Aircraft cabin interior and exterior continuous integrated comprehensive heat management system

Abstract

The invention discloses an internal and external continuous integrated comprehensive heat management system for an aircraft cabin. The internal and external continuous integrated comprehensive heat management system comprises an end active cooling component, a shell, a local active cooling component, a pneumatic heat conduction component, a storage tank, a fluid transportation pipe network, N high-power electronic devices, N embedded microfluid radiators and a measurement control system, the end head active cooling part is arranged at the end part of the shell; the local active cooling part is mounted in the middle of the shell; the storage box is located in the shell and connected with the head active cooling component through the pneumatic heat conduction component. The embedded microfluid radiators are respectively arranged on the corresponding high-power electronic equipment; the head active cooling part, the local active cooling part, the storage box and the embedded microfluid radiator are communicated through a fluid conveying pipe network; and the measurement control system is arranged in the shell. According to the system, cabin thermal protection and an in-cabin thermal management system are coupled, integrated comprehensive thermal management is carried out, and comprehensive utilization of limited resources in a cabin is achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of integrated thermal management, and in particular relates to an integrated thermal management system that is continuously integrated inside and outside an aircraft cabin. Background Art

[0002] In order to achieve the purpose of long-range strong penetration and strike defense, new aircraft need to maintain high-speed flight for a long time in the dense atmosphere. Due to the strong compression of the air and the violent friction between the air and the wall, the temperature of the aircraft wall will rise rapidly, causing uneven thermal expansion and even ablation inside the structure. At the same time, the mission capabilities of high-speed aircraft are constantly improving and expanding. For example, the loading of high-power equipment has increased the demand for advanced power supplies and power supply technologies. With the high-power trend of airborne equipment, the heat dissipation and thermal management problems in the cabin will be very serious. In traditional methods, the thermal protection outside the aircraft cabin is designed separately from the thermal management inside the cabin. Thermal protection is usually located on the outside of the aircraft, using heat sink, ablation, radiation and active methods to protect the internal load-bearing structure, instruments and equipment and the temperature of the payload within the allowable temperature range.

[0003] Faced with the rapidly increasing internal and external heat treatment requirements of new aircraft, this traditional independent internal and external design is becoming increasingly inadequate. In order to achieve the goal, it often leads to a complex and heavy system, which seriously affects the performance of the aircraft and can no longer meet the refined design requirements of future high-speed aircraft. Summary of the invention

[0004] The technology of the present invention solves the problem: Overcoming the shortcomings of the prior art, providing a continuous integrated thermal management system inside and outside the aircraft cabin, coupling the cabin thermal protection with the cabin thermal management system, performing integrated integrated thermal management, and realizing the comprehensive utilization of limited resources in the cabin. It is one of the effective ways to solve the "thermos bottle" flight problem of new aircraft.

[0005] In order to solve the above technical problems, the present invention discloses a continuous integrated thermal management system for the interior and exterior of an aircraft cabin, comprising: an end active cooling component, a shell, a local active cooling component, an aerodynamic heat conduction component, a storage tank, a fluid transport network, N high-power electronic devices, N embedded microfluidic radiators and a measurement and control system; wherein N≥1;

[0006] The end active cooling component is installed at the end of the shell;

[0007] The local active cooling component is installed in the middle of the shell;

[0008] The tank is located inside the shell and connected to the head active cooling component through the pneumatic heat conduction component;

[0009] Each embedded microfluidic heat sink is installed on a corresponding high-power electronic device; wherein the embedded microfluidic heat sink is integrated with the chip of the high-power electronic device;

[0010] The head active cooling component, the local active cooling component, the storage tank and the embedded microfluidic radiator are connected through a fluid transport pipe network;

[0011] The measurement and control system is installed inside the housing.

[0012] In the above-mentioned integrated thermal management system inside and outside the aircraft cabin, the end active cooling component is a porous structure, including: a first porous area composed of a plurality of holes, and a first liquid collecting cavity on the wall side of the first porous area; wherein the first porous area is connected to the first liquid collecting cavity.

[0013] In the above-mentioned integrated thermal management system inside and outside the aircraft cabin, the local active cooling component is a porous structure, including a second porous area composed of a plurality of holes, and a second liquid collecting cavity on the wall side of the second porous area; wherein the second porous area is connected to the second liquid collecting cavity.

[0014] In the above-mentioned integrated thermal management system for the interior and exterior of the aircraft cabin, the aerodynamic heat conduction components include: a high-temperature metal heat pipe and a ceramic protective sleeve; the high-temperature metal heat pipe includes: an evaporation section, an insulation section and a condensation section;

[0015] The evaporation section is arranged on the downstream outer surface of the terminal active cooling component;

[0016] The condensing section is arranged in the storage tank;

[0017] The ceramic protective sleeve is wrapped around the outside of the thermal insulation section.

[0018] In the above-mentioned integrated thermal management system for the interior and exterior of the aircraft cabin, the tank includes: a gas expansion tank, a water tank and a movable sealing plate;

[0019] The gas expansion box and the water tank are butt-jointed and installed; wherein a movable sealing plate is provided between the gas expansion box and the water tank;

[0020] The condensation section of the high-temperature metal heat pipe is arranged in the gas expansion box.

[0021] In the above-mentioned integrated thermal management system for the interior and exterior of the aircraft cabin, the fluid transport network includes: an end fluid transport network and a high-power electronic equipment fluid transport network;

[0022] The second electronic valve and the first electronic valve are respectively installed on the branch A and the branch B in the end fluid transport network;

[0023] Fluid transport pipeline network for high-power electronic equipment, including bypass pipeline network and heat exchange pipeline network;

[0024] The fourth electronic valve and the third electronic valve are installed on the branch C and the branch D in the bypass pipe network respectively;

[0025] The sixth electronic valve and the fifth electronic valve are respectively installed on the branch E and the branch F in the heat exchange pipe network.

[0026] In the above-mentioned integrated thermal management system inside and outside the aircraft cabin, the end of the end fluid transport pipeline network is connected to the first liquid collecting cavity; the end of the high-power electronic equipment fluid transport pipeline network is connected to the second liquid collecting cavity.

[0027] In the above-mentioned integrated thermal management system for the interior and exterior of the aircraft cabin, the measurement and control system includes: a data collector, a controller, an end active cooling temperature sensor, a local cooling temperature sensor, and a high-power electronic device temperature sensor;

[0028] The terminal active cooling temperature sensor is embedded and packaged in the first porous area;

[0029] A local cooling temperature sensor is embedded and packaged in the second porous area;

[0030] High-power electronic equipment temperature sensor embedded package in high-power electronic equipment;

[0031] The data collector is connected to the terminal active cooling temperature sensor, the local cooling temperature sensor and the high-power electronic device temperature sensor through cables;

[0032] The data collector is connected to the controller via RS-485 communication;

[0033] The controller is connected to each electronic valve via cables.

[0034] In the above-mentioned aircraft cabin internal and external continuous integrated thermal management system,

[0035] Data collector, used to collect the temperature measurement value T of the active cooling temperature sensor of the end a , the temperature measurement value T of the local cooling temperature sensor b and the temperature measurement value T of the temperature sensor of the power electronic device c ; The temperature measurement value T a , temperature measurement value T b and the temperature measurement value T c Transmit to the controller;

[0036] The controller is used to receive the temperature measurement value T a , temperature measurement value T b and the temperature measurement value T c , control the opening and closing of each electronic valve:

[0037] Judge T a Is it greater than the set terminal temperature upper limit T a—max :If T a Greater than T a—max , then set the lower limit of the terminal temperature T a—min As the target, the first electronic valve and the second electronic valve are controlled to open by PID method; if T a Not greater than T a—max , then judge T a Is it less than T a—min :If T a Less than T a—min , then T a—max As the target, the first electronic valve and the second electronic valve are closed by controlling the PID method; if T a Not less than T a—min , the states of the first electronic valve and the second electronic valve are maintained unchanged;

[0038] Judge T b Is it greater than the set local temperature upper limit T b—max :If T b Greater than T b—max , then set the lower limit of local temperature T b—min As the target, the third and fourth electronic valves are controlled to open by PID method; if T b Not greater than T b—max , then judge T b Is it less than T b—min :If T b Less than T b—min , then T b—max As the target, the third and fourth electronic valves are controlled to close by PID method; if T b Not less than T b—min , the states of the third electronic valve and the fourth electronic valve are maintained unchanged;

[0039] Judge T c Is it greater than the set upper temperature limit T of the electronic equipment? c—max :If T c Greater than T c—max , then set the lower limit of the electronic equipment temperature T c—min As the target, the fifth and sixth electronic valves are controlled to open by PID method; if T c Not greater than T c—max , then judge T c Is it less than T c—min :If T c Less than T c—min , then T c—max As the target, the fifth and sixth electronic valves are closed by controlling the PID method; if T c Not less than Tc—min , the states of the fifth and sixth electronic valves are maintained unchanged.

[0040] In the above-mentioned aircraft cabin internal and external continuous integrated thermal management system,

[0041] When the aircraft is flying at high speed, due to the strong compression of air and the intense friction between air and the wall, a large amount of aerodynamic heat will be generated at the end and side wall of the aircraft, and the aerodynamic heat will be transmitted to the gas expansion tank through the aerodynamic heat conduction component; the gas will expand after being heated and push the movable sealing plate to move, and the cooling medium in the water tank will enter the end fluid transport pipeline network and the high-power electronic equipment fluid transport pipeline network under the push of the movable sealing plate;

[0042] The cooling medium entering the end fluid transport network first enters the first liquid collecting cavity, then enters the first porous area, completes heat exchange with the first porous area, flows out of the aircraft end wall, and spreads downstream to form a thermal protection air film;

[0043] The cooling medium entering the fluid transport network of high-power electronic equipment first enters the embedded microfluidic radiator through the heat exchange network, then enters the second liquid collecting cavity, and finally enters the second porous area. After completing the heat exchange with the second porous area, it flows out of the aircraft wall and spreads into a thermal protective air film along the downstream; or, the cooling medium entering the fluid transport network of high-power electronic equipment first enters the second liquid collecting cavity through the heat exchange network, then enters the second porous area, after completing the heat exchange with the second porous area, it flows out of the aircraft wall and spreads into a thermal protective air film along the downstream.

[0044] The present invention has the following advantages:

[0045] (1) The present invention discloses a continuously integrated thermal management system for the interior and exterior of an aircraft cabin. By means of a centralized cold source and a liquid-gas continuous phase change, the invention realizes the unified treatment of thermal protection of the aircraft wall and thermal control of the aircraft's internal electronic devices, and realizes integrated adaptive regulation, thereby improving the level of aircraft integrated design.

[0046] (2) The present invention discloses a continuously integrated thermal management system for the interior and exterior of an aircraft cabin, which relies on aerodynamic heat to achieve self-transportation of cooling fluid without the need for additional auxiliary power equipment, thereby reducing the number and weight of equipment and improving system reliability.

[0047] (3) The present invention discloses a continuously integrated thermal management system for the interior and exterior of an aircraft cabin, which (1) supplies liquid to end cooling and local cooling separately, thereby solving the problem of mismatch between supply and demand of cooling fluids due to the large difference in aerodynamic pressure between the end and the local area. At the same time, the local cooling areas can be arranged at intervals according to actual needs, thereby improving the flexibility and applicability of system layout and expansion, and improving the cooling efficiency of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0048] Figure 1 This is a schematic diagram of the structure of a continuous integrated thermal management system for the interior and exterior of an aircraft cabin according to an embodiment of the present invention;

[0049] Figure 2 It is a schematic diagram of the control components of a continuous integrated thermal management system for the interior and exterior of an aircraft cabin according to an embodiment of the present invention;

[0050] Figure 3 It is a schematic diagram of a comprehensive thermal management control strategy in an embodiment of the present invention. DETAILED DESCRIPTION

[0051] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments disclosed in the present invention will be further described in detail below with reference to the accompanying drawings.

[0052] like Figure 1 As shown, in this embodiment, the aircraft cabin internal and external continuous integrated thermal management system includes: a terminal active cooling component 1, a shell 2, a local active cooling component 3, an aerodynamic heat conduction component 4, a tank 5, a fluid transport network 6, N (N≥1) high-power electronic devices 7, N embedded microfluidic radiators 8 and a measurement control system 9. Among them, the terminal active cooling component 1 is installed at the end of the shell 2; the local active cooling component 3 is installed in the middle of the shell 2; the tank 5 is located inside the shell 2 and is connected to the terminal active cooling component 1 through the aerodynamic heat conduction component 4; each embedded microfluidic radiator 8 is installed on the corresponding high-power electronic device 7, and the embedded microfluidic radiator 8 is designed to be integrated with the chip of the high-power electronic device 7; the terminal active cooling component 1, the local active cooling component 3, the tank 5 and the embedded microfluidic radiator 8 are connected through the fluid transport network 6; the measurement control system 9 is installed inside the shell 2.

[0053] In this embodiment, the end active cooling component 1 is a porous structure, including: a first porous region 11 composed of a plurality of holes, and a first liquid collecting cavity 12 on the inner wall side of the first porous region 11; the first porous region 11 is connected to the first liquid collecting cavity 12. Similarly, the local active cooling component 3 is a porous structure, including a second porous region 31 composed of a plurality of holes, and a second liquid collecting cavity 32 on the inner wall side of the second porous region 31; the second porous region 31 is connected to the second liquid collecting cavity 32. Preferably, the porous medium material can be titanium alloy TC4, and the porosity can be 50μm to 100μm.

[0054] In this embodiment, the pneumatic heat conduction component 4 may specifically include: a high-temperature metal heat pipe 41 and a ceramic protective sleeve 42. Further, the high-temperature metal heat pipe 41 includes: an evaporation section 411, an insulation section 412 and a condensation section 413. Among them, the evaporation section 411 is arranged on the downstream outer surface of the terminal active cooling component 1; the condensation section 413 is arranged in the storage tank 5; and the ceramic protective sleeve 42 is coated on the outside of the insulation section 412.

[0055] In this embodiment, the storage tank 5 may specifically include: a gas expansion tank 51, a water tank 52 and a movable sealing plate 53. The gas expansion tank 51 and the water tank 52 are butt-jointed, and a movable sealing plate 53 is provided between the gas expansion tank 51 and the water tank 52; the condensing section 413 of the high-temperature metal heat pipe 41 is arranged in the gas expansion tank 51.

[0056] In this embodiment, the fluid transport network 6 may specifically include: a terminal fluid transport network 61 and a high-power electronic device fluid transport network 62. Among them, the end of the terminal fluid transport network 61 is connected to the first liquid collecting chamber 12, and the branch A613 and the branch B614 in the terminal fluid transport network 61 are respectively installed with a second electronic valve 612 and a first electronic valve 611. Further, the end of the high-power electronic device fluid transport network 62 is connected to the second liquid collecting chamber 32; the high-power electronic device fluid transport network 62 includes: a bypass network 621 and a heat exchange network 622; the branch C6212 and the branch D6214 in the bypass network 621 are respectively installed with a fourth electronic valve 6213 and a third electronic valve 6211; the branch E6221 and the branch F6224 in the heat exchange network 622 are respectively installed with a sixth electronic valve 6223 and a fifth electronic valve 6222.

[0057] In this embodiment, if Figure 2 As shown, the measurement control system 9 may specifically include: a data collector 91, a controller 92, an active cooling temperature sensor 93 at the end, a local cooling temperature sensor 94, and a high-power electronic device temperature sensor 95. Among them, the active cooling temperature sensor 93 at the end is embedded and packaged in the first porous area 11; the local cooling temperature sensor 94 is embedded and packaged in the second porous area 31; the high-power electronic device temperature sensor 95 is embedded and packaged in the high-power electronic device 7; the data collector 91 is connected to the active cooling temperature sensor 93 at the end, the local cooling temperature sensor 94, and the high-power electronic device temperature sensor 95 through a cable; the data collector 91 is connected to the controller 92 through an RS-485 communication method; and the controller 92 is connected to each electronic valve through a cable.

[0058] Preferably, the data collector 91 is used to collect the temperature measurement value T of the terminal active cooling temperature sensor 93. a , the temperature measurement value T of the local cooling temperature sensor 94b and the temperature measurement value T of the power electronic device temperature sensor 95 c ; The temperature measurement value T a , temperature measurement value T b and the temperature measurement value T c Transmitted to the controller 92.

[0059] Further, the controller 92 is used to receive the temperature measurement value T a , temperature measurement value T b and the temperature measurement value T c , control the opening and closing of each electronic valve. Figure 3 The specific control strategy is as follows:

[0060] Judge T a Is it greater than the set terminal temperature upper limit T a—max :If T a Greater than T a—max , then set the lower limit of the terminal temperature T a—min As the target, the first electronic valve 611 and the second electronic valve 612 are controlled to open by PID method; if T a Not greater than T a—max , then judge T a Is it less than T a—min :If T a Less than T a—min , then T a—max As the target, the first electronic valve 611 and the second electronic valve 612 are closed by controlling the PID method; if T a Not less than T a—min , the states of the first electronic valve 611 and the second electronic valve 612 are maintained unchanged. Then T is determined again. a Is it greater than T a—max , and the cycle is repeated.

[0061] Judge T b Is it greater than the set local temperature upper limit T b—max :If T b Greater than T b—max , then set the lower limit of local temperature T b—min As the target, the third electronic valve 6211 and the fourth electronic valve 6213 are controlled to open by PID method; if T b Not greater than T b—max , then judge T b Is it less than T b—min :If T b Less than T b—min , then T b—max As the target, the third electronic valve 6211 and the fourth electronic valve 6213 are closed by controlling the PID method; if T bNot less than T b—min , the third electronic valve 6211 and the fourth electronic valve 6213 are maintained unchanged. Then T is determined again. a Is it greater than T a—max , and the cycle is repeated.

[0062] Judge T c Is it greater than the set upper temperature limit T of the electronic equipment? c—max :If T c Greater than T c—max , then set the lower limit of the electronic equipment temperature T c—min As the target, the fifth electronic valve 6222 and the sixth electronic valve 6223 are controlled to open by PID method; if T c Not greater than T c—max , then judge T c Is it less than T c—min :If T c Less than T c—min , then T c—max As the target, the fifth electronic valve 6222 and the sixth electronic valve 6223 are closed by controlling the PID method; if T c Not less than T c—min , the fifth electronic valve 6222 and the sixth electronic valve 6223 are maintained unchanged. Then T is determined again. a Is it greater than T a—max , and the cycle is repeated.

[0063] In this embodiment, the working principle of the integrated thermal management system inside and outside the aircraft cabin is as follows:

[0064] a. When the aircraft is flying at high speed, due to the strong compression of air and the violent friction between the air and the wall, a large amount of aerodynamic heat will be generated at the end and side walls of the aircraft, and the aerodynamic heat will be transmitted to the gas expansion tank 51 through the aerodynamic heat conduction component 4; the gas expands after being heated and pushes the movable sealing plate 53 to move, and the cooling medium in the water tank 52 enters the end fluid transport pipeline 61 and the high-power electronic equipment fluid transport pipeline 62 under the push of the movable sealing plate 53.

[0065] b. The cooling medium entering the end fluid transport network 61 first enters the first liquid collecting cavity 12, then enters the first porous area 11, completes heat exchange with the first porous area 11, flows out of the aircraft end wall, and spreads along the downstream to form a thermal protection air film.

[0066] c. The cooling medium entering the fluid transport network 62 of the high-power electronic equipment can first enter the embedded microfluidic radiator 8 through the heat exchange network 622, then enter the second liquid collecting chamber 32, and finally enter the second porous area 31, according to the heat dissipation requirements of the high-power electronic equipment, and flow out of the aircraft wall after completing the heat exchange with the second porous area 31, and spread along the downstream to form a layer of thermal protective air film. Or, when the high-power electronic equipment does not need to dissipate heat, the cooling medium can also directly enter the second liquid collecting chamber 32, that is: the cooling medium entering the fluid transport network 62 of the high-power electronic equipment first enters the second liquid collecting chamber 32 through the heat exchange network 622, then enters the second porous area 31, and flows out of the aircraft wall after completing the heat exchange with the second porous area 31, and spreads along the downstream to form a layer of thermal protective air film.

[0067] In this embodiment, the gas in the gas expansion tank 51 may be helium; the cooling medium in the water tank 52 may be water; and the working medium of the high-temperature metal heat pipe 41 may be sodium.

[0068] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0069] The contents not described in detail in the specification of the present invention belong to the common knowledge of the professionals in this field.

Claims

1. A continuous integrated thermal management system for the interior and exterior of an aircraft cabin, It is characterized in that include: An end active cooling component (1), a housing (2), a local active cooling component (3), a pneumatic heat conduction component (4), a storage tank (5), a fluid transport network (6), N high-power electronic devices (7), N embedded microfluidic heat sinks (8) and a measurement control system (9); wherein N≥1; The end active cooling component (1) is installed at the end of the housing (2); A local active cooling component (3) is installed in the middle of the housing (2); The storage tank (5) is located inside the housing (2) and is connected to the head active cooling component (1) via a pneumatic heat conduction component (4); Each embedded microfluidic heat sink (8) is mounted on a corresponding high-power electronic device (7) respectively; wherein the embedded microfluidic heat sink (8) and the chip of the high-power electronic device (7) are integrated; The head active cooling component (1), the local active cooling component (3), the storage tank (5) and the embedded microfluidic heat sink (8) are connected through a fluid transport pipe network (6); The measurement control system (9) is installed inside the housing (2).

2. The aircraft cabin internal and external continuous integrated thermal management system according to claim 1, It is characterized in that The end active cooling component (1) is a porous structure, comprising: a first porous region (11) composed of a plurality of holes, and a first liquid collecting cavity (12) on the inner wall side of the first porous region (11); wherein the first porous region (11) is connected to the first liquid collecting cavity (12).

3. The aircraft cabin internal and external continuous integrated thermal management system according to claim 2, It is characterized in that The local active cooling component (3) is a porous structure, comprising a second porous region (31) composed of a plurality of holes, and a second liquid collecting cavity (32) on the inner wall side of the second porous region (31); wherein the second porous region (31) is connected to the second liquid collecting cavity (32).

4. The aircraft cabin internal and external continuous integrated thermal management system according to claim 3, It is characterized in that The pneumatic heat conduction component (4) comprises: a high-temperature metal heat pipe (41) and a ceramic protective sleeve (42); the high-temperature metal heat pipe (41) comprises: an evaporation section (411), an insulation section (412) and a condensation section (413); The evaporation section (411) is arranged on the downstream outer surface of the end active cooling component (1); The condensation section (413) is arranged in the storage tank (5); The ceramic protective sleeve (42) is coated on the outside of the thermal insulation section (412).

5. The aircraft cabin internal and external continuous integrated thermal management system according to claim 4, It is characterized in that The storage tank (5) comprises: a gas expansion tank (51), a water tank (52) and a movable sealing plate (53); The gas expansion box (51) and the water box (52) are butt-jointed and installed; wherein a movable sealing plate (53) is provided between the gas expansion box (51) and the water box (52); The condensation section (413) of the high-temperature metal heat pipe (41) is arranged in the gas expansion box (51).

6. The aircraft cabin internal and external continuous integrated thermal management system according to claim 5, It is characterized in that The fluid transport pipeline network (6) comprises: an end fluid transport pipeline network (61) and a high-power electronic equipment fluid transport pipeline network (62); A second electronic valve (612) and a first electronic valve (611) are respectively installed on branch A (613) and branch B (614) in the end fluid transport pipe network (61); A high-power electronic equipment fluid transport pipe network (62), comprising: a bypass pipe network (621) and a heat exchange pipe network (622); A fourth electronic valve (6213) and a third electronic valve (6211) are respectively installed on branch C (6212) and branch D (6214) in the bypass pipe network (621); The sixth electronic valve (6223) and the fifth electronic valve (6222) are respectively installed on the branch E (6221) and the branch F (6224) in the heat exchange pipe network (622).

7. The aircraft cabin internal and external continuous integrated thermal management system according to claim 6, It is characterized in that The end of the end head fluid transport pipe network (61) is in communication with the first liquid collecting chamber (12); the end of the high-power electronic equipment fluid transport pipe network (62) is in communication with the second liquid collecting chamber (32).

8. The aircraft cabin internal and external continuous integrated thermal management system according to claim 7, It is characterized in that A measurement control system (9), comprising: a data acquisition device (91), a controller (92), an end active cooling temperature sensor (93), a local cooling temperature sensor (94) and a high-power electronic device temperature sensor (95); The terminal active cooling temperature sensor (93) is embedded and packaged in the first porous area (11); The local cooling temperature sensor (94) is embedded and packaged in the second porous area (31); A high-power electronic device temperature sensor (95) is embedded and packaged in the high-power electronic device (7); The data collector (91) is connected to the terminal active cooling temperature sensor (93), the local cooling temperature sensor (94) and the high-power electronic device temperature sensor (95) by means of cables; The data collector (91) is connected to the controller (92) via RS-485 communication; The controller (92) is connected to each electronic valve via cables.

9. The aircraft cabin internal and external continuous integrated thermal management system according to claim 8, It is characterized in that A data collector (91) is used to collect a temperature measurement value T of the terminal active cooling temperature sensor (93). a , the temperature measurement value T of the local cooling temperature sensor (94) b and a temperature measurement value T of a temperature sensor (95) of a high power electronic device c ; The temperature measurement value T a , temperature measurement value T b and the temperature measurement value T c Transmit to controller (92); The controller (92) is used to receive the temperature measurement value T a , temperature measurement value T b and the temperature measurement value T c , control the opening and closing of each electronic valve: Judge T a Is it greater than the set terminal temperature upper limit T a—max :If T a Greater than T a—max , then set the lower limit of the terminal temperature T a—min As the target, the first electronic valve (611) and the second electronic valve (612) are controlled to open by PID method; if T a Not greater than T a—max , then judge T a Is it less than T a—min :If T a Less than T a—min , then T a—max As the target, the first electronic valve (611) and the second electronic valve (612) are controlled to close by PID method; if T a Not less than T a—min , the states of the first electronic valve (611) and the second electronic valve (612) are maintained unchanged; Determine T b whether it is greater than the set local temperature upper limit T b—max : If T b is greater than T b—max , then target the set local temperature lower limit T b—min and control the opening of the third solenoid valve (6211) and the fourth solenoid valve (6213) in a PID manner; if T b is not greater than T b—max , then determine whether T b is less than T b—min : If T b is less than T b—min , then target T b—max and control the closing of the third solenoid valve (6211) and the fourth solenoid valve (6213) in a PID manner; if T b is not less than T b—min , then keep the states of the third solenoid valve (6211) and the fourth solenoid valve (6213) unchanged; Judge T c Is it greater than the set upper temperature limit T of the electronic equipment? c—max :If T c Greater than T c—max , then set the lower limit of the electronic equipment temperature T c—min As the target, the fifth electronic valve (6222) and the sixth electronic valve (6223) are controlled to open by PID method; if T c Not greater than T c—max , then judge T c Is it less than T c—min :If T c Less than T c—min , then T c—max As the target, the fifth electronic valve (6222) and the sixth electronic valve (6223) are closed by controlling the PID method; if T c Not less than T c—min , the states of the fifth electronic valve (6222) and the sixth electronic valve (6223) remain unchanged.

10. The aircraft cabin internal and external continuous integrated thermal management system according to claim 6, It is characterized in that When the aircraft is flying at high speed, a large amount of aerodynamic heat is generated at the end and side walls of the aircraft due to the strong compression of air and the intense friction between the air and the wall surface. The aerodynamic heat is transmitted to the gas expansion box (51) through the aerodynamic heat conduction component (4); the gas expands after being heated and pushes the movable sealing plate (53) to move, and the cooling medium in the water tank (52) enters the end fluid transport pipeline network (61) and the high-power electronic equipment fluid transport pipeline network (62) under the push of the movable sealing plate (53); The cooling medium entering the end fluid transport network (61) first enters the first liquid collecting cavity (12), then enters the first porous area (11), completes heat exchange with the first porous area (11), flows out of the end wall of the aircraft, and spreads downstream to form a thermal protection air film; The cooling medium entering the fluid transport network (62) of the high-power electronic device first enters the embedded microfluidic heat sink (8) through the heat exchange network (622), then enters the second liquid collecting chamber (32), and finally enters the second porous region (31). After completing the heat exchange with the second porous region (31), the cooling medium flows out of the aircraft wall surface and spreads downstream to form a thermal protective air film; or, the cooling medium entering the fluid transport network (62) of the high-power electronic device first enters the second liquid collecting chamber (32) through the heat exchange network (622), then enters the second porous region (31), after completing the heat exchange with the second porous region (31), the cooling medium flows out of the aircraft wall surface and spreads downstream to form a thermal protective air film.

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