Hypersonic velocity leading edge combined cooling structure, system and method capable of coping with space-time non-uniform heat flow

Abstract

The invention provides a hypersonic velocity leading edge combined cooling structure, system and method capable of coping with space-time non-uniform heat flow, and is mainly used for solving the problems that in the existing active thermal protection technology, head cooling insufficiency and downstream cooling excess are likely to occur in space, the cooling effect is difficult to dynamically adjust in time, cooling insufficiency or excess in some time periods is caused, and the cooling effect is poor. And the whole porous medium structure is inconvenient to check and maintain. The invention discloses a hypersonic velocity leading edge combined cooling structure capable of coping with space-time non-uniform heat flow. The hypersonic velocity leading edge combined cooling structure comprises a diverging part, a structure part, a rear cover plate and a shunting core, through discrete arrangement of the diverging parts and setting of different porosities for the diverging parts at different positions, the porosities of the N diverging parts are sequentially reduced from the head part to the tail part, and the larger the porosities are, the more the coolant distribution amount is, so that the technical problems of insufficient head cooling and excessive downstream cooling easily occurring in space are solved.

Description

Technical Field

[0001] The present invention relates to an active thermal protection structure, system and method for an aircraft, and particularly to a hypersonic leading edge combined cooling structure, system and method capable of coping with spatio-temporally non-uniform heat flux. Background Art

[0002] A hypersonic aircraft generally refers to an aircraft with a flight speed higher than 5Ma and a flight altitude in the range of 20 - 100 km. It has the characteristics of high flight speed, difficult early warning, and high penetration success rate, and has significant military value.

[0003] During the flight of a hypersonic aircraft, due to its extremely high speed, it will generate an extremely high temperature when it violently rubs against the air in the atmosphere. In order to protect the structure and internal equipment of the aircraft, thermal protection must be carried out. With the increase in the speed and maneuverability of hypersonic aircraft, the aerodynamic thermal environment they face is more severe, and there is a risk that the aircraft structure system will become unstable due to aerodynamic thermal shock. At the same time, due to the increasing requirement for the reusable aircraft, traditional passive thermal protection technologies (such as heat absorption and heat insulation technologies) and semi-active thermal protection technologies (such as ablation and heat pipe technologies) face objective difficulties when dealing with more complex and changeable flight environments.

[0004] As an efficient active thermal protection technology, transpiration cooling realizes efficient thermal management by using porous media inside the aircraft structure and allowing a coolant to flow through these media. Its core principle is to use the densely distributed microchannels inside the porous media to increase the specific surface area and improve the heat transfer efficiency. The coolant flowing out of the microchannels will also form a uniform gas film protection layer on the outer surface of the structure to further block heat, and is regarded as one of the main technical solutions for the active thermal protection of the hypersonic leading edge.

[0005] However, for the leading-edge structure of hypersonic vehicles, transpiration cooling has the following disadvantages: (1) Spatially, from the stagnation point of the hypersonic vehicle's nose backward, the aerodynamic heat and aerodynamic forces change violently and are extremely unevenly distributed. In the stagnation area where the aerodynamic heat is the highest and cooling is most needed, the aerodynamic force is the largest, and it is the most difficult for the coolant to flow out. If the transpiration cooling structure uses an integral continuous and uniform porous medium as the transpiration surface, it is easy to have insufficient cooling at the head and excessive cooling downstream. When conducting large-area thermal protection, this situation of uneven spatial cooling will further deteriorate. (2) Temporally, when the vehicle flies along the flight profile or maneuvers rapidly, flight characteristic parameters such as altitude, flight speed, and pitch angle change with time, making the surface aerodynamic thermal distribution have significant time dependence. The thermal protection requirements for each period are different, and the existing active thermal protection technologies are difficult to dynamically adjust the cooling effect in time, resulting in insufficient or excessive cooling in some periods. (3) For hypersonic vehicles with high requirements for reusability, using an integral porous medium transpiration surface will bring inconvenience to the inspection and maintenance of the thermal protection system.

[0006] In summary, it has become very necessary and urgent to develop a lightweight and efficient active thermal protection structure that can cope with the spatially and temporally non-uniform aerodynamic thermal environment, is suitable for large-area use, and is convenient for rapid maintenance between adjacent flights. Summary of the Invention

[0007] The object of the present invention is to solve the technical problems of the existing active thermal protection technologies, which are prone to insufficient cooling at the head and excessive cooling downstream in space, difficult to dynamically adjust the cooling effect in time, resulting in insufficient or excessive cooling in some periods, and inconvenient inspection and maintenance of the integral porous medium structure. The present invention proposes a hypersonic leading-edge combined cooling structure, system, and method that can cope with spatially and temporally non-uniform heat fluxes.

[0008] To solve the above technical problems, the technical solution provided by the present invention is as follows:

[0009] A hypersonic leading-edge combined cooling structure that can cope with spatially and temporally non-uniform heat fluxes, characterized in that it includes a housing, a rear cover plate, and N shunt cores;

[0010] The housing includes N divergent parts and N structural parts, where N≥3; the N divergent parts and the N structural parts are alternately connected; one of the divergent parts is arranged at the head of the housing, which is a hollow structure with one end closed and the other end open, and the open end faces the inside of the housing; the remaining N-1 divergent parts and the N structural parts are both hollow structures with both ends open;

[0011] The side wall of the divergent part is a porous medium structure, and the porosity of the N divergent parts decreases sequentially from the head to the tail of the housing;

[0012] The rear cover plate is arranged at the rear end of the structural part located at the tail of the housing, and together with the N diverging parts and N structural parts, it encloses and forms a cooling cavity; a coolant inlet is axially opened at the center of the rear cover plate;

[0013] The N shunt cores are sequentially arranged coaxially and at intervals in the cooling cavity, and a radial coolant shunt channel is formed between two adjacent shunt cores; N - 1 coolant shunt channels respectively correspond to the first N - 1 structural parts one by one;

[0014] Axially penetrating coolant main channels are respectively arranged on the N shunt cores, and the inlet of the coolant main channel of the shunt core closer to the rear cover plate is communicated with the coolant inlet for inputting coolant;

[0015] A coolant delivery channel is formed between the outer side wall of the shunt core and the inner side walls of the diverging part and the structural part; the flow area of the coolant delivery channel located at the head of the housing is larger than that of the coolant shunt channel, and the flow area of the coolant shunt channel gradually decreases from the head to the tail of the housing.

[0016] Furthermore, an elastic sealing ring is sleeved on one end of the shunt core close to the rear cover plate, and the elastic sealing ring is connected with the rear cover plate, and is used for sealing connection in cooperation with expansion and contraction when the shunt core moves axially.

[0017] Furthermore, N = 3, and the three structural parts are respectively a first structural part, a second structural part and a third structural part; the third structural part is connected with the rear cover plate;

[0018] The three shunt cores are respectively a first shunt core, a second shunt core and a third shunt core; a coolant shunt channel is respectively formed between the first shunt core and the second shunt core, and between the second shunt core and the third shunt core.

[0019] Furthermore, the connection between the diverging part and the structural part is detachable.

[0020] Furthermore, the diverging part and the structural part are bonded by a high - temperature resistant sealant or connected by bolts.

[0021] Furthermore, the diverging part is made by sintering high - temperature resistant material particles or 3D printing.

[0022] The present invention also provides a hypersonic leading - edge combined cooling system capable of coping with spatio - temporal non - uniform heat flux, including a combined cooling structure, a coolant unit, a sensor and a transmission unit; the special feature lies in:

[0023] The combined cooling structure adopts the above - mentioned hypersonic leading - edge combined cooling structure capable of coping with spatio - temporal non - uniform heat flux;

[0024] The sensor is installed inside the cooling cavity and is used for detecting the data of the increase and decrease of the heat flux inside the cooling cavity;

[0025] The coolant unit includes a coolant storage chamber and a coolant drive pump;

[0026] The coolant storage chamber stores coolant;

[0027] The input end of the coolant driving pump is connected to the sensor, and the output end of the coolant driving pump is connected to the input end of the coolant storage chamber, for driving the coolant storage chamber to transport the coolant, and adjusting the supply amount of the coolant supplied by the coolant storage chamber according to the heat flow increase and decrease data;

[0028] The output end of the coolant storage chamber is connected to the coolant inlet on the rear cover plate for conveying coolant into the cooling cavity;

[0029] The input end of the transmission unit is connected to the sensor for receiving and processing heat flow increase and decrease data, and the output end of the transmission unit is connected to the shunt core for driving the shunt core to move axially and actively adjusting the axial movement direction of the shunt core according to the heat flow increase and decrease data.

[0030] Furthermore, the coolant is a gas coolant or a liquid coolant.

[0031] The present invention also provides a hypersonic leading edge combined cooling method capable of coping with time-space non-uniform heat flow. The hypersonic leading edge combined cooling system capable of coping with time-space non-uniform heat flow is special in that it comprises the following steps:

[0032] S1, impact cooling: the coolant driving pump drives the coolant storage chamber to transport the coolant, and the coolant flows into the coolant main channel in the cooling cavity through the coolant inlet;

[0033] The coolant flows along the coolant main channel, and part of the coolant flows out from the outlet of the coolant main channel to form impact cooling on the divergent part located at the head of the shell; the remaining part of the coolant flows through the coolant shunt channel to the coolant delivery channel to form impact cooling on the inner surface of the divergent part and the structural part;

[0034] S2, divergent cooling: the coolant is divergently cooled through N divergent parts;

[0035] S3, air film cooling: After the coolant flows out of the diverging part, a uniform air film is formed on the outer surface of the shell, separating the high-temperature heat flow from the shell, and performing air film cooling;

[0036] S4, the sensor detects the increase and decrease data of the heat flow inside the cooling chamber and transmits it to the coolant drive pump and the transmission unit respectively;

[0037] When the heat flux increases, the coolant drive pump drives the coolant storage chamber to increase the supply of coolant, and the transmission unit drives the flow splitter core to move towards the head direction, enhancing the impingement cooling intensity at the shell head; when the heat flux decreases, the coolant drive pump drives the coolant storage chamber to reduce the supply of coolant, and the transmission unit drives the flow splitter core to move towards the tail direction, reducing the impingement cooling intensity at the shell head.

[0038] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0039] 1. The hypersonic leading edge combined cooling structure of the present invention that can cope with spatio-temporally non-uniform heat flux includes a diverging part, a structural part, a rear cover plate, and a flow splitter core. Through the discrete arrangement of the diverging parts and setting different porosities for the diverging parts at different positions, a reasonable non-uniform coolant distribution matching the aerodynamic heat distribution of the hypersonic leading edge can be achieved within a large area. In the present invention, the porosities of the N diverging parts from the head to the tail decrease in sequence. The larger the porosity, the more the coolant distribution, thus solving the technical problems of insufficient cooling at the head and excessive cooling downstream that are prone to occur in space.

[0040] 2. The hypersonic leading edge combined cooling system of the present invention that can cope with spatio-temporally non-uniform heat flux includes a combined cooling structure, a coolant unit, a sensor, and a transmission unit; by controlling the moving direction of the flow splitter core along the axis through the transmission system and controlling the supply of coolant in the coolant storage chamber by the coolant drive pump, the impingement cooling intensity on the inner surface can be adjusted at any time, the cooling effect can be dynamically adjusted, and non-uniform cooling in time can be achieved to meet the immediate and active cooling under different flight states.

[0041] 3. The hypersonic leading edge combined cooling method of the present invention that can cope with spatio-temporally non-uniform heat flux, through the combined action of various cooling mechanisms such as impingement cooling on the inner surface of the shell, diverging cooling of the diverging part, and film cooling on the outer surface of the shell, has high cooling efficiency and small coolant consumption: realizes the full utilization of the coolant heat sink, saves the coolant consumption, and reduces the weight of the thermal protection system.

[0042] 4. The hypersonic leading edge combined cooling structure of the present invention that can cope with spatio-temporally non-uniform heat flux, wherein the diverging part and the structural part are detachably connected. During repeated mission execution, the combined cooling structure can be quickly scanned and detected, and the diverging parts with ablation or cracks can be found and disassembled and replaced in time. It has strong reusability and a short maintenance cycle. Description of the Drawings

[0043] Figure 1 It is a schematic cross-sectional view of an embodiment of the hypersonic leading edge combined cooling structure of the present invention that can cope with spatio-temporally non-uniform heat flux;

[0044] Figure 23D schematic diagram of an embodiment of the hypersonic leading edge combined cooling structure capable of coping with spatio-temporally non-uniform heat flux according to the present invention;

[0045] Figure 3 Schematic diagram of the principle of an embodiment of the hypersonic leading edge combined cooling method capable of coping with spatio-temporally non-uniform heat flux according to the present invention;

[0046] Description of reference numerals:

[0047] 11. Divergent part; 12. First structural part; 13. Second structural part; 14. Third structural part; 15. Rear cover plate; 16. Coolant inlet; 17. Coolant diversion channel; 18. Coolant delivery channel; 19. Diversion core; 20. Elastic sealing ring. Detailed implementation manners

[0048] The present invention will be further described below in conjunction with the drawings and embodiments.

[0049] The hypersonic leading edge combined cooling structure capable of coping with spatio-temporally non-uniform heat flux according to the present invention, as Figure 1 , Figure 2 shown, includes a housing, a rear cover plate 15, N diversion cores 19 and an elastic sealing ring 20.

[0050] The housing includes N divergent parts 11 and N structural parts, N≥3, and in this embodiment, N = 3. The 3 divergent parts 11 and the 3 structural parts are alternately connected and arranged. The connection between the divergent part 11 and the structural part is detachable, specifically adhesive bonding with high-temperature resistant sealant or mechanical connection with bolts. The inner diameters of the 3 divergent parts 11 and the 3 structural parts increase in sequence from the head to the tail.

[0051] The 3 divergent parts 11 are arranged in a discrete manner. One of the divergent parts 11 is arranged at the head of the housing, which is a hollow structure with one end closed and one end open, and the open end faces the inner side of the housing; the other two divergent parts 11 are hollow structures with both ends open. The divergent part 11 is made of high-temperature resistant material, produced by sintering of high-temperature resistant material particles or 3D printing, such as ultra-high temperature ceramics, ceramic matrix composites, and superalloys. The side wall of the divergent part 11 is a porous medium structure, and the porous medium is a material with a large number of pores inside.

[0052] The porosity of the 3 divergent parts 11 decreases in sequence from the head to the tail; the higher the porosity, the smaller the flow resistance, enabling more coolant to flow out through the divergent part 11 at the head, realizing a reasonable coolant distribution matching the external non-uniform aerodynamic thermal environment, and improving the overall cooling efficiency and cooling uniformity of the leading edge of the hypersonic vehicle.

[0053] The three structural parts are hollow structures with openings at both ends. The three structural parts are the first structural part 12, the second structural part 13, and the third structural part 14 respectively. The rear end of the third structural part 14 is connected to the rear cover plate 15. The space enclosed by the rear cover plate 15, the diverging part 11, and the structural parts is the cooling cavity.

[0054] A coolant inlet 16 is axially provided at the center of the rear cover plate 15. The rear cover plate 15 is processed with a heat-insulating material having a low thermal conductivity to prevent a large amount of heat flow invading from the leading edge from being transported to the rear structure system of the aircraft through the rear cover plate 15, separating the leading edge of the hypersonic aircraft that requires active thermal protection from the rear structure, and giving full play to the active thermal protection function of the leading edge combined cooling structure.

[0055] The three flow-dividing cores 19 are the first flow-dividing core, the second flow-dividing core, and the third flow-dividing core respectively, and are sequentially arranged at intervals coaxially in the cooling cavity for axial movement. A coolant flow-dividing channel 17 is formed between the first flow-dividing core and the second flow-dividing core, and between the second flow-dividing core and the third flow-dividing core respectively. The two coolant flow-dividing channels 17 respectively correspond to the first structural part 12 and the second structural part 13 one by one. Axially penetrating coolant main channels are provided on the three flow-dividing cores 19. The inlet of the coolant main channel of the flow-dividing core 19 close to the rear cover plate 15 is communicated with the coolant inlet 16 for inputting coolant, and the outlet of the coolant main channel of the flow-dividing core 19 close to the head of the housing faces the diverging part 11 at the head.

[0056] A coolant delivery channel 18 is formed between the outer side wall of the flow-dividing core 19 and the inner side walls of the diverging part 11 and the structural parts. The flow area of the coolant delivery channel 18 at the head of the housing is larger than that of the coolant flow-dividing channel 17, and the flow area of the coolant flow-dividing channel 17 decreases sequentially from the head to the tail of the housing. By setting different flow areas, the intensity of impingement cooling at different positions can be adjusted.

[0057] An elastic sealing ring 20 is sleeved on one end of the flow-dividing core 19 close to the rear cover plate 15, and the elastic sealing ring 20 is connected to the rear cover plate 15 for sealing connection by cooperating with expansion and contraction when the flow-dividing core 19 moves axially.

[0058] The present invention further includes a hypersonic leading edge combined cooling system capable of coping with spatio-temporally non-uniform heat flux, including a combined cooling structure, a coolant unit, a sensor, and a transmission unit;

[0059] The combined cooling structure adopts the above-mentioned hypersonic leading edge combined cooling structure capable of coping with spatio-temporally non-uniform heat flux;

[0060] The sensor is installed inside the cooling cavity for detecting the data of the increase and decrease of the heat flux inside the cooling cavity;

[0061] The coolant unit includes a coolant storage chamber and a coolant driving pump;

[0062] Coolant is stored in the coolant storage chamber; the coolant is a fluid coolant, such as a gas coolant or a liquid coolant; the gas coolant is the cold air extracted from the tail of the hypersonic vehicle, and the liquid coolant is the cooling water carried by the hypersonic vehicle itself.

[0063] The input end of the coolant driving pump is connected to the sensor, and the output end of the coolant driving pump is connected to the input end of the coolant storage chamber, which is used to drive the coolant storage chamber to transport the coolant and adjust the supply amount of the coolant supplied by the coolant storage chamber according to the heat flux increase and decrease data;

[0064] The output end of the coolant storage chamber is connected to the coolant inlet 16 on the rear cover plate 15, which is used to transport the coolant into the cooling cavity;

[0065] The input end of the transmission unit is connected to the sensor, which is used to receive and process the heat flux increase and decrease data. The output end of the transmission unit is connected to the flow dividing core 19, which is used to drive the flow dividing core 19 to move axially and actively adjust the axial movement direction of the flow dividing core 19 according to the heat flux increase and decrease data.

[0066] The present invention also provides a hypersonic leading edge combined cooling method capable of coping with spatio-temporal non-uniform heat flux, based on the above-mentioned hypersonic leading edge combined cooling system capable of coping with spatio-temporal non-uniform heat flux, as Figure 3 shown, a shock wave surface is formed outside the head of the hypersonic vehicle, and the cooling method includes the following steps:

[0067] S1. Impingement cooling: The coolant driving pump drives the coolant storage chamber to transport the coolant, and the coolant flows into the coolant main channel in the cooling cavity through the coolant inlet 16;

[0068] The coolant flows along the coolant main channel, and part of the coolant flows out from the outlet of the coolant main channel to form impingement cooling on the diverging part 11 located at the head of the housing; the remaining part of the coolant is shunted to the coolant delivery channel 18 through the coolant shunt channel 17 to form impingement cooling on the inner surfaces of the diverging part 11 and the structural part;

[0069] S2. Divergent cooling: The coolant is subjected to divergent cooling through N diverging parts 11; the porosity of each discretely arranged diverging part 11 is different, and the coolant can be redistributed in a large range. At the head where the aerodynamic heat and force environment is more severe, by arranging the diverging part 11 with a larger porosity, the coolant distribution amount at this place is increased, and a reasonable coolant distribution matching the spatio-temporal non-uniform heat flux is achieved;

[0070] S3. Film cooling: Since the pore structure of the porous medium in the divergence part 11 is tiny and densely distributed, after the coolant flows out of the divergence part 11, a uniform gas film is formed on the outer surface of the housing, separating the high-temperature mainstream from the housing and further enhancing the film cooling effect.

[0071] S4. The sensor detects the data of the increase and decrease of the heat flux inside the cooling cavity and transmits it to the coolant drive pump and the transmission unit respectively.

[0072] When the heat flux increases, the coolant drive pump drives the coolant storage chamber to increase the supply of coolant, and the transmission unit drives the flow dividing core 19 to move towards the head direction to enhance the impingement cooling intensity of the housing head. When the heat flux decreases, the coolant drive pump drives the coolant storage chamber to reduce the supply of coolant, and the transmission unit drives the flow dividing core 19 to move towards the tail direction to reduce the impingement cooling intensity of the housing head. The coolant unit and the transmission unit actively adjust the impingement cooling intensity to effectively cope with the non-uniform heat flux in time.

[0073] After the hypersonic vehicle completes a mission, the combined cooling structure is scanned and detected, and the divergence part 11 with ablation and cracks is disassembled and replaced.

[0074] In the embodiment of the present invention, multiple cooling mechanisms such as impingement cooling on the inner surface of the hypersonic leading edge structure, transpiration cooling in the structural layer, and film cooling on the outer surface of the structure are combined and act together. By setting the divergence part 11 with different porosities and the coolant delivery channels with different flow areas, and cooperating with the use of active control units such as the coolant unit and the transmission system, it can cope with the non-uniform aerodynamic thermal environment in space and time, and has the advantages of light weight, high efficiency, suitability for large-area use, and convenience for rapid maintenance between adjacent flights.

Claims

1. A hypersonic leading edge combined cooling structure capable of coping with non-uniform heat flow in time and space, characterized in that: It comprises a shell, a rear cover plate (15) and N diverter cores (19); The shell comprises N divergent portions (11) and N structural portions, wherein N is greater than or equal to 3; the N divergent portions (11) and the N structural portions are alternately connected and arranged; one of the divergent portions (11) is arranged at the head of the shell, and is a hollow structure with one end closed and the other end open, and the open end faces the inside of the shell; the remaining N-1 divergent portions (11) and the N structural portions are hollow structures with two ends open; The side wall of the diverging portion (11) is a porous medium structure, and the porosity of the N diverging portions (11) decreases from the head to the tail of the shell; The rear cover plate (15) is arranged at the rear end of the structural part located at the rear of the shell, and is surrounded by the N diverging parts (11) and the N structural parts to form a cooling cavity; a coolant inlet (16) is opened in the central axial direction of the rear cover plate (15); N of the flow-dividing cores (19) are coaxially arranged in the cooling cavity in sequence and spaced apart, and a radial coolant flow-dividing channel (17) is formed between two adjacent flow-dividing cores (19); N-1 coolant flow-dividing channels (17) correspond one-to-one to the first N-1 structural parts respectively; The N flow-dividing cores (19) are respectively provided with axially penetrating coolant main channels, and the inlet of the coolant main channel of the flow-dividing core (19) close to the rear cover plate (15) is connected to the coolant inlet (16) for inputting coolant; A coolant delivery channel (18) is formed between the outer wall of the diverter core (19) and the inner wall of the diverging portion (11) and the structural portion; the flow area of ​​the coolant delivery channel (18) located at the head of the shell is larger than the flow area of ​​the coolant diverter channel (17), and the flow area of ​​the coolant diverter channel (17) decreases from the head to the tail of the shell.

2. The hypersonic leading edge combined cooling structure capable of coping with time-space non-uniform heat flow according to claim 1, characterized in that: It also includes an elastic sealing ring (20) sleeved on one end of the flow dividing core (19) close to the rear cover plate (15), and the elastic sealing ring (20) is connected to the rear cover plate (15) and is used to cooperate with the expansion and contraction when the flow dividing core (19) moves in the axial direction to achieve a sealing connection.

3. The hypersonic leading edge combined cooling structure capable of coping with time-space non-uniform heat flow according to claim 2, characterized in that: N=3, the three structural parts are respectively a first structural part (12), a second structural part (13) and a third structural part (14); the third structural part (14) is connected to the rear cover plate (15); The three flow-dividing cores (19) are respectively a first flow-dividing core, a second flow-dividing core and a third flow-dividing core; a coolant flow-dividing channel (17) is respectively formed between the first flow-dividing core and the second flow-dividing core, and between the second flow-dividing core and the third flow-dividing core.

4. The hypersonic leading edge combined cooling structure capable of coping with time-space non-uniform heat flow according to any one of claims 1 to 3, characterized in that: The diverging portion (11) and the structural portion are detachably connected.

5. The hypersonic leading edge combined cooling structure capable of coping with time-space non-uniform heat flow according to claim 4, characterized in that: The diverging portion (11) and the structural portion are bonded with high temperature resistant sealant or connected with bolts.

6. The hypersonic leading edge combined cooling structure capable of coping with time-space non-uniform heat flow according to claim 5, characterized in that: The diverging portion (11) is made by sintering high temperature resistant material particles or by 3D printing.

7. A hypersonic leading edge combined cooling system capable of coping with time-space non-uniform heat flow, comprising a combined cooling structure, a coolant unit, a sensor and a transmission unit; characterized in that: The combined cooling structure adopts the hypersonic leading edge combined cooling structure capable of coping with time-space non-uniform heat flow as described in any one of claims 1 to 6; The sensor is installed inside the cooling cavity and is used to detect the increase and decrease data of the heat flow inside the cooling cavity; The coolant unit includes a coolant storage chamber and a coolant drive pump; The coolant storage chamber stores coolant; The input end of the coolant driving pump is connected to the sensor, and the output end of the coolant driving pump is connected to the input end of the coolant storage chamber, for driving the coolant storage chamber to transport the coolant, and adjusting the supply amount of the coolant supplied by the coolant storage chamber according to the heat flow increase and decrease data; The output end of the coolant storage chamber is connected to the coolant inlet (16) on the rear cover plate (15) for conveying the coolant into the cooling cavity; The input end of the transmission unit is connected to the sensor for receiving and processing the heat flow increase and decrease data, and the output end of the transmission unit is connected to the shunt core (19) for driving the shunt core (19) to move axially and actively adjusting the direction of the shunt core (19) moving axially according to the heat flow increase and decrease data.

8. The hypersonic leading edge combined cooling system capable of coping with time-space non-uniform heat flow according to claim 7, characterized in that: The coolant is a gas coolant or a liquid coolant.

9. A hypersonic leading edge combined cooling method capable of coping with time-space non-uniform heat flow, based on the hypersonic leading edge combined cooling system capable of coping with time-space non-uniform heat flow according to claim 7 or 8, characterized in that: The following steps are involved: S1, impact cooling: the coolant driving pump drives the coolant storage chamber to transport the coolant, and the coolant flows into the coolant main channel in the cooling chamber through the coolant inlet (16); The coolant flows along the coolant main channel, and part of the coolant flows out from the outlet of the coolant main channel to form impact cooling on the diverging portion (11) located at the head of the shell; the remaining part of the coolant is diverted to the coolant delivery channel (18) through the coolant diverting channel (17), and forms impact cooling on the inner surface of the diverging portion (11) and the structural portion; S2, divergent cooling: the coolant is divergently cooled through N divergent parts (11); S3, air film cooling: after the coolant flows out of the diverging part (11), a uniform air film is formed on the outer surface of the shell, separating the high-temperature heat flow from the shell, and performing air film cooling; S4, the sensor detects the increase and decrease data of the heat flow inside the cooling chamber and transmits it to the coolant drive pump and the transmission unit respectively; When the heat flow increases, the coolant driving pump drives the coolant storage chamber to increase the supply of coolant, and the transmission unit drives the diverter core (19) to move toward the head direction, thereby increasing the impact cooling intensity of the shell head; when the heat flow decreases, the coolant driving pump drives the coolant storage chamber to reduce the supply of coolant, and the transmission unit drives the diverter core (19) to move toward the tail direction, thereby reducing the impact cooling intensity of the shell head.

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