A phase change thermal management package structure for a hypersonic vehicle conformal antenna

Abstract

The application discloses a phase change thermal management packaging structure for a hypersonic vehicle conformal antenna and belongs to the technical field of conformal antennas, and comprises a phase change cold plate and a packaging shell on the upper surface of the phase change cold plate, both of which are conformal to the antenna, can reduce the contact thermal resistance, and the conformal phase change cold plate provides additional mechanical support, thereby increasing the stability of the whole structure; the phase change cold plate comprises a base and a surface end cover; the surface end cover comprises a plurality of strip-shaped hollow parts; the surface end cover is located above the base and forms a cavity filled with a phase change material; the cavity further comprises a plurality of fins and a plurality of protruding parts; each protruding part comprises a long groove; the orthographic projections of the strip-shaped hollow parts are respectively coincident with the orthographic projections of the long grooves in the direction perpendicular to the plane where the phase change cold plate is located; and the fins are located on the outer surfaces of at least one side wall of each protruding part, so that the filling rate of the phase change material can be improved, the occupied volume can be reduced, and the heat conduction effect can be improved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of conformal antennas, and particularly relates to a phase change thermal management packaging structure for a conformal antenna of a hypersonic aircraft. BACKGROUND

[0002] With the development of antenna technology, compared with traditional planar antennas, conformal antennas are closely attached to the surface of the shell, which not only enhances the stealth capability of the aircraft, but also improves the overall integration and aerodynamic performance. Therefore, conformal antennas are crucial in hypersonic aircrafts. However, as the integration of antennas continues to improve, the power density of T / R components (transmit / receive modules) also gradually increases, and generates a lot of heat during operation. Without effective thermal management, the performance of the antenna will decrease, the service life will be shortened, and even failure and damage will occur. Therefore, efficient thermal management of T / R components is not only the basis for ensuring normal operation, but also the key to improving overall reliability.

[0003] Phase change heat dissipation belongs to passive heat dissipation technology, which does not require additional power sources. The phase change material does not change in temperature during the phase change process, but stores a large amount of heat energy. Compared with traditional air cooling and liquid cooling heat dissipation technologies, phase change heat dissipation has higher heat absorption capacity and higher space utilization rate, and can be flexibly integrated into cold plates of various shapes and sizes.

[0004] At present, the commonly used thermal management equipment for aircrafts is a planar cold plate, which has a single structure and is difficult to adapt to complex and multi-curved antenna shapes. Moreover, the planar cold plate cannot fully utilize the space, and the volume size required to fill the same mass of phase change material is large, which is not conducive to lightweight. At the same time, the planar cold plate is difficult to fit the irregular heat source surface, and the heat dissipation area is limited, which increases the local thermal resistance, reduces the heat conduction efficiency, and may cause hot spots in the heat source concentrated area, affecting the overall heat dissipation effect. In addition, the above-mentioned planar structure causes the heat diffusion path to be radial, resulting in uneven temperature between the edge area and the center, and a large temperature gradient, which reduces the service life of the antenna.

[0005] In summary, the antenna in the hypersonic aircraft has the characteristics of high heat flux and complex and compact structure, and the planar cold plate has little effect on heat dissipation. SUMMARY

[0006] In order to solve the above problems in the prior art, the present application provides a phase change thermal management packaging structure for a conformal antenna of a hypersonic aircraft. The technical problems to be solved by the present application are solved by the following technical scheme:

[0007] The present application provides a phase change thermal management packaging structure for a conformal antenna of a hypersonic aircraft, comprising: a phase change cold plate and a packaging shell located on the upper surface of the phase change cold plate, the phase change cold plate and the packaging shell are conformal designed with the antenna; wherein,

[0008] The phase change cold plate includes: a base and a surface end cap; the surface end cap includes a plurality of strip-shaped hollow portions extending along a first direction and arranged along a second direction, the first direction being perpendicular to the second direction; the surface end cap is located above the base, forming a cavity filled with phase change material, the cavity also including a plurality of fins and a plurality of protrusions, each of the protrusions including a long groove, along a direction perpendicular to the plane where the phase change cold plate is located, the orthographic projection of each strip-shaped hollow portion coincides with the orthographic projection of each long groove, and the fins are located on the outer surface of at least one sidewall of each protrusion.

[0009] In one embodiment of the present invention, it further includes an upper aerogel and a lower aerogel, located on the upper and lower surfaces of the encapsulation shell, respectively.

[0010] In one embodiment of the present invention, the phase change material includes: paraffin wax, expanded graphite, or a mixed phase change material of paraffin wax and expanded graphite.

[0011] In one embodiment of the present invention, the fins have a tree-like structure.

[0012] In one embodiment of the present invention, when both outer surfaces of the two sidewalls of a certain protrusion include fins, the fins on the two outer surfaces of the two sidewalls are symmetrical about the protrusion.

[0013] In one embodiment of the present invention, the base further includes a plurality of through holes penetrating the lower surface of the groove in the protrusion and the lower surface of the base.

[0014] In one embodiment of the present invention, the plurality of through holes are arranged to form a plurality of sub-rows extending along a first direction and arranged along a second direction;

[0015] Along the direction perpendicular to the plane where the phase change cold plate is located, the orthographic projection of each sub-row is located within the orthographic projection of each of the strip-shaped hollow portions.

[0016] In one embodiment of the present invention, the fins of the tree-like structure are optimized according to the following steps:

[0017] To minimize the average temperature of the phase change material, the objective function is established as follows:

[0018]

[0019] In the formula, V represents the volume of the cavity, T represents the temperature of the phase change material, ε represents the minimum average temperature of the phase change material to be solved, and θ s Indicates fin density, This represents the volume fraction of the phase change material.

[0020] Based on the variable density interpolation model SIMP and the minimum temperature of the phase change material obtained by solving, the thermal conductivity of the phase change material is redefined by interpolation method and penalty factor, and the density filtering smoothing is carried out in combination with Helmholtz filtering equation, the projection is carried out in the way of hyperbolic tangent projection, the shape of the fin after topological optimization and the optimal distribution of the fin material are obtained;Wherein,

[0021] The Helmholtz filtering equation is expressed as:

[0022]

[0023] 0<θ s ≤1;

[0024] In the formula, θ f is the filtered fin density, R min is the filtering radius, R min =0.35mm;

[0025] The variable density interpolation model is expressed as:

[0026]

[0027] In the formula, θ p represents the penalty factor, θ min represents the minimum penalty volume fraction, θ min =0.01, P simp represents the SIMP index, P simp =5;

[0028] The hyperbolic tangent projection function is expressed as:

[0029]

[0030] In the formula, γ represents the projection slope, and η represents the projection threshold.

[0031] In an embodiment of the present application, the material of the phase change cold plate is aluminum alloy.

[0032] Compared with the prior art, the present application has the following advantages:

[0033] (1) The present application provides a phase change thermal management packaging structure of a hypersonic vehicle conformal antenna, which comprises a phase change cold plate and a packaging shell located on the upper surface of the phase change cold plate, the phase change cold plate is designed conformally with the antenna, which can reduce the contact thermal resistance and has excellent heat dissipation advantage, and the conformal cold plate provides additional mechanical support, the closely fitted structure increases the stability of the whole structure, and can also meet the fastening requirements between components, thereby reducing the number of assembly parts and improving the reliability.

[0034] (2) The base and the surface end cover of the phase change cold plate jointly form a cavity, the cavity is filled with a phase change material and includes multiple protruding portions, and the outer surface of at least one side wall in each protruding portion is provided with a tree structure, so that the heat conduction effect is greatly improved. Compared with the way of using traditional heat dissipation fins, the overall heat conduction effect of the present application is better, the occupied volume is small, and the filling rate of the phase change material is improved; compared with the way of heat conduction of the heat pipe, the present application avoids the low reliability caused by the complex installation structure, and effectively solves the problem of low phase change heat dissipation and heat conduction efficiency.

[0035] (3) For the conformal antenna in the hypersonic vehicle, the present application not only considers the heat dissipation problem of the conformal antenna itself, but also uses aerogel material for heat insulation design for friction aerodynamic heat, wherein the first layer of aerogel is located on the upper surface of the packaging shell and can insulate the friction aerodynamic heat from the external environment, and the second layer of aerogel is located between the conformal cold plate and the array antenna, which not only can insulate heat, but also can play an important role in shock absorption, especially when facing mechanical impact or vibration, the impact load can be absorbed and relieved.

[0036] (4) The structure design of the conformal cold plate is flexible, which is manufactured in two parts by machining, the sealing property of the overall structure is ensured by vacuum brazing process, and the aluminum alloy and the phase change material can ensure light weight and high heat conduction capacity at the same time.

[0037] (5) The design of the strip-shaped hollow part and the through hole not only reduces the processing difficulty, but also improves the convenience of disassembly and assembly.

[0038] The present application will be further described in detail below with reference to the accompanying drawings and embodiments. BRIEF DESCRIPTION OF DRAWINGS

[0039] Figure 1 is a schematic diagram of a phase change thermal management packaging structure for a conformal antenna of a hypersonic vehicle provided by an embodiment of the present application;

[0040] Figure 2 is a structural schematic diagram of a phase change cold plate provided by an embodiment of the present application;

[0041] Figure 3 is an internal plan view of a phase change cold plate provided by an embodiment of the present application;

[0042] Figure 4 is a sectional view of a phase change thermal management packaging structure for a conformal antenna of a hypersonic vehicle provided by an embodiment of the present application;

[0043] Figure 5 is an exploded view of a phase change thermal management packaging structure for a conformal antenna of a hypersonic vehicle provided by an embodiment of the present application;

[0044] Figure 6is a bottom view of the phase change cold plate provided by an embodiment of the present application;

[0045] Figure 7 is a top view of the phase change cold plate provided by an embodiment of the present application. DETAILED DESCRIPTION

[0046] The present application will be further described in conjunction with specific embodiments, but the embodiments of the present application are not limited thereto.

[0047] Figure 1 is a schematic diagram of a phase change thermal management packaging structure for a hypersonic vehicle conformal antenna provided by an embodiment of the present application, Figure 2 is a structural schematic diagram of the phase change cold plate provided by an embodiment of the present application, Figure 3 is an internal top view of the phase change cold plate provided by an embodiment of the present application, Figure 4 is a sectional view of the phase change thermal management packaging structure for a hypersonic vehicle conformal antenna provided by an embodiment of the present application. As Figures 1-4 shown, the present application provides a phase change thermal management packaging structure 100 for a hypersonic vehicle conformal antenna, comprising: a phase change cold plate 1 and a packaging shell 2 located on the upper surface of the phase change cold plate 1, both the phase change cold plate 1 and the packaging shell 2 are conformal designed with the antenna; wherein,

[0048] The phase change cold plate 1 comprises: a base 101 and a surface end cover 102; the surface end cover 102 comprises a plurality of strip-shaped hollow parts 103 extending along a first direction and arranged along a second direction, the first direction is perpendicular to the second direction; the surface end cover 102 is located above the base 101, forming a cavity filled with a phase change material 104, the cavity further comprises a plurality of fins 105 and a plurality of protruding parts 106, each protruding part 106 comprises a long slot 107, the orthogonal projection of each strip-shaped hollow part 103 respectively coincides with the orthogonal projection of each long slot 107 along the direction perpendicular to the plane where the phase change cold plate 1 is located, and the fin 105 is located on the outer surface of at least one side wall of each protruding part 106.

[0049] Specifically, in the above phase change thermal management packaging structure 100, both the phase change cold plate 1 and the packaging shell 2 are conformal designed with the antenna, so that the phase change cold plate 1 can be precisely attached to the complex surface of the antenna, thereby increasing the thermal contact area of the phase change cold plate 1, reducing the air gap between the interfaces, reducing the contact thermal resistance and shortening the heat transfer path, so that the heat can be more efficiently transferred from the heat source to the phase change cold plate 1; at the same time, the overall temperature uniformity can be improved, local hot spots can be avoided, and better heat dissipation performance can be achieved.

[0050] Optionally, the phase change cold plate 1 is composed of a base 101 and a surface end cover 102, the surface end cover 102 is located above the base 101, and includes a plurality of strip-shaped hollow parts 103 extending in a first direction and arranged in a second direction. The surface end cover 102 and the base 101 form a cavity, and a plurality of protrusions 106 are arranged in the cavity. Each protrusion 106 extends in the first direction, and the plurality of protrusions 106 are arranged in the second direction, as shown in Figures 2-3 Each protrusion 106 includes a long groove 107, that is, the middle part of each protrusion 106 is concave. In a direction perpendicular to the plane on which the phase change cold plate 1 is located, the orthographic projection of each strip-shaped hollow part 103 coincides with the orthographic projection of each long groove 107, that is, the strip-shaped hollow part 103, the protrusion 106, and the long groove 107 in the protrusion 106 extend in the same direction.

[0051] In this embodiment, the cavity is filled with a phase change material 104 such as paraffin. Paraffin has a high latent heat of phase change and a relatively low cost, so it is widely used in the field of phase change heat dissipation. Paraffin can absorb a large amount of heat during the phase change process, but its thermal conductivity is low, which can cause uneven temperature distribution in the paraffin. To solve this problem, the phase change heat management package structure 100 provided by the present application introduces fins 105 into the cavity to increase the heat dissipation area and the overall thermal conductivity.

[0052] Specifically, each protrusion 106 includes two side walls arranged opposite to each other in the second direction, and at least one side wall of each protrusion 106 is provided with fins 105 on the outer surface to improve the heat conduction efficiency and temperature uniformity. The fins 105 can have a tree structure. It should be noted that when the two side walls of a protrusion 106 are both provided with fins 105, the fins 105 on the outer surfaces of the two side walls are symmetrical about the protrusion 106 to achieve efficient conjugate heat transfer.

[0053] It should be understood that the conventional fins 105 are designed in a uniform geometric shape, which cannot fully utilize the heat distribution of the heat source, resulting in lower local heat conduction efficiency than other areas. They are usually manufactured in standard sizes, which can cause material waste or significant increase in structure weight. Therefore, it is necessary to optimize the distribution of the phase change material 104 in space, dynamically adjust the shape and distribution of the fins 105 according to the different heat flux densities, and accurately configure the material based on the heat dissipation target and heat load, so as to play the best performance in heat dissipation while reducing the overall weight.

[0054] In this embodiment, the tree structure of the fins 105 is optimized according to the following steps:

[0055] S1, establish a target function with the minimum average temperature of the phase change material 104 as the target,

[0056]

[0057] In the formula, V represents the volume of the cavity, T represents the temperature of the phase change material 104, ε represents the minimum average temperature of the phase change material 104 to be solved, θ s represents the fin 105 density, represents the volume fraction of the phase change material 104,

[0058] In this step, by optimizing the objective function, it can be determined that the topology optimization of the fin 105 is to minimize the temperature of the phase change material 104, and the subsequent filtering and projection processing is carried out for this purpose, and the constraint condition is used to determine the volume of the phase change material 104.

[0059] S2, based on the variable density interpolation model SIMP and the minimum temperature of the phase change material 104 solved, the thermal conductivity of the phase change material 104 is redefined by interpolation method and penalty factor, and the density filtering smoothing is carried out by combining the Helmholtz filtering equation, and the hyperbolic tangent projection is used to carry out projection, and the shape of the topology optimized fin 105 and the optimal distribution of the fin 105 material are obtained. Wherein,

[0060] The Helmholtz filtering equation is expressed as:

[0061]

[0062] 0<θ s ≤1;

[0063] In the formula, θ f is the filtered fin 105 density, R min is the filtering radius, R min =0.35mm.

[0064] The Helmholtz filtering equation can reduce the dependence on the grid, reduce the grainy feeling of the figure, eliminate local details, make the fin 105 structure continuous, and ensure the feasibility of subsequent processing.

[0065] The variable density interpolation model is expressed as:

[0066]

[0067] In the formula, θ p represents the penalty factor, θ min represents the minimum penalty volume fraction, θ min =0.01, P simp represents the SIMP index, P simp =5.

[0068] The hyperbolic tangent projection function is expressed as:

[0069]

[0070] In the formula, γ represents the projection slope, and η represents the projection threshold.

[0071] The Helmholtz filter produces an intermediate state density, and the hyperbolic tangent projection can project the density to 0 or 1, making the filtered boundary clearer and avoiding numerical oscillation.

[0072] In this problem, the thermal conductivity, density, and specific heat capacity are involved, and the steady-state topology optimization of heat transfer only introduces a penalty factor for the thermal conductivity:

[0073] k (i) =k PCM +θ p (k Al -k PCM );

[0074] ρ (i) =ρ PCM +θ(ρ Al -ρ PCM );

[0075] c p(i) =c pPCM +θ(c pAl -c pPCM );

[0076] In the formula, k (i) represents the interpolated thermal conductivity, k PCM represents the thermal conductivity of the phase change material 104, k Al represents the thermal conductivity of the fin 105, ρ (i) represents the interpolated density, ρ PCM represents the density of the phase change material 104, ρ Al represents the density of the fin 105, c p(i) represents the interpolated specific heat capacity, c pPCM represents the specific heat capacity of the phase change material 104, c pAl represents the specific heat capacity of the fin 105. Local approximation is performed using the moving asymptote algorithm, and the result converges after 46 iterations.

[0077] It should be understood that the two-dimensional fin after topology optimization is stretched into a pseudo-three-dimensional fin in the normal direction and distributed on the outer surface of the side wall of the protrusion 106, and the topology-optimized tree-shaped structure fin 105 is beneficial to improve the heat conduction efficiency and temperature uniformity.

[0078] The fin with a tree-shaped branch shape not only improves the overall heat conduction efficiency, but also makes the phase change material melt uniformly, and enhances the convective heat transfer caused by melting. In addition, this structure has good mechanical properties, and the tree-shaped fin root can increase the structural strength of the protrusion 106. Through pseudo-three-dimensional stretching, the geometric characteristics can be accurately realized while reducing the processing difficulty.

[0079] In some other embodiments of the present application, the filled phase change material 104 can also include expanded graphite or a mixed phase change material 104 of paraffin and expanded graphite.

[0080] Figure 5 is an exploded view of a phase change thermal management packaging structure for a hypersonic vehicle conformal antenna provided by an embodiment of the present application. Please see Figures 4-5 In the phase change thermal management packaging structure 100 described above, further comprising: an upper aerogel 3 and a lower aerogel 4, respectively located on the upper surface and the lower surface of the packaging shell 2.

[0081] Specifically, the packaging shell 2 is made of aluminum alloy material, the upper surface is filled with the upper aerogel 3 for isolating friction aerodynamic heat, and the lower surface is provided with a mounting groove for filling the lower aerogel 4. The lower aerogel 4 can protect the phase change cold plate 1 from the influence of the upper temperature, avoid the melting of the internal phase change material 104, and also play a role in shock absorption between the phase change cold plate 1 and the array antenna.

[0082] The multi-layer heat dissipation structure adopted in the embodiment significantly improves the overall heat dissipation effect of the phase change thermal management packaging structure 100. The phase change cold plate 1 is the main heat dissipation component, the phase change material 104 filled in the internal phase change cold plate 1 is the main heat dissipation channel of the T / R component, which can absorb heat and keep the temperature stable, and the double-layer aerogel also plays a key role in heat insulation, which can prevent the transmission of friction aerodynamic heat to the phase change cold plate 1.

[0083] Figure 6 is a bottom view of the phase change cold plate provided by an embodiment of the present application, Figure 7 is a top view of the phase change cold plate provided by an embodiment of the present application. Optionally, please see Figure 4 、 6 -7, the base 101 further includes a plurality of through holes 108 penetrating through the lower surface of the groove in the protruding portion 106 and the lower surface of the base 101, which facilitates the positioning and installation of the radio frequency coaxial connector and the connection of the coaxial cable with the upper antenna. As shown in the figure, the plurality of through holes 108 are arranged to form a plurality of sub-arrays extending in a first direction and arranged in a second direction; in a direction perpendicular to the plane in which the phase change cold plate 1 is located, the orthographic projection of each sub-array is located within the orthographic projection of each strip-shaped hollow portion 103.

[0084] In addition, the phase change cold plate 1 can also be selected from an aluminum alloy material, the lower surface of which has a flange interface for fixing a connector flange, and the upper surface of which is conformal with the antenna and connected with the packaging shell 2. As can be seen, in the phase change thermal management packaging structure 100 described above, the phase change cold plate 1 does not need an additional support structure, can adapt to thermal expansion deformation, and maintains stable contact with the antenna, thereby achieving integrated design with the antenna structure. This completely conformal design can also reduce the occupied space in a limited space, thereby directly reducing the weight of the phase change cold plate 1 and improving the space and material utilization efficiency.

[0085] From the perspective of feasibility, the phase change cold plate 1 can be manufactured in two parts, a base 101 and a surface end cover 102. Considering that laser selective melting (SLM) has high forming precision and can better realize the shape of the tree-shaped structure of the fins 105, the SLM process is selected for additive manufacturing of the phase change cold plate 1. The specific method is as follows:

[0086] Step 1: Preheat the aluminum alloy powder that has not been dampened and check the oxygen content, set the laser power and scanning speed;

[0087] Step 2: Place the base 101 downward for printing, and the protruding part 107 and the fins 105 are integrally stretched and can be self-supported. In order to avoid the warping of the side wall surface, a zigzag support is designed on the side wall surface, which can ensure the support effect and facilitate the removal of the support in the later stage. The threaded hole is printed as a corresponding depth hole, and the hole is separately tapped in the later stage.

[0088] Step 3: Place the surface end cover 102 horizontally for printing, with the cylindrical surface upward. The round hole and the long slot 103 hole are perpendicular to the printing direction and do not need additional support. Remove the support from the processed parts, heat treatment, surface polishing, and precision machining of the mating surface to ensure the shape and position error.

[0089] Step 4: Fill the prepared phase change material 104 into the cavity multiple times and press it evenly.

[0090] Step 5: Align the base 101 and the surface end cover 102, and use vacuum brazing technology to tightly connect the entire phase change cold plate 1 to ensure the sealing property.

[0091] As can be seen from the above embodiments, the phase change thermal management packaging structure of the conformal antenna of a hypersonic vehicle has the following beneficial effects:

[0092] (1) The phase change thermal management packaging structure of the conformal antenna of a hypersonic vehicle provided by the present application includes a phase change cold plate and a packaging shell on the upper surface of the phase change cold plate. The phase change cold plate is designed to be conformal with the antenna, which can reduce the contact thermal resistance and has excellent heat dissipation advantages. In addition, the conformal cold plate provides additional mechanical support, the tightly fitted structure increases the stability of the entire structure, and can also meet the fastening requirements between components, thereby reducing the number of assembly parts and improving the reliability.

[0093] (2) The base and the surface end cover of the phase change cold plate jointly form a cavity, the cavity is filled with a phase change material and includes multiple protruding portions, and the outer surface of at least one side wall in each protruding portion is provided with a tree structure, which greatly improves the heat conduction effect. Compared with the way of using traditional heat dissipation fins, the overall heat transfer effect of the present application is better, and the occupied volume is small, which is conducive to improving the filling rate of the phase change material; compared with the heat pipe heat conduction mode, the present application avoids the low reliability caused by the complex installation structure, and effectively solves the problem of low phase change heat dissipation and heat conduction efficiency.

[0094] (3) For the conformal antenna in the hypersonic vehicle, the present application not only considers the heat dissipation problem of the conformal antenna itself, but also uses aerogel material for heat insulation design against friction aerodynamic heat, wherein the first layer of aerogel is located on the upper surface of the packaging shell, which can insulate the friction aerodynamic heat brought by the external environment, and the second layer of aerogel is located between the conformal cold plate and the array antenna, which not only can insulate heat, but also can play an important role in shock absorption, especially when facing mechanical impact or vibration, it can absorb and relieve impact load.

[0095] (4) The structure design of the conformal cold plate is flexible, which is manufactured by machining into two parts, the sealing property of the overall structure is ensured by vacuum brazing process, and the aluminum alloy and the phase change material can ensure light weight and high heat conduction capacity at the same time.

[0096] (5) The design of the strip-shaped hollow part and the through hole not only reduces the processing difficulty, but also improves the convenience of disassembly and assembly.

[0097] In the description of the present application, the description of the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In the present specification, the illustrative description of the above terms is not necessarily for the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in the present specification.

[0098] The above is a further detailed description of the present application in conjunction with specific preferred embodiments, and the specific implementation of the present application cannot be limited to these descriptions. For those skilled in the art, without departing from the concept of the present application, a number of simple deductions or substitutions can be made, which should be regarded as falling within the protection scope of the present application.

Claims

1. A phase change thermal management packaging structure for a hypersonic vehicle conformal antenna, characterized by, The application relates to a phase change cold plate and a packaging shell on the upper surface of the phase change cold plate, wherein the phase change cold plate and the packaging shell are conformal designs with an antenna. The phase change cold plate comprises a base and a surface end cover, the surface end cover comprises a plurality of strip-shaped hollow parts extending along a first direction and arranged along a second direction, the first direction is perpendicular to the second direction, the surface end cover is located above the base to form a cavity filled with a phase change material, the cavity further comprises a plurality of fins and a plurality of protruding parts, each protruding part comprises a long groove, and the orthographic projection of each strip-shaped hollow part is coincided with the orthographic projection of each long groove along the direction perpendicular to the plane of the phase change cold plate, the fins are located on the outer surface of at least one side wall of each protruding part. The base further comprises a plurality of through holes penetrating through the lower surface of the recess and the lower surface of the base, and the plurality of through holes are arranged to form a plurality of sub-arrays extending along the first direction and arranged along the second direction. The orthographic projection of each sub-array is located in the orthographic projection of each strip-shaped hollow part along the direction perpendicular to the plane of the phase change cold plate. The application further relates to an upper aerogel and a lower aerogel located on the upper surface and the lower surface of the packaging shell respectively.

2. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna of claim 1, wherein, The phase change material comprises paraffin, expanded graphite or a mixed phase change material of paraffin and expanded graphite. The fins are tree-shaped structures.

3. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna of claim 1, wherein, When the outer surfaces of two side walls of a protruding part both comprise fins, the fins on the outer surfaces of the two side walls are symmetrical about the protruding part.

4. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna of claim 1, wherein, The tree-shaped fins are obtained by optimization according to the following steps:

5. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna of claim 4, wherein, A target function is established to minimize the average temperature of the phase change material.

6. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna of claim 4, wherein, Based on the variable density interpolation model SIMP and the minimum temperature of the phase change material, the thermal conductivity of the phase change material is redefined by interpolation and a penalty factor, and density filtering smoothing is performed by combining a Helmholtz filtering equation, projection is performed in a hyperbolic tangent projection mode to obtain the optimal distribution of the fin shape and the fin material after topological optimization; wherein, The Helmholtz filtering equation is expressed as: ； ； wherein represents the volume of the cavity, represents the temperature of the phase change material, represents the minimum average temperature of the phase change material to be solved, represents the fin density, represents the volume fraction of the phase change material, ; The variable density interpolation model is expressed as: The hyperbolic tangent projection function is expressed as: ； ； wherein is the filtered fin density, is the filtered radius, ; The material of the phase change cold plate is an aluminum alloy. ； wherein represents a penalty factor, represents a minimum penalty volume fraction, , represents a SIMP index, ; ​ ； In the formula, denotes the projection slope, denotes the projection threshold.

7. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna of claim 1, wherein, ​

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