Pump-driven two-phase fluid loop for high-temperature heat dissipation in fixed plane area and design method

Abstract

The invention relates to the technical field of thermal protection of high-speed aircrafts, in particular to a pump-driven two-phase fluid loop for high-temperature heat dissipation in a fixed plane area and a design method. The pump-driven two-phase fluid loop for high-temperature heat dissipation in the fixed plane area comprises a pipeline system, a condenser, a liquid storage container and a power pump. The pipeline system comprises a main loop and a plurality of heat dissipation branches; the heat dissipation branches are arranged in the corresponding gaps; and the two ends of the main loop are communicated with the plurality of heat dissipation branches through multi-stage branches. Under the action of the power pump, the cooling working medium in the liquid storage container is pumped into each heat dissipation branch of the multi-stage branches; in the heat dissipation branch, the cooling working medium completes heat exchange, at least part of the liquid-phase cooling working medium is converted into a gas phase in the process, then the gas-phase and liquid-phase mixed cooling working medium returns to the main loop and enters the condenser for heat exchange and cooling, finally, the cooling working medium is completely converted into the liquid-phase cooling working medium, and the cooling working medium can be evenly distributed in a target area. The cooling effect is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of high-speed aircraft thermal protection, and in particular to a pump-driven two-phase fluid circuit for dissipating high-temperature heat in a fixed plane area and a design method thereof. Background Art

[0002] Hypersonic vehicles are aircraft capable of traveling at speeds exceeding Mach 5 within the atmosphere or near-space. During flight, the outer walls of hypersonic vehicles can rapidly heat up to extremely high temperatures due to aerodynamic heating. To protect internal structures from high temperatures, a multi-layered thermal protection system is typically employed. These measures effectively reduce the temperature transmitted to the structural layers, bringing it within a safe range that the structural materials can withstand. By optimizing the configuration and design of the thermal protection system, the overall weight can be reduced and performance improved while ensuring the safety of the aircraft structure. This design ensures that hypersonic vehicles can operate stably under extreme conditions. Summary of the Invention

[0003] The main purpose of the present invention is to provide a pump-driven two-phase fluid circuit for dissipating high-temperature heat from a fixed plane area, so as to optimize the thermal protection system of a hypersonic aircraft and protect the internal structure of the aircraft from damage by high temperature; the present invention also provides a design method for designing the above-mentioned pump-driven two-phase fluid circuit for dissipating high-temperature heat from a fixed plane area.

[0004] To achieve the above objectives, an embodiment of the present invention provides a pump-driven two-phase fluid circuit for dissipating high-temperature heat from a fixed planar area, which is arranged in a multi-layer thermal protection structure of an aircraft, wherein the multi-layer thermal protection structure includes a thermal insulation layer, a thermal conductive layer, and a composite material structure layer; the composite material structure layer has a plurality of spaced-apart gaps;

[0005] A pump-driven two-phase fluid circuit for dissipating high-temperature heat from a fixed plane area comprises: a piping system, a condenser, a liquid storage container, and a power pump; the piping system comprises a main circuit and a plurality of heat dissipation branches, the condenser, the liquid storage container, and the power pump being sequentially arranged on the main circuit;

[0006] The heat dissipation branches are arranged in a one-to-one correspondence with the gaps, and the heat dissipation branches are arranged in the corresponding gaps; the two ends of the main circuit are connected to a plurality of the heat dissipation branches through multi-level branches.

[0007] Another embodiment of the present invention further provides a design method for designing the aforementioned pump-driven two-phase fluid circuit for high-temperature heat dissipation in a fixed plane area;

[0008] The design method comprises the steps of:

[0009] S1, taking the cross-sectional area of ​​the gaps in the composite material structure layer as the cross-sectional area A0 of the preset heat dissipation branch, and determining the number n of the heat dissipation branches based on the number of gaps in the composite material structure layer;

[0010] S2, based on the cross-sectional area A0 of the preset heat dissipation branch and the number n of heat dissipation branches, obtain the volume V of the main circuit and the heat dissipation branch 外 ;

[0011] S3, based on the volume V of the main circuit and the heat dissipation main circuit 外 Get the volume V of the liquid storage container;

[0012] S4, obtaining the filling amount M of the cooling medium based on the volume V of the liquid storage container;

[0013] S5, comparing the charging amount M of the cooling medium in step S4 with the carrying capacity of the aircraft to obtain a comparison result;

[0014] S6. Adjust the cross-sectional area A0 of the preset heat dissipation branch based on the comparison result of step S5. When the cross-sectional area A0 of the preset heat dissipation branch changes, repeat steps S2 to S5 until the charging amount M of the cooling medium meets the carrying capacity of the aircraft, and obtain the cross-sectional area A of the heat dissipation branch.

[0015] Furthermore, the steps include:

[0016] S7, selecting a power pump based on the volume V of the liquid storage container and the carrying capacity of the aircraft;

[0017] S8, obtaining a flow resistance ΔP of the pipeline system based on a cross-sectional area A of the heat dissipation branch, and comparing the flow resistance ΔP of the pipeline system with a maximum flow resistance that can be overcome by the power pump;

[0018] S9 , adjusting the number of parallel heat dissipation branches based on the comparison result of step S8 , and repeating step S8 until the flow resistance ΔP of the pipeline system meets the maximum flow resistance that the power pump can overcome.

[0019] Furthermore, the pipeline system further includes a first branch section and a second branch section connecting the main circuit and the heat dissipation branch;

[0020] Step S8 also includes the steps of: obtaining the flow resistance ΔP1 of the main circuit, the flow resistance ΔP2 of any one of the heat dissipation branches, the flow resistance ΔP3 of the longest branch in the first branch segment, and the flow resistance ΔP4 of the longest branch in the second branch segment based on the cross-sectional area A of the heat dissipation branch, and summing ΔP1, ΔP2, ΔP3, and ΔP4 to obtain the flow resistance ΔP of the pipeline system.

[0021] Furthermore, step S9 also includes the following steps: when the comparison result in step S8 is that the flow resistance ΔP of the pipeline system is greater than the maximum flow resistance that the power pump can overcome, adjust the number of parallel heat dissipation branches, and repeat step S8 until the flow resistance ΔP of the pipeline system meets the maximum flow resistance that the power pump can overcome.

[0022] Furthermore, in step S8, adjusting the number of heat dissipation branches includes: reducing the length of some of the heat dissipation branches connected in series to increase the number of heat dissipation branches connected in parallel.

[0023] Furthermore, step S6 also includes the following steps: when the comparison result in step S5 is that the filling amount M of the cooling medium is greater than the carrying capacity of the aircraft, reducing the cross-sectional area A0 of the heat dissipation branch to reduce the filling amount M of the cooling medium, and repeating steps S2-S5 until the filling amount M of the cooling medium is consistent with the carrying capacity of the aircraft, and obtaining the cross-sectional area A of the heat dissipation branch.

[0024] Furthermore, step S3 includes:

[0025] S31, determining a value range of the volume V of the liquid storage container based on the following formula:

[0026] S31, determining a value range of the volume V of the liquid storage container based on the following formula:

[0027] M≤0.9×(V+V 外 )×, at temperature T H Under working conditions;

[0028] At temperature T L Under working conditions;

[0029] Under the design working temperature T condition;

[0030] V 外 =V 外1 +V 外2 ;

[0031]

[0032] S32: Determine the minimum value of the value range of V as the volume V of the liquid storage container.

[0033] Furthermore, step S3 further includes:

[0034] Get T H and T L .

[0035] Furthermore, the cross-sectional area of ​​the main circuit is the sum of the cross-sectional areas of the heat dissipation branches.

[0036] Beneficial effects of the present invention:

[0037] The present invention provides a pump-driven two-phase fluid circuit for dissipating high-temperature heat from a fixed plane area. The circuit is arranged in a multi-layer thermal protection structure of an aircraft, wherein the multi-layer thermal protection structure includes a heat-insulating layer, a heat-conducting layer, and a composite material structural layer. The composite material structural layer has a plurality of spaced-apart gaps. The pump-driven two-phase fluid circuit for dissipating high-temperature heat from a fixed plane area includes a piping system, a condenser, a liquid storage container, and a power pump. The piping system includes a main circuit and a plurality of heat dissipation branches. The condenser, the liquid storage container, and the power pump are sequentially arranged on the main circuit. The heat dissipation branches are arranged in a one-to-one correspondence with the gaps, and the heat dissipation branches are arranged in the corresponding gaps. The two ends of the main circuit are connected to the plurality of heat dissipation branches through multi-stage branches. Under the action of the power pump, the cooling medium in the liquid storage container is pumped into each heat dissipation branch of the multi-stage branch. In the heat dissipation branch, the cooling medium completes heat exchange, and at least part of the liquid phase of the cooling medium is converted to the gas phase during this process. Subsequently, the mixed gas and liquid phase cooling medium returns to the main circuit and enters the condenser for heat exchange and cooling, and is finally completely converted to the liquid phase of the cooling medium. The cooling medium can be evenly distributed in the target area to improve the cooling effect. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the specific embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0039] Figure 1 A schematic structural diagram of a pump-driven two-phase fluid circuit for dissipating high-temperature heat in a fixed plane area provided by an embodiment of the present invention.

[0040] Icon: 100-condenser;

[0041] 200-liquid storage container;

[0042] 300-power pump;

[0043] 400-main circuit;

[0044] 600-first branch segment;

[0045] 700-Second branch section. DETAILED DESCRIPTION

[0046] To make the objectives, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings herein can be arranged and designed in various different configurations.

[0047] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention as claimed, but rather merely represents selected embodiments of the present invention. All other embodiments derived by persons of ordinary skill in the art based on the embodiments of the present invention without creative effort shall fall within the scope of protection of the present invention.

[0048] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, it does not need to be further defined or explained in subsequent drawings.

[0049] In the description of the present invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" and the like indicate positions or locations based on the positions shown in the accompanying drawings, or the positions or locations in which the inventive product is typically placed when in use. These terms are intended solely to facilitate the description of the present invention and to simplify the description, and are not intended to indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. Furthermore, the terms "first," "second," and "third," etc., are used solely to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0050] Furthermore, terms such as "horizontal," "vertical," and "overhanging" do not necessarily imply that a component must be absolutely horizontal or overhanging, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but rather that it can be slightly tilted.

[0051] In the description of the present invention, it should also be noted that, unless otherwise expressly specified or limited, the terms "disposed," "installed," "connected," and "connected" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; they may refer to mechanical connections or electrical connections; they may refer to direct connections or indirect connections through an intermediate medium; and they may refer to internal communication between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention based on the specific circumstances.

[0052] The following embodiments of the present invention are described in detail with reference to the accompanying drawings. In the absence of conflict, the following embodiments and features in the embodiments may be combined with each other.

[0053] like Figure 1 As shown, one embodiment of the present invention provides a pump-driven two-phase fluid circuit for dissipating high-temperature heat from a fixed plane area, which is arranged at the multi-layer thermal protection structure of an aircraft. The multi-layer thermal protection structure of the aircraft includes a thermal insulation layer, a thermal conductive layer, and a composite material structure layer. The thermal insulation layer, the thermal conductive layer, and the composite material structure layer are stacked in sequence from the outside to the inside, and the composite material structure layer has a plurality of spaced gaps, and each gap extends in the same direction, that is, has the same length. The pump-driven two-phase fluid circuit for dissipating high-temperature heat from a fixed plane area includes a pipeline system, a condenser 100, a liquid storage container 200, and a power pump 300. The pipeline system includes a main circuit 400 and several heat dissipation branches. The condenser 100, the liquid storage container 200, and the power pump 300 are sequentially arranged on the main circuit 400. The heat dissipation branches are preferably connected in parallel and connected to the main circuit 400 through a multi-stage branching method. The liquid storage container 200 is used to store the cooling medium for cooling, the power pump 300 is used to provide power for the flow of the cooling medium, and the condenser 100 is used to cool the gas phase cooling medium into the liquid phase. The heat dissipation branches correspond one-to-one with the gaps in the composite material structural layers, and the heat dissipation branches are arranged in the corresponding gaps. Under the action of the power pump 300, the cooling medium in the liquid storage container 200 is pumped into each heat dissipation branch of the multi-stage branch; in the heat dissipation branch, the cooling medium completes heat exchange, and at least part of the liquid phase cooling medium is converted into the gas phase in this process. Subsequently, the cooling medium mixed with the gas phase and the liquid phase returns to the main circuit 400 and enters the condenser 100 for heat exchange and cooling, and finally all of it is converted into the liquid phase cooling medium. Through the above structure, the cooling medium can be evenly distributed in the target area, improving the cooling effect.

[0054] Another embodiment of the present invention further provides a design method for designing the aforementioned pump-driven two-phase fluid circuit for dissipating high-temperature heat in a fixed plane area.

[0055] The design method provided by the embodiment of the present invention includes the following steps:

[0056] S1, taking the cross-sectional area of ​​the gaps in the composite material structure layer as the cross-sectional area A0 of the heat dissipation branch, and determining the number n of the heat dissipation branches based on the number of gaps in the composite material structure layer;

[0057] S2, based on the cross-sectional area A0 of the heat dissipation branch and the number n of heat dissipation branches, obtain the volume V of the main circuit and the heat dissipation branch 外 ;

[0058] S3, based on the volume V of the main circuit and the heat dissipation main circuit 外 Get the volume V of the liquid storage container;

[0059] S4, obtaining the filling amount M of the cooling medium based on the volume V of the liquid storage container;

[0060] S5, comparing the charging amount M of the cooling medium in step S4 with the carrying capacity of the aircraft to obtain a comparison result;

[0061] S6, based on the comparison result of step S5, adjust the cross-sectional area A0 of the heat dissipation branch; and when the cross-sectional area A0 of the heat dissipation branch changes, repeat steps S2-S5 until the filling amount M of the cooling medium meets the carrying capacity of the aircraft, and the cross-sectional area A of the heat dissipation branch is obtained.

[0062] The design method provided in this embodiment first uses the cross-sectional area of ​​the gaps in the composite material structure layer as the cross-sectional area A0 of the preset heat dissipation branch, and determines the number n of heat dissipation branches based on the number of gaps in the composite material structure layer. Since the length dimension of the composite material structure layer is known, it can be specifically obtained by measurement. In this way, the volume V of the main circuit 400 and the heat dissipation branch can be obtained based on the cross-sectional area A0 of the preset heat dissipation branch and the number of heat dissipation branches. 外 , where the cross-sectional area of ​​the main loop 400 is the sum of the cross-sectional areas of each heat dissipation branch, and the length of the main loop 400 is determined by the space in the aircraft for arranging the above-mentioned pump-driven two-phase fluid circuit for dissipating high-temperature heat from the fixed plane area. The volumes of the first branch segment 600 and the second branch segment 700 mentioned below are calculated based on the cross-sectional area of ​​the main loop 400, and the length of the first branch segment 600 and the second branch segment 700 is the shortest straight-line distance between the main loop 400 and the heat dissipation branch.

[0063] Get V 外 Then the volume of the liquid storage container can be calculated. Specifically, step S3 includes:

[0064] S31, determining a value range of the volume V of the liquid storage container based on the following formula:

[0065] At temperature T H Under working conditions;

[0066] At temperature T L Under working conditions;

[0067] Under the design working temperature T condition;

[0068] V 外 =V 外1 +V 外2 ;

[0069]

[0070] Where V 外 is the volume of the piping system;

[0071] V 外1 is the volume of the single-phase part in the piping system;

[0072] V 外2 is the volume of the two-phase part in the piping system;

[0073] is the average density of the two-phase flow;

[0074] At temperature T H The density of the liquid phase under the working conditions;

[0075] At temperature T H The density of the gas phase under the working conditions;

[0076] At temperature T L The density of the liquid phase under the working conditions;

[0077] At temperature T L The density of the liquid phase under the working conditions;

[0078] ρ T-0.5ΔT，l is the density of the liquid phase at temperature T-0.5ΔT;

[0079] ε is the dryness of the gas-liquid two-phase flow.

[0080] T H is the upper temperature limit of the operating range, T L is the temperature lower line of the working range, T is the design working temperature, and the above is obtained based on actual test results; the phase change temperature is T, the liquid inlet subcooling is ΔT, and the average temperature of the liquid single-phase section is T-0.5ΔT.

[0081] S32: Determine the minimum value of the value range of V as the volume V of the liquid storage container.

[0082] Optionally, in this embodiment, the liquid storage container 200 is an ellipsoidal container with a wall thickness of 1 mm and a material of titanium alloy. After determining the volume of the liquid storage container 200, the filling amount of the cooling medium in the liquid storage container 200 can be obtained, and the filling amount of the cooling medium is compared with the mass of the cooling medium that can be carried in the aircraft. If the filling amount of the cooling medium is less than the mass of the cooling medium that can be carried by the aircraft, there is no need to adjust the cross-sectional area A0 of the preset heat dissipation branch, that is, the cross-sectional area of ​​the gap can be used as the cross-sectional area A of the heat dissipation branch; if the filling amount of the cooling medium is greater than the mass of the cooling medium that can be carried by the aircraft, it is necessary to adjust the cross-sectional area A0 of the preset heat dissipation mass, and repeat the above steps after adjustment for verification, through continuous adjustment and verification, until the filling amount M of the cooling medium is less than the mass of the cooling medium that can be carried by the aircraft, the cross-sectional area A of the heat dissipation mass is obtained.

[0083] It should be noted that, along the flow direction of the cooling medium, the cooling medium is in liquid phase from the condenser 100 to the heat dissipation branch, and is a mixture of gas phase and liquid phase in the rest of the position.

[0084] Furthermore, the design method provided by the embodiment of the present invention further includes the steps of:

[0085] S7, selecting a power pump based on the volume V of the liquid storage container and the carrying capacity of the aircraft;

[0086] S8, obtaining a flow resistance ΔP of the pipeline system based on a cross-sectional area A of the heat dissipation branch, and comparing the flow resistance ΔP of the pipeline system with a maximum flow resistance that can be overcome by the power pump;

[0087] S9 , adjusting the number of parallel branches of the heat dissipation branch based on the comparison result of step S8 , and repeating step S8 until the flow resistance ΔP of the pipeline system meets the maximum flow resistance that the power pump can overcome.

[0088] In this embodiment, after the cross-sectional area A of the heat dissipation branch is determined, the volume V of the liquid storage container 200 is also determined accordingly. Subsequently, the power pump 300 is selected based on the volume V of the liquid storage container 200 and the aircraft's carrying capacity. After the power pump 300 is determined, the flow resistance ΔP of the piping system is calculated based on the parameters of the power pump 300 and the cross-sectional area A of the heat dissipation mass. This flow resistance ΔP is then compared with the maximum flow resistance that the power pump 300 can overcome to determine whether the power pump 300 can drive the normal flow of the coolant. If the flow resistance ΔP of the piping system is less than the maximum flow resistance that the power pump 300 can overcome, it indicates that the power pump 300 can drive the normal flow of the coolant. If the flow resistance ΔP of the piping system is greater than the maximum flow resistance that the power pump 300 can overcome, it indicates that the capacity of the power pump 300 has been exceeded. The number of parallel heat dissipation branches needs to be adjusted, and the flow resistance ΔP of the piping system is calculated based on the adjusted parameters until the flow resistance ΔP of the piping system is less than the maximum flow resistance that the power pump 300 can overcome.

[0089] In this embodiment, when the flow resistance ΔP of the pipeline system is greater than the maximum flow resistance that the power pump 300 can overcome, when the number of parallel branches of the heat dissipation branch is adjusted, the series length of some of the heat dissipation branches can be reduced, and the flow resistance ΔP of the pipeline system can be reduced by increasing the number of heat dissipation branches.

[0090] In this embodiment, when calculating the flow resistance of the pipeline system, it is necessary to calculate the flow resistance ΔP1 of the main loop 400, the flow resistance ΔP2 of any heat dissipation branch, the flow resistance ΔP3 of the longest branch in the first branch section 600, and the flow resistance ΔP4 of the longest branch in the second branch section 700 respectively, and sum up ΔP1, ΔP2, ΔP3, and ΔP4 to obtain the flow resistance ΔP of the pipeline system.

[0091] For the single-phase part in the piping system, that is, the liquid phase cooling medium part in the piping system, the flow resistance is calculated as follows:

[0092]

[0093] Where, u1 is the flow rate of the cooling medium;

[0094] m1 is the flow rate of the cooling medium, which is obtained according to the parameters of the power pump;

[0095] S1 is the cross-sectional area of ​​the flow channel;

[0096] ρ1 is the density of the single-phase cooling medium;

[0097] D1 is the hydraulic diameter of the flow channel;

[0098] v1 is the viscosity of the single-phase cooling medium;

[0099] Re1 is the Reynolds number;

[0100] f1 is the friction coefficient of the single-phase cooling medium in the corresponding flow channel;

[0101] p1 is the flow resistance;

[0102] L1 is the length of the flow channel.

[0103] As mentioned above, the single-phase cooling medium part includes the part from the condenser 100 to the first branch section 600 and the part of the first branch section 600 in the main circuit 400. When calculating, the flow rate, flow rate, density and viscosity of the cooling medium in the main circuit 400, the cross-sectional area, hydraulic diameter of the part of the main circuit 400 and the length of the part from the condenser 100 to the first branch section 600 in the main circuit 400 are substituted into the above formula to obtain ΔP1; similarly, when calculating the flow resistance of the first branch section 600, take the longest pipeline in the first branch section 600 and substitute the above parameters to obtain the flow resistance ΔP3 of the first branch section 600.

[0104] For the two-phase part in the piping system, that is, the cooling medium part where the liquid phase and gas phase are mixed in the piping system, the flow resistance is calculated as follows:

[0105]

[0106] Where, u2 is the flow rate of the cooling medium;

[0107] m2 is the flow rate of the cooling medium, which is obtained according to the parameters of the power pump;

[0108] S2 is the cross-sectional area of ​​the flow channel;

[0109] ρ2 is the average density of the two-phase cooling medium;

[0110] ε is the volume fraction of the liquid phase;

[0111] D2 is the hydraulic diameter of the flow channel;

[0112] v2 is the average viscosity of the two-phase cooling medium;

[0113] Re2 is the Reynolds number;

[0114] f2 is the friction coefficient of the two-phase cooling medium in the corresponding flow channel;

[0115] p2 is the flow resistance;

[0116] L2 is the length of the flow channel.

[0117] The single-phase cooling medium part includes the second branch section 700 to the condenser 100 and the second branch section 700 part in the main loop 400. When calculating, the flow rate, flow rate, density and viscosity of the cooling medium in the main loop 400, the cross-sectional area, hydraulic diameter of the main loop 400 part and the length of the second branch section 700 to the condenser 100 in the main loop 400 are substituted into the above formula to obtain ΔP2; similarly, when calculating the flow resistance of the second branch section 700, take the longest pipeline in the second branch section 700 and substitute the above parameters to obtain the flow resistance ΔP4 of the second branch section 700.

[0118] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the above embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the above embodiments, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of the present invention.

Claims

1. A pump-driven two-phase fluid circuit for dissipating high-temperature heat from a fixed planar area, arranged in a multi-layer thermal protection structure of an aircraft, the multi-layer thermal protection structure comprising a thermal insulation layer, a thermally conductive layer, and a composite material structural layer; the composite material structural layer having a plurality of spaced-apart gaps; It is characterized by: A pump-driven two-phase fluid circuit for dissipating high-temperature heat in a fixed plane area comprises: a piping system, a condenser (100), a liquid storage container (200), and a power pump (300); the piping system comprises a main circuit (400) and a plurality of heat dissipation branches; the condenser (100), the liquid storage container (200), and the power pump (300) are sequentially arranged on the main circuit (400); The heat dissipation branches are arranged in a one-to-one correspondence with the gaps, and the heat dissipation branches are arranged in the corresponding gaps; and both ends of the main circuit (400) are connected to a plurality of the heat dissipation branches through multi-level branches.

2. A design method, characterized in that: Used to design a pump-driven two-phase fluid circuit for high-temperature heat dissipation in a fixed plane area as claimed in claim 1; The design method comprises the steps of: S1, taking the cross-sectional area of ​​the gaps in the composite material structure layer as the cross-sectional area A0 of the preset heat dissipation branch, and determining the number n of the heat dissipation branches based on the number of gaps in the composite material structure layer; S2, based on the cross-sectional area A0 of the preset heat dissipation branch and the number n of heat dissipation branches, obtain the volume V of the main circuit and the heat dissipation branch 外 ; S3, based on the volume V of the main circuit and the heat dissipation main circuit 外 Get the volume V of the liquid storage container; S4, obtaining the filling amount M of the cooling medium based on the volume V of the liquid storage container; S5, comparing the charging amount M of the cooling medium in step S4 with the carrying capacity of the aircraft to obtain a comparison result; S6. Adjust the cross-sectional area A0 of the preset heat dissipation branch based on the comparison result of step S5. When the cross-sectional area A0 of the preset heat dissipation branch changes, repeat steps S2 to S5 until the charging amount M of the cooling medium meets the carrying capacity of the aircraft, and obtain the cross-sectional area A of the heat dissipation branch.

3. The design method according to claim 2, characterized in that: Also includes the steps: S7, selecting a power pump based on the volume V of the liquid storage container and the carrying capacity of the aircraft; S8, obtaining a flow resistance ΔP of the pipeline system based on a cross-sectional area A of the heat dissipation branch, and comparing the flow resistance ΔP of the pipeline system with a maximum flow resistance that can be overcome by the power pump; S9 , adjusting the number of parallel heat dissipation branches based on the comparison result of step S8 , and repeating step S8 until the flow resistance ΔP of the pipeline system meets the maximum flow resistance that the power pump can overcome.

4. The design method according to claim 3, characterized in that: The pipeline system further comprises a first branch section (600) and a second branch section (700) connecting the main circuit and the heat dissipation branch; Step S8 also includes the steps of: obtaining the flow resistance ΔP1 of the main circuit, the flow resistance ΔP2 of any one of the heat dissipation branches, the flow resistance ΔP3 of the longest branch in the first branch segment, and the flow resistance ΔP4 of the longest branch in the second branch segment based on the cross-sectional area A of the heat dissipation branch, and summing ΔP1, ΔP2, ΔP3, and ΔP4 to obtain the flow resistance ΔP of the pipeline system.

5. The design method according to claim 3, characterized in that: Step S9 also includes the following steps: when the comparison result in step S8 is that the flow resistance ΔP of the pipeline system is greater than the maximum flow resistance that the power pump can overcome, adjusting the number of parallel heat dissipation branches and repeating step S8 until the flow resistance ΔP of the pipeline system meets the maximum flow resistance that the power pump can overcome.

6. The design method according to claim 5, characterized in that: In step S8 , adjusting the number of parallel heat dissipation branches includes reducing the length of a portion of the heat dissipation branches connected in series to increase the number of parallel heat dissipation branches.

7. The design method according to claim 2, characterized in that: Step S6 also includes the following steps: when the comparison result in step S5 is that the filling amount M of the cooling medium is greater than the carrying capacity of the aircraft, reducing the cross-sectional area A0 of the heat dissipation branch to reduce the filling amount M of the cooling medium, and repeating steps S2-S5 until the filling amount M of the cooling medium is consistent with the carrying capacity of the aircraft, and obtaining the cross-sectional area A of the heat dissipation branch.

8. The design method according to claim 2, characterized in that: Step S3 includes: S31, determining a value range of the volume V of the liquid storage container based on the following formula: M≤0.9×(V+V 外 )×, at temperature T H Under working conditions; At temperature T L Under working conditions; Under the design working temperature T condition; V 外 =V 外1 +V 外2 ; S32: Determine the minimum value of the value range of V as the volume V of the liquid storage container.

9. The design method according to claim 8, characterized in that: Step S3 further includes: Get T H and T L .

10. The design method according to claim 9, characterized in that: The cross-sectional area of ​​the main circuit is the sum of the cross-sectional areas of each heat dissipation branch.

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