15. The heat dissipation shell 11 comprises a cover (not marked in the figure) and a bottom plate 111. The cover is arranged on the bottom plate 111. The micro-column structure 12, the cross support column 13, the micro-groove structure 14 and the liquid absorption core structure 15 are arranged on the bottom plate 111. Among them Figure 2 The X direction is the axial direction, and the Y direction is the radial direction.

[0030] Specifically, the micro-column structure 12 is arranged at the heat absorption end of the heat dissipation shell 11. In the embodiment, the micro-column structure 12 is arranged in a matrix form by multiple groups of columns. The micro-column structure 12 provides a path for heat conduction in the heat dissipation shell 11. The liquid absorption core structure 15 is arranged between adjacent columns. The porosity of the liquid absorption core structure 15 is arranged in a continuous gradient from the heat absorption end to the heat release end of the heat dissipation shell 11. The working fluid in the heat dissipation shell 11 is sucked by the capillary action provided by the liquid absorption core structure 15. It should be noted that the liquid absorption core structure 15 in the embodiment can be purchased in the market, for example, the liquid absorption core structure 15 is a capillary core. The multiple cross support columns 13 are arranged side by side away from the heat absorption end of the heat dissipation shell 11. The micro-groove structure 14 is arranged between adjacent columns of the cross support columns 13 for connecting the heat absorption end and the heat release end. The liquid absorption core structure 15 is embedded in the micro-column structure 12. The cross support columns 13 are non-uniformly distributed along the axial extension direction of the micro-column structure 12. The axial length of the cross support column 13 is greater than the radial length of the cross support column 13. The surface deformation of the capillary phase change heat diffusion plate 1 caused by the positive pressure in the heat dissipation shell 11 is prevented. The cross support column 13 is combined along the axial extension direction of the micro-column structure 12. The flow path of the working fluid is optimized while the deformation is inhibited. The bottleneck of the trade-off between mechanical stability and heat transfer efficiency of the traditional vapor chamber is broken. A dual-function structure of pressure-resistant support and working fluid flow guide is formed.

[0031] Referring to Figure 4The fractal gradient heat capacity plate 2 comprises a heat capacity shell 21 and a fractal fin structure 22, and the heat capacity shell 21 is internally provided with the multi-stage fractal fin structure 22 close to one side of the capillary phase change heat diffusion plate 1. The fractal fin structure 22 comprises a first fin 221 and a second fin 222. One end of the first fin 221 is fixed to the inside of the heat capacity shell 21 close to the capillary phase change heat diffusion plate, and the other end is connected to the second fin 222. In this embodiment, the first fin 221 is in a strip structure, and the second fin 222 is in a V-shaped structure with an opening direction away from the first fin 221.

[0032] Specifically, in this embodiment, the length and width of the fractal fin structure 22 satisfy the following relationship:

[0033] L k = L0α k k = 0, 1,..., n

[0034] W k = W0α -k / Δ k = 0, 1,..., n

[0035] In the formula, L0 and W0 represent the length and width of the first fin respectively, k is the fractal order, α represents the length ratio, and Δ represents the width fractal dimension.

[0036] The fractal fin structure 22 in the heat capacity shell 21 strengthens heat transfer. Since the melting rate of the phase change material close to the capillary phase change heat diffusion plate 1 is higher than that of the phase change material away from the capillary phase change heat diffusion plate 1, the first fin 221 is arranged close to the capillary phase change heat diffusion plate 1, and the second fin 222 is arranged away from the capillary phase change heat diffusion plate 2. Therefore, the melting rate of the phase change material on the inside can be significantly improved.

[0037] Through the coupling design of the multi-stage fractal fin structure 22, the local thermal saturation problem caused by uneven heat flow distribution in the traditional heat storage cavity is solved, and the dynamic balance of the melting / solidification rate of the phase change material is realized. In addition, the heat diffusion path of the fractal fin structure 22 and the working fluid circulation path of the micro-channel structure 14 work together to realize double-mode thermal management under dynamic thermal load.

[0038] The working principle of this embodiment is as follows:

[0039] In the heat source working stage, part of the heat is transferred to the working fluid in the heat dissipation shell 11 by the micro-column structure 12 in the form of heat conduction, the working fluid is heated and evaporated, the generated steam moves axially upward and moves along the steam flow space to the heat releasing end of the capillary phase change heat diffusion plate 1, and then condenses into liquid after transferring heat to the heat radiation plate 3 arranged at the upper part of the heat releasing end, and the heat radiation plate 3 dissipates heat to the low-temperature environment outside. The condensed liquid returns to the heat absorbing end of the capillary phase change heat diffusion plate 1 under the capillary force provided by the wick structure 15 in the micro-channel structure 14, so as to complete the efficient transmission of heat from the heat source 4 to the heat radiation plate 3. At the same time, another part of the heat from the heat source 4 is directly stored in the fractal gradient heat capacity plate 2, absorbed by the phase change material, and in the non-working stage of the heat source, the heat of the solidified phase change material is taken away by the heat radiation plate 4, so as to restore to the initial state.

[0040] In the embodiment, part of the heat generated by the spacecraft is efficiently transmitted to the heat radiation surface by the capillary phase change heat diffusion plate 1, and the remaining heat is stored in the fractal gradient heat capacity plate 2, so as to provide effective heat management capability in the extreme space environment, and protect the key equipment of the spacecraft from thermal damage; and the heat transferred in the capillary phase change heat diffusion plate 1 is taken away by the space low-temperature environment radiation, without the need for an additional cooling device, and only relying on the self-circulation of the working fluid in the capillary phase change heat diffusion plate 1 to complete the cooling process, thereby improving the reliability and safety of the space mission.

[0041] It is obvious to those skilled in the art that the present application is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or essential characteristics of the present application. Therefore, the embodiments should be regarded as exemplary and non-limiting, and the scope of the present application is defined by the appended claims rather than the above description, and therefore all changes falling within the meaning and scope of the equivalent elements of the claims are intended to be included in the present application, and any reference signs in the claims should not be regarded as limiting the claims involved.

[0042] The above-described embodiments only represent the implementation of the application, and the protection scope of the application is not limited to the above-described embodiments. For those skilled in the art, without departing from the concept of the present application, a number of modifications and improvements can be made, which are all within the protection scope of the present application.

Claims

1. A micro-groove phase change vapor chamber, characterized by: The application relates to a heat diffusion plate, and relates to a heat diffusion plate comprising a capillary phase change heat diffusion plate, a fractal gradient heat capacity plate and a heat radiation plate. The capillary phase change heat diffusion plate comprises a heat dissipation shell, a micro-column structure, a cross support column, a micro-channel structure and a liquid absorption core structure. The fractal gradient heat capacity plate comprises a heat capacity shell and a fractal fin structure.

2. The micro-groove phase change vapor chamber of claim 1, wherein: The heat dissipation shell comprises a cover and a bottom plate.

3. The micro-groove phase change vapor chamber of claim 1, wherein: The micro-column structure is arranged in a matrix of column groups, and the liquid absorption core structure is arranged between adjacent columns.

4. The micro-groove phase change vapor chamber of claim 1, wherein: The porosity of the liquid absorption core structure is arranged in a continuous gradient from the heat absorption end to the heat release end of the capillary phase change heat diffusion plate.

5. The micro-groove phase change vapor chamber of claim 1, wherein: The fractal fin structure comprises a first fin and a second fin.

6. The micro-channel phase change thermal panel according to claim 5, wherein: The first fin is in a strip structure, and the second fin is in a V-shaped structure.

7. The micro-channel phase change thermal panel of claim 1, wherein: The length and width of the fractal fin structure satisfy the following relationship: L k = Loα k k = 0, 1,... n W k = W0α -k / Δ k = 0, 1,... n In the formula, L0 and W0 represent the length and width of the first fin, k is the fractal order, alpha represents the length ratio, and delta represents the width fractal dimension.

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