Phase change heat management packaging structure for conformal antenna of hypersonic flight vehicle

Abstract

The invention discloses a phase change heat management packaging structure for a conformal antenna of a hypersonic flight vehicle, and belongs to the technical field of conformal antennae, the phase change heat management packaging structure 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 and the packaging shell are conformal with the antenna, the contact heat resistance can be reduced, the conformal phase change cold plate provides additional mechanical support, and the packaging shell is not prone to deformation. The stability of the whole structure is improved; 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 to form a cavity filled with phase change materials, a plurality of fins and a plurality of protruding parts are further arranged in the cavity, each protruding part comprises a long groove, the orthographic projection of each strip-shaped hollow-out part coincides with the orthographic projection of the corresponding long groove in the direction perpendicular to the plane where the phase change cold plate is located, and the phase change cold plate is formed. The fins are located on the outer surface of at least one side wall in each protruding part, so that the filling rate of the phase change material can be increased, the occupied volume is reduced, and the heat conduction effect is improved.

Description

Technical Field

[0001] The present invention belongs to the technical field of conformal antennas, and in particular relates to a phase change thermal management packaging structure for a conformal antenna of a hypersonic aircraft. Background Art

[0002] With the development of antenna technology, conformal antennas can not only enhance the stealth capability of aircraft, but also improve the overall integration and aerodynamic performance compared to traditional planar antennas, so conformal antennas are crucial in hypersonic aircraft. However, as the integration of antennas continues to increase, the power density of T / R components (transceiver modules) is also gradually increasing, and heat is generated seriously during operation. Without effective thermal management methods, the antenna performance will be reduced, the life will be shortened, and even failures and damage will occur. Therefore, efficient thermal management of T / R components is not only the basis for ensuring their normal operation, but also the key to improving overall reliability.

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

[0004] At present, the most commonly used cold plate for thermal management of aircraft equipment is a flat cold plate, which has a single structure and shape and is difficult to adapt to the complex, multi-curved antenna shape. In addition, the flat cold plate cannot make full use of the space, and the volume required to fill the same mass of phase change material is large, which is not conducive to lightweighting. At the same time, it is difficult for the flat cold plate to fit the irregular surface of the heat source, and the heat dissipation area is limited, which will increase the local thermal resistance and reduce the thermal conductivity. It may cause hot spots to form in the heat source concentrated area, affecting the overall heat dissipation effect. In addition, the above-mentioned planar structure makes the heat diffusion path radial, resulting in uneven temperature between the edge area and the center temperature, and excessive temperature gradient, which reduces the life of the antenna.

[0005] In summary, the antennas in hypersonic vehicles have the characteristics of high heat flux density and complex and compact structure, and the use of flat cold plates to dissipate heat has little effect. Summary of the invention

[0006] In order to solve the above problems existing in the prior art, the present invention provides a phase change thermal management packaging structure for a conformal antenna of a hypersonic aircraft. The technical problem to be solved by the present invention is achieved through the following technical solutions:

[0007] The present invention 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, wherein the phase change cold plate and the packaging shell are both designed to conform to the antenna; wherein:

[0008] The phase change cold plate includes: a base and a surface end cover; the surface end cover 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 cover is located above the base to form a cavity filled with a phase change material, the cavity also includes a plurality of fins and a plurality of protrusions, each of the protrusions includes a long groove, along a direction perpendicular to the plane where the phase change cold plate is located, the orthographic projections of each strip-shaped hollow portion coincide with the orthographic projections of each long groove, and the fin is located on the outer surface of at least one side wall of each of the protrusions.

[0009] In one embodiment of the present invention, it further comprises: an upper aerogel layer and a lower aerogel layer, which are respectively located on the upper surface and the lower surface of the packaging shell.

[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 are in a tree-like structure.

[0012] In one embodiment of the present invention, when both side wall outer surfaces of a certain protrusion include fins, the fins on the two side wall outer surfaces 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 raised portion 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 the first direction and arranged along the second direction;

[0015] Along a direction perpendicular to the plane where the phase change cold plate is located, the orthographic projection of each sub-column 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 structure are optimized according to the following steps:

[0017] With the goal of minimizing the average temperature of the phase change material, an objective function is established:

[0018]

[0019] Wherein, 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, θ s represents the fin density, 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 the interpolation method and the penalty factor, and the density filtering and smoothing are performed in combination with the Helmholtz filtering equation. The hyperbolic tangent projection is used for projection to obtain the topologically optimized fin shape and the optimal distribution of the fin material; wherein,

[0021] The Helmholtz filtering equation is expressed as:

[0022]

[0023] 0<θ s ≤1;

[0024] In the formula, θ f is the fin density after filtration, R min is the filter 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] Where γ represents the projection slope and η represents the projection threshold.

[0031] In one embodiment of the present invention, the phase change cold plate is made of aluminum alloy.

[0032] Compared with the prior art, the present invention has the following beneficial effects:

[0033] (1) The present invention provides a phase change thermal management packaging structure of a conformal antenna for 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 is conformally designed with the antenna to reduce contact thermal resistance and has great heat dissipation advantages. The conformal cold plate provides additional mechanical support, and the tightly fitting 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 reliability.

[0034] (2) The base and the surface end cover of the phase change cold plate together form a cavity, which is filled with phase change material and includes a plurality of protrusions. The outer surface of at least one side wall of each protrusion is provided with a tree-like structure, which greatly improves the thermal conductivity. Compared with the method of using traditional heat sink fins, the overall heat transfer effect of the present invention is better, and the volume occupied is small, which is conducive to improving the filling rate of the phase change material; compared with the heat pipe heat conduction method, the present invention avoids the low reliability caused by the complex installation structure, and effectively solves the problem of low heat conduction efficiency of phase change heat dissipation.

[0035] (3) With respect to conformal antennas in hypersonic vehicles, the present invention not only takes into account the heat dissipation problem of the antennas themselves, but also uses aerogel materials for heat insulation design to address frictional aerodynamic heat. The first layer of aerogel is located on the upper surface of the packaging shell, which can isolate the frictional aerodynamic heat brought by the external environment. The second layer of aerogel is located between the conformal cold plate and the array antenna, which can not only provide heat insulation, but also play an important role in shock absorption, especially in the face of mechanical shock or vibration, and can absorb and alleviate the impact load.

[0036] (4) The conformal cold plate has a flexible structural design and is manufactured in two parts, the upper and lower parts, by machining. The sealing of the overall structure is ensured by the vacuum brazing process. The use of aluminum alloy and phase change material can ensure both lightweight and high thermal conductivity.

[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 invention will be further described in detail below with reference to the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

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

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

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

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

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

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

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

[0046] The present invention is further described in detail below with reference to specific embodiments, but the embodiments of the present invention 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 invention, Figure 2 is a schematic diagram of the structure of a phase change cold plate provided in an embodiment of the present invention, Figure 3 is an internal top view of a phase change cold plate provided in an embodiment of the present invention, Figure 4 FIG. 1 is a cross-sectional view of a phase change thermal management packaging structure for a conformal antenna of a hypersonic aircraft provided by an embodiment of the present invention. Figure 1-4 As shown, an embodiment of the present invention provides a phase change thermal management packaging structure 100 for a conformal antenna of a hypersonic aircraft, comprising: a phase change cold plate 1 and a packaging shell 2 located on the upper surface of the phase change cold plate 1, wherein the phase change cold plate 1 and the packaging shell 2 are both designed to conform to the antenna; wherein,

[0048] The phase change cold plate 1 includes: a base 101 and a surface end cover 102; the surface end cover 102 includes a plurality of strip-shaped hollow portions 103 extending along a first direction and arranged along a second direction, and 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, and the cavity also includes a plurality of fins 105 and a plurality of protrusions 106, each protrusion 106 includes a long groove 107, and along a direction perpendicular to the plane where the phase change cold plate 1 is located, the orthographic projection of each strip-shaped hollow portion 103 coincides with the orthographic projection of each long groove 107, and the fin 105 is located on the outer surface of at least one side wall of each protrusion 106.

[0049] Specifically, in the above-mentioned phase change thermal management packaging structure 100, the phase change cold plate 1 and the packaging shell 2 are both conformally designed with the antenna, so that the phase change cold plate 1 can be accurately fitted 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 heat can be more efficiently transferred from the heat source to the phase change cold plate 1; at the same time, it can also improve the overall temperature uniformity, avoid the generation of local hot spots, and achieve better heat dissipation performance.

[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 portions 103 extending along a first direction and arranged along a second direction, the surface end cover 102 and the base 101 form a cavity, and a plurality of protrusions 106 are provided in the cavity, each protrusion 106 extends along the first direction, and the plurality of protrusions 106 are arranged along the second direction, such as Figure 2-3 As shown, each raised portion 106 includes a long groove 107, that is, the middle portion of each raised portion 106 is concave, and along the direction perpendicular to the plane where the phase change cold plate 1 is located, the orthographic projection of each strip-shaped hollow portion 103 coincides with the orthographic projection of each long groove 107, that is, the strip-shaped hollow portion 103, the raised portion 106 and the long groove 107 in the raised portion 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 phase change latent heat 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 will cause uneven temperature distribution inside the paraffin. To solve this problem, the phase change thermal management packaging structure 100 provided by the present invention introduces fins 105 in the cavity to increase the heat dissipation area and increase 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 outer surface of each protrusion 106 is provided with fins 105 to improve thermal conductivity and temperature uniformity, and the fins 105 may be in a tree-like structure. It should be noted that when both side wall outer surfaces of a protrusion 106 include fins 105, the fins 105 on the two side wall outer surfaces are symmetrical about the protrusion 106 to achieve efficient conjugate heat transfer.

[0053] It should be understood that the traditional fins 105 are designed with a uniform geometric shape. This structure cannot fully utilize the heat distribution of the heat source, resulting in lower local heat conduction efficiency than other areas. It is often manufactured in standard sizes, which may result in material waste or significant weight gain of the structure. 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 materials based on the heat dissipation goals and heat loads, so as to reduce the overall weight while achieving the best heat dissipation performance.

[0054] In this embodiment, the tree-like structured fins 105 are optimized according to the following steps:

[0055] S1. With the goal of minimizing the average temperature of the phase change material 104, establish an objective function:

[0056]

[0057] Wherein, 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, and θ s represents the density of fin 105, represents the volume fraction of the phase change material 104,

[0058] In this step, by optimizing the objective function, it can be clarified that the goal of the topology optimization of the fin 105 is to minimize the temperature of the phase change material 104 , and only with this goal can subsequent filtering and projection processing be performed, and the constraint condition is 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 obtained by solution, the thermal conductivity of the phase change material 104 is redefined by interpolation method and penalty factor, and density filtering and smoothing are performed in combination with the Helmholtz filtering equation. The hyperbolic tangent projection is used for projection to obtain the topologically optimized shape of the fin 105 and the optimal distribution of the fin 105 material. Among them,

[0060] The Helmholtz filtering equation is expressed as:

[0061]

[0062] 0<θ s ≤1;

[0063] In the formula, θ f is the density of the fin 105 after filtration, R min is the filter radius, R min =0.35mm.

[0064] The Helmholtz filtering equation can reduce the reliance on the grid and the granularity of the graphics, thereby eliminating local details and making the fin 105 structure continuous, thereby ensuring 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] Where γ represents the projection slope and η represents the projection threshold.

[0071] After Helmholtz filtering, intermediate state density will be generated. Using hyperbolic tangent projection, the density can be projected to 0 or 1, making the boundary after filtering clearer and avoiding numerical oscillation.

[0072] This problem involves thermal conductivity, density, and specific heat capacity. Steady-state topology optimization heat transfer only introduces a penalty factor for 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] Where: 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 density after interpolation, 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. The moving asymptote algorithm is used for local approximation, and the result converges after 46 iterations.

[0077] It should be understood that the topologically optimized two-dimensional fins are stretched into pseudo three-dimensional fins in the normal direction and distributed on the outer surface of the side wall of the protrusion 106. The topologically optimized tree-like structure fins 105 are beneficial to improving thermal conductivity and temperature uniformity.

[0078] The tree-shaped fins can not only improve the overall heat conduction efficiency and make the phase change material melt evenly, but also enhance the convective heat transfer caused by melting; in addition, this structure has good mechanical properties, and the root of the tree-shaped fins can increase the structural strength of the protrusion 106. Through pseudo-three-dimensional stretching, the geometric features can be accurately realized while reducing the processing difficulty.

[0079] In some other embodiments of the present application, the filled phase change material 104 may 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 aircraft conformal antenna provided by an embodiment of the present invention. Figure 4-5 In the above-mentioned phase change thermal management packaging structure 100, it also includes: an upper aerogel layer 3 and a lower aerogel layer 4, which are 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, and the upper surface is filled with an upper layer of aerogel 3 to isolate frictional aerodynamic heat. An installation groove is opened on the lower surface to fill the lower layer of aerogel 4. The lower layer of aerogel 4 can protect the phase change cold plate 1 from being affected by the upper temperature, avoid the internal phase change material 104 from melting, and can also play a shock-absorbing role between the phase change cold plate 1 and the array antenna.

[0082] The multi-layer heat dissipation structure adopted in this embodiment significantly improves the overall heat dissipation effect of the phase change thermal management packaging structure 100, wherein the phase change cold plate 1 is the main heat dissipation component, and the phase change material 104 filled inside serves as the main heat dissipation channel of the T / R component, which can absorb heat and maintain temperature stability. The double-layer aerogel also plays a key role in thermal insulation and can prevent frictional aerodynamic heat from being transferred to the phase change cold plate 1.

[0083] Figure 6 is a bottom view of a phase change cold plate provided in an embodiment of the present invention, Figure 7 is a top view of a phase change cold plate provided by an embodiment of the present invention. Figure 4 , 6 -7, the base 101 also includes a plurality of through holes 108 that penetrate the lower surface of the groove in the raised portion 106 and the lower surface of the base 101, which facilitates the positioning and installation of the RF 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-columns extending along the first direction and arranged along the second direction; along the direction perpendicular to the plane where the phase change cold plate 1 is located, the orthographic projection of each sub-column is located in the orthographic projection of each strip-shaped hollow portion 103.

[0084] In addition, the phase change cold plate 1 can also be made of aluminum alloy material, with a flange interface on its lower surface for fixing the connector flange, and the upper surface conforms to the antenna and is connected to the packaging shell 2. It can be seen that in the above-mentioned phase change thermal management packaging structure 100, the phase change cold plate 1 does not require an additional support structure, while adapting to thermal expansion deformation and maintaining stable contact with the antenna, realizing an integrated design with the antenna structure. This fully fitted design can also reduce the occupied space within a limited space, thereby directly reducing the weight of the phase change cold plate 1 and improving the efficiency of space and material use.

[0085] From the perspective of feasibility, the phase change cold plate 1 can be manufactured by dividing it into two parts: a base 101 and a surface end cap 102. Considering that the selective laser melting (SLM) molding precision is high and can better realize the appearance of the tree-like fin 105, the SLM process additive manufacturing method is selected to process the phase change cold plate 1. The specific method is as follows:

[0086] Step 1: preheat the aluminum alloy powder that is not damp, check the oxygen content, and set the laser power and scanning speed;

[0087] Step 2: Print the base 101 downward. The raised part 107 and the fin 105 are stretched as one piece and can be self-supporting. To avoid warping of the side wall, a serrated support is designed for the side wall, which not only ensures the support effect but also facilitates removal later. The threaded holes are printed as corresponding depth holes, which will be tapped separately later.

[0088] Step 3: Print the surface end cap 102 flatly with the cylindrical surface facing up. The circular hole and the long slot 103 are perpendicular to the printing direction, and no additional support is required. The processed parts are removed from the support, heat treated, surface polished, and the mating surfaces are finely processed to ensure the shape and position errors.

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

[0091] It can be seen from the above embodiments that the beneficial effects of the present invention are:

[0092] (1) The present invention provides a phase change thermal management packaging structure of a conformal antenna for 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 is conformally designed with the antenna to reduce contact thermal resistance and has great heat dissipation advantages. The conformal cold plate provides additional mechanical support, and the tightly fitting 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 reliability.

[0093] (2) The base and the surface end cover of the phase change cold plate together form a cavity, which is filled with phase change material and includes a plurality of protrusions. The outer surface of at least one side wall of each protrusion is provided with a tree-like structure, which greatly improves the thermal conductivity. Compared with the method of using traditional heat sink fins, the overall heat transfer effect of the present invention is better, and the volume occupied is small, which is conducive to improving the filling rate of the phase change material; compared with the heat pipe heat conduction method, the present invention avoids the low reliability caused by the complex installation structure, and effectively solves the problem of low heat conduction efficiency of phase change heat dissipation.

[0094] (3) With respect to conformal antennas in hypersonic vehicles, the present invention not only takes into account the heat dissipation problem of the antennas themselves, but also uses aerogel materials for heat insulation design to address frictional aerodynamic heat. The first layer of aerogel is located on the upper surface of the packaging shell, which can isolate the frictional aerodynamic heat brought by the external environment. The second layer of aerogel is located between the conformal cold plate and the array antenna, which can not only provide heat insulation, but also play an important role in shock absorption, especially in the face of mechanical shock or vibration, and can absorb and alleviate the impact load.

[0095] (4) The conformal cold plate has a flexible structural design and is manufactured in two parts, the upper and lower parts, by machining. The sealing of the overall structure is ensured by the vacuum brazing process. The use of aluminum alloy and phase change material can ensure both lightweight and high thermal conductivity.

[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 invention, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" etc. 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 invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine different embodiments or examples described in this specification.

[0098] The above contents are further detailed descriptions of the present invention in combination with specific preferred embodiments, and it cannot be determined that the specific implementation of the present invention is limited to these descriptions. For ordinary technicians in the technical field to which the present invention belongs, several simple deductions or substitutions can be made without departing from the concept of the present invention, which should be regarded as falling within the protection scope of the present invention.

Claims

1. A phase change thermal management packaging structure for a hypersonic vehicle conformal antenna, characterized in that: include: A phase change cold plate and a packaging shell located on the upper surface of the phase change cold plate, wherein the phase change cold plate and the packaging shell are both designed to conform to the antenna; wherein, The phase change cold plate includes: a base and a surface end cover; the surface end cover 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 cover is located above the base to form a cavity filled with a phase change material, the cavity also includes a plurality of fins and a plurality of protrusions, each of the protrusions includes a long groove, along a direction perpendicular to the plane where the phase change cold plate is located, the orthographic projections of each strip-shaped hollow portion coincide with the orthographic projections of each long groove, and the fin is located on the outer surface of at least one side wall of each of the protrusions.

2. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna according to claim 1, characterized in that: Also includes: The upper aerogel layer and the lower aerogel layer are respectively located on the upper surface and the lower surface of the packaging shell.

3. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna according to claim 1, characterized in that: The phase change material includes: paraffin wax, expanded graphite or a mixed phase change material of paraffin wax and expanded graphite.

4. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna according to claim 1, characterized in that: The fins are in a tree-like structure.

5. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna according to claim 4, characterized in that: When both side wall outer surfaces of a certain protrusion include fins, the fins on the two side wall outer surfaces are symmetrical about the protrusion.

6. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna according to claim 2, characterized in that: The base also includes a plurality of through holes penetrating the lower surface of the groove in the raised portion and the lower surface of the base.

7. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna according to claim 6, characterized in that: The plurality of through holes are arranged to form a plurality of sub-rows extending along the first direction and arranged along the second direction; Along a direction perpendicular to the plane where the phase change cold plate is located, the orthographic projection of each sub-column is located within the orthographic projection of each of the strip-shaped hollow portions.

8. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna according to claim 4, characterized in that: The fins of the tree structure are optimized according to the following steps: With the goal of minimizing the average temperature of the phase change material, an objective function is established: Wherein, 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, θ s represents the fin density, represents the volume fraction of the phase change material, 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 the interpolation method and the penalty factor, and the density filtering and smoothing are performed in combination with the Helmholtz filtering equation. The hyperbolic tangent projection is used for projection to obtain the topologically optimized fin shape and the optimal distribution of the fin material; wherein, The Helmholtz filtering equation is expressed as: 0<θ s ≤1; In the formula, θ f is the fin density after filtration, R min is the filter radius, R min =0.35mm; The variable density interpolation model is expressed as: In the formula, θ p represents the penalty factor, θ min represents the minimum penalty volume fraction, θ min =0.01, P simp represents SIMP index, P simp =5; The hyperbolic tangent projection function is expressed as: Where γ represents the projection slope and η represents the projection threshold.

9. The phase change thermal management packaging structure for a hypersonic vehicle conformal antenna according to claim 1, characterized in that: The material of the phase change cold plate is aluminum alloy.

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