Alternating ablation / alternating injection thermal protection structure, design method and vehicle

Abstract

The application discloses an alternating injection / ejection heat protection structure, a design method and an aircraft, and relates to the field of sweat cooling heat protection structures. The alternating injection / ejection heat protection structure comprises a main body, a plurality of independent partitions are sequentially arranged along the direction of the airflow, and a partition is arranged between adjacent independent partitions to completely separate them. Each independent partition comprises, from the outside to the inside, an ejection control layer, an intermediate layer, an injection control layer and a cooling cavity. The injection control layer and the ejection control layer are alternately arranged along the direction of the airflow by a porous structure and a conventional structure, and the intermediate layer is composed of a conventional structure. A plurality of coolant delivery channels are arranged in the main body and are isolated from each other. Each channel is in communication with the cooling cavity in the corresponding independent partition. The application realizes accurate control of the alternating injection and ejection of the coolant according to the heat partition of the outer surface of the structure, optimizes the distribution of the coolant, and improves the heat protection efficiency. The application provides a solution for the heat protection of the aircraft surface under the condition of uneven distribution of thermal and force loads.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of transpiration cooling thermal protection structure, more particularly, to an alternating injection / alternating injection thermal protection structure, a design method and an aircraft. BACKGROUND

[0002] The super-speed aircraft is developing towards long time, high Mach number and repeatability, which puts forward higher requirements for thermal protection.

[0003] The widely used semi-passive ablation thermal protection will change the shape of the aircraft during long-time continuous heating, so it is necessary to develop an active thermal protection system with stronger cooling performance.

[0004] Transpiration cooling uses the way of biological transpiration cooling, uses the carried cooling medium to overflow on the heated surface to form a uniform film to protect the aircraft, and the cooling medium exchanges heat with the structure in the porous medium to carry away part of the heat.

[0005] However, due to the extremely uneven distribution of heat and force load on the surface of the aircraft, the heat flux in the stagnation point area is much higher than that in other areas, and the pressure in this area is the highest, resulting in the least supply of coolant in this area.

[0006] Therefore, how to realize the on-demand supply of coolant is a problem to be solved by the technical personnel in the field. SUMMARY

[0007] Therefore, the purpose of the present application is to provide an alternating injection / alternating injection thermal protection structure, a design method and an aircraft, which effectively realizes the on-demand supply of coolant and provides a solution for thermal protection under the condition of uneven distribution of heat and force load on the surface of the aircraft.

[0008] In order to achieve the above-mentioned purpose, the present application provides the following technical scheme:

[0009] An alternating injection / alternating injection thermal protection structure comprises a main body, the main body is provided with a plurality of independent partitions in sequence along the direction of incoming flow according to the heating condition, and a partition is arranged between two adjacent independent partitions to completely separate them.

[0010] Each of the independent partitions is sequentially provided from outside to inside with an injection control layer, an intermediate layer, an ejection control layer and a cooling cavity, the injection control layer and the ejection control layer are alternately arranged along the flow direction by a porous structure and a conventional structure, and the intermediate layer is composed of a conventional structure;

[0011] The main body is provided with a plurality of coolant delivery channels which are isolated from each other and are used to pass in coolant, and each of the coolant delivery channels is individually communicated with the cooling cavity in the corresponding independent partition.

[0012] Preferably, the ejection control layer comprises two first porous sections which are arranged at intervals along the flow direction, and a first conventional section is arranged between the two first porous sections, so that the ejection control layer forms two ejection zones and one closed zone.

[0013] The first porous section is composed of a porous structure, and the first conventional section is composed of a conventional structure.

[0014] Preferably, the injection control layer comprises a second porous section and a second conventional section which are sequentially arranged, so that the injection control layer forms one injection zone and one closed zone.

[0015] The second porous section is composed of a porous structure, and the second conventional section is composed of a conventional structure.

[0016] Preferably, the injection zone is arranged with a first injection inlet, and the two ejection zones are respectively arranged with a first ejection port and a second ejection port.

[0017] A first flow path is formed between the first injection inlet and the first ejection port, and a second flow path is formed between the first injection inlet and the second ejection port, and the lengths of the first flow path and the second flow path are arranged according to the conditions at the first ejection port and the second ejection port.

[0018] Preferably, the materials adopted by the ejection control layer, the intermediate layer and the injection control layer are high-temperature alloys or ceramics.

[0019] Preferably, the porous structure is sintered from high-temperature alloy powder or ceramic powder.

[0020] Preferably, the coolant is gaseous coolant or liquid coolant.

[0021] Preferably, a plurality of the coolant delivery channels are coaxially arranged.

[0022] A design method of an alternating ejection / alternating injection thermal protection structure, comprising:

[0023] According to the heating condition of the outer surface of the structure, the structure is divided into N independent partitions which are isolated from each other, and a metal partition plate is arranged between adjacent independent partitions to completely separate them;

[0024] A matching build material is selected, and an injection control layer, an intermediate layer, an injection control layer and a cooling cavity are built from outside to inside in each independent partition;

[0025] In the injection control layer, a porous structure, a conventional structure and a porous structure are arranged in sequence along the flow direction to form two injection zones and one closed zone, and an injection port is arranged in each injection zone.

[0026] In the injection control layer, a porous structure, a conventional structure and a porous structure are arranged in sequence along the flow direction to form two injection zones and one closed zone, and an injection port is arranged in each injection zone.

[0027] All the conventional structures are arranged in the intermediate layer.

[0028] A plurality of coaxially arranged and mutually isolated coolant delivery channels are built in the structure, and each coolant delivery channel corresponds to a cooling cavity.

[0029] A kind of aircraft, comprising the heat protection structure of the above-mentioned alternate injection / alternate injection.

[0030] The alternate injection / alternate injection heat protection structure provided by the application divides the structure into a plurality of independent partitions according to the heating condition along the flow direction, completely separates adjacent independent partitions by a partition plate, prevents mutual flow between different independent partitions, supplies coolant to the corresponding independent partition as needed through a separate coolant delivery channel, realizes on-demand supply of coolant, and provides a solution for heat protection under uneven thermal and mechanical load distribution on the surface of the aircraft.

[0031] The further scheme provided by the application can achieve at least one of the following beneficial technical effects:

[0032] By adjusting the alternate arrangement mode of the porous structure and the conventional structure, the distance of the first flow path and the second flow path is effectively adjusted, so that the path with severe heating at the injection port can be reduced in distance, so that more coolant flows to the injection port with more severe heating, and the on-demand distribution of coolant is further realized.

[0033] With the coolant flowing out of the injection port, the coolant flows downstream to form a layer of gas film wrapped outside the closed zone of the injection control layer, reducing aerodynamic heating, and at the same time, the coolant convectively exchanges heat with the inside of the closed zone during its movement along the flow path, further reducing the temperature of the closed zone. BRIEF DESCRIPTION OF DRAWINGS

[0034] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description only represent some of the embodiments of the present application, and for those skilled in the art, other drawings can be obtained without creative effort based on the provided drawings.

[0035] Figure 1 The figure is a structural schematic diagram of the thermal protection structure in the embodiment.

[0036] The reference signs include:

[0037] 1, main body; 2, independent partition; 3, partition; 4, injection control layer; 5, intermediate layer; 6, injection control layer; 7, cooling cavity; 8, coolant delivery channel; 9, closed area; 10, first injection port; 11, first injection port; 12, second injection port; 13, first flow path; 14, second flow path. DETAILED DESCRIPTION

[0038] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments only represent some of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative effort belong to the scope of protection of the present application.

[0039] Unless otherwise defined, the technical terms or scientific terms used in the present application should be understood as the common meanings understood by those skilled in the art. The terms "first", "second" and similar words used in the present application do not represent any order, number or importance. The terms "connected" or "connected" and similar words are not limited to physical or mechanical connections, but can include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to represent relative positional relationships, and when the absolute positions of the described objects are changed, the relative positional relationships can also be changed accordingly. The embodiments of the present application disclose an alternating injection / alternating injection thermal protection structure, a design method and a spacecraft.

[0040] The core of the present application is to provide an alternating injection / alternating injection thermal protection structure.

[0041] Another core of the present application is to provide a design method of the alternating injection / alternating injection thermal protection structure.

[0042] Still another core of the present application is to provide a spacecraft comprising the above-mentioned alternating injection / alternating injection thermal protection structure.

[0043] Please refer to Figure 1 .

[0044] The heat protection structure of the present application comprises a main body 1, which is divided into a plurality of independent zones 2 along the flow direction according to the heat receiving condition, and a partition 3 is arranged between two adjacent independent zones 2 to completely separate them.

[0045] Each independent zone 2 is sequentially provided with an injection control layer 6, an intermediate layer 5, an ejection control layer 4 and a cooling cavity 7 from outside to inside, and the injection control layer 6 and the ejection control layer 4 are alternately arranged by porous structure and conventional structure along the flow direction, and the intermediate layer 5 is composed of conventional structure.

[0046] A plurality of coolant delivery channels 8 are arranged in the main body 1 to deliver coolant, and each coolant delivery channel 8 is individually communicated with the cooling cavity 7 in the corresponding independent zone 2.

[0047] Specifically, the main body 1 is divided into N independent zones 2 according to the heat receiving condition of the structure surface, and the plurality of independent zones are sequentially divided into first zone, second zone, …, Nth zone according to the flow direction from the leading edge, and the two adjacent independent zones 2 are completely separated by the partition 3 to prevent mutual flow between different independent zones 2.

[0048] Each independent zone 2 is sequentially provided with an injection control layer 6, an intermediate layer 5, an ejection control layer 4 and a cooling cavity 7 from outside to inside, and the main body 1 is provided with a plurality of coolant delivery channels 8 for delivering coolant, and each coolant delivery channel 8 is respectively matched with the cooling cavity 7.

[0049] The cooling cavity 7 in each independent zone 2 is matched with a separate coolant delivery channel 8, i.e. one-to-one arrangement, and the coolant enters the cooling cavity 7 through the coolant delivery channel 8, and the coolant is only in the independent zone 2 through the partition 3.

[0050] The injection control layer 6 and the ejection control layer 4 in each independent zone 2 are alternately arranged by porous structure and conventional structure along the flow direction, and the intermediate layer 5 is composed of conventional structure, which controls the injection and ejection of the coolant by alternately arranging the porous structure and the conventional structure.

[0051] The heat protection structure of the present application divides the structure into a plurality of independent zones 2 along the flow direction according to the heat receiving condition, completely separates the adjacent independent zones 2 by the partition 3 to prevent mutual flow between different independent zones 2, supplies the coolant to the corresponding independent zone 2 by the separate coolant delivery channel 8 to achieve the on-demand supply of the coolant, and provides a solution for the heat protection of the uneven heat and force load distribution on the surface of the aircraft.

[0052] The alternating injection / ejection thermal protection structure provided by the present application will be described in more detail below with reference to the accompanying drawings and specific embodiments.

[0053] In one specific embodiment, with reference to Figure 1 , the ejection control layer 4 comprises two first porous sections arranged at intervals along the flow direction, and a first normal section arranged between the two first porous sections, so that the ejection control layer 4 forms two ejection zones and one closed zone 9; the first porous sections are composed of porous structures, and the first normal section is composed of normal structures.

[0054] Specifically, the ejection control layer 4 is arranged with porous structures, normal structures, and porous structures in sequence along the flow direction to form two ejection zones and one closed zone 9, the ejection control layer 4 can guide the coolant out through the ejection zones, and the closed zone 9 can prevent the disordered flow of the coolant, thereby achieving effective control of the ejection of the coolant.

[0055] On the basis of any one of the above embodiments, with reference to Figure 1 , the injection control layer 6 comprises a second porous section and a second normal section arranged in sequence, so that the injection control layer 6 forms one injection zone and one closed zone 9; the second porous section is composed of porous structures, and the second normal section is composed of normal structures.

[0056] Specifically, the injection control layer 6 is arranged with porous structures and normal structures in sequence along the flow direction to form one injection zone and one closed zone 9, the injection control layer 6 can inject the coolant into the required area in a targeted manner, the closed zone 9 avoids the leakage and unnecessary diffusion of the coolant, and effective control of the injection of the coolant is achieved.

[0057] On the basis of any one of the above embodiments, with reference to Figure 1 , the injection zone is arranged with a first injection port 10, and the two ejection zones are respectively arranged with a first ejection port 11 and a second ejection port 12; a first flow path 13 is formed between the first injection port 10 and the first ejection port 11, a second flow path 14 is formed between the first injection port 10 and the second ejection port 12, and the lengths of the first flow path 13 and the second flow path 14 are arranged according to the conditions at the first ejection port 11 and the second ejection port 12.

[0058] Specifically, taking the first zone as an example, the first injection port 10 is formed in the injection zone, the first injection port 11 and the second injection port 12 are respectively formed in the two injection zones, the coolant enters the cooling cavity through the coolant conveying channel 8, and enters the porous structure layer through the first injection port 10, and is driven by pressure to flow to the first injection port 11 and the second injection port 12 in the porous structure layer. As shown in the figure, the heating condition of the first injection port 11 is more serious than that of the second injection port 12, the first flow path 13 is formed between the first injection port 10 and the first injection port 11, and the second flow path 14 is formed between the first injection port 10 and the second injection port 12. Because the heating condition of the first injection port 11 is more serious, the first flow path 13 is arranged alternately with the conventional structure through the porous structure, so that the first flow path 13 is shorter than the second flow path 14, so that the coolant flows to the first injection port 11 through the first flow path 13 more, thereby realizing the adjustment of the coolant flow. Of course, if the second injection port 12 is seriously heated, the second flow path 14 is arranged to be shorter than the first flow path 13, and the number of the second injection port 12 is arranged according to the requirement.

[0059] It also needs to be explained that in the process of the coolant flowing along the flow path, on the one hand, the coolant flowing out of the injection port flows downstream, thereby forming a layer of gas mold on the structure surface outside the closed zone of the injection control layer 4, reducing the aerodynamic heating of the region, and on the other hand, the coolant is in counterflow heat exchange with the inner side of the closed zone 9 in the process of flowing along the flow path to the injection port, thereby reducing the temperature of the closed zone 9. Thus, the cooling of the closed zone is realized.

[0060] In a specific embodiment provided in the application, the materials of the injection control layer 4, the intermediate layer 5 and the injection control layer 6 are high-temperature alloys or ceramics.

[0061] Specifically, the high-temperature alloy has good high-temperature strength and oxidation resistance, and can maintain structural stability in a high-temperature environment; the ceramic material has excellent heat insulation performance and chemical stability.

[0062] It needs to be explained that the high-temperature alloy refers to a kind of metal material taking iron, nickel and cobalt as the base, which can work at a high temperature above 600 DEG C and under certain stress for a long time, has excellent high-temperature strength, good oxidation resistance and heat corrosion resistance, good fatigue performance, fracture toughness and other comprehensive performance, and is also called "super alloy". It is mainly applied in the fields of aerospace and energy.

[0063] Further, the porous structure is sintered from high-temperature alloy powder or ceramic powder. Alternatively, the porous structure can also be made of other materials with high-temperature resistance and certain porosity.

[0064] On the basis of any one of the above embodiments, the coolant is a gaseous coolant or a liquid coolant.

[0065] On the basis of any one of the above embodiments, the plurality of coolant delivery channels 8 are coaxially arranged. Figure 1

[0066] Specifically, the plurality of coolant delivery channels 8 are coaxially arranged in the main body 1, and are sequentially sleeved and respectively extend into the corresponding cooling cavities. The outlets of the coolant delivery channels 8 are connected with the partition plates 3, so as to further ensure the isolation between the adjacent independent partitions 2. The different coolant delivery channels 8 are isolated from each other, and the flow and pressure are separately controlled. In this way, the supply of the coolant can be accurately adjusted according to the thermal and force load conditions of each independent partition.

[0067] The coolant delivery channels 8 are composed of high-temperature-resistant pipes, which can be selected from high-temperature alloys or ceramic pipes. The inner walls of the pipes are smooth to reduce the resistance of the coolant flow.

[0068] The coaxially arranged coolant delivery channels 8 can save space and make the structure more compact. The delivery channels are composed of multiple layers of pipes, which are independent and well sealed from each other. The inner and outer pipes can respectively deliver coolants with different pressures and flow rates to meet the needs of different independent partitions. The materials of the pipes can also be selected from high-temperature-resistant materials such as high-temperature alloys or ceramics.

[0069] On the basis of any one of the above embodiments, the partition plates 3 are usually made of metal materials such as stainless steel, which have good strength and sealing performance. The function of the partition plates is to prevent the coolant in different independent partitions from flowing into each other, and to ensure that the supply and control of the coolant in each partition are independent. The partition plates are tightly connected with the edges of the independent partitions, and are sealed by welding or sealing glue, etc. to ensure complete isolation between the partitions.

[0070] ​The implementation principle of the heat protection structure of the alternative injection / alternative injection embodiment of the present application is as follows: the heat protection structure can effectively control the injection and injection of the coolant according to the uneven distribution of the thermal and force loads on the surface of the aircraft through the partition design and the alternative arrangement of the porous structure and the conventional structure. The independent partitions avoid the mutual interference of the coolants in different regions, the coolant supply of each partition can be independently adjusted by the coolant delivery channel 8, and the porous structure realizes the overflow and circulation of the coolant on demand. Compared with the prior art, the structure solves the problem that the coolant is difficult to supply on demand in space, improves the cooling efficiency, reduces the waste of the coolant, and provides a more effective solution for the heat protection of the aircraft in a complex thermal and force load environment. By arranging the coolant delivery channel 8 coaxially, the space occupied by the structure is reduced and the integration of the structure is improved on the premise that the coolant supply of each independent partition is independently controlled. This arrangement makes the heat protection structure more suitable for the aircraft with limited space, and also facilitates the installation and maintenance of the coolant delivery system, further improving the practicability and reliability of the heat protection structure.

[0071] The design method of the alternative injection / alternative injection heat protection structure provided by the present application comprises the following steps:

[0072] S1, according to the heating condition of the outer surface of the structure, the structure is divided into N independent partitions which are isolated from each other, and a metal partition is arranged between adjacent independent partitions to completely separate them;

[0073] S2, selecting a matched construction material and constructing the injection control layer 4, the intermediate layer 5, the injection control layer 6 and the cooling cavity 7 from outside to inside in each independent partition;

[0074] S3, in the injection control layer 4, the porous structure, the conventional structure and the porous structure are arranged in the flow direction in sequence to form two injection zones and one closed zone, and the injection port is arranged in each injection zone;

[0075] S4, in the injection control layer 6, the porous structure and the conventional structure are arranged in the flow direction in sequence to form one injection zone and one closed zone, and the injection port is arranged in the injection zone;

[0076] S5, the conventional structure is arranged in the intermediate layer 5;

[0077] S6, a plurality of coaxially arranged and mutually isolated coolant delivery channels 8 are constructed in the structure, and each coolant delivery channel 8 corresponds to one cooling cavity.

[0078] Specifically, in step S1, when the partition is carried out, the thermal and force load distribution of the aircraft surface needs to be analyzed and measured in detail. Thermal sensors, pressure sensors and other devices can be used to obtain thermal flow and pressure data at different positions. According to these data, the structure is reasonably divided into multiple independent partitions 2. The metal partition 3 is usually made of metal materials such as stainless steel, which is installed between adjacent partitions and fixed by welding or bolt connection to ensure complete isolation between partitions. And multiple independent partitions 2 can be divided into first zone, second zone, …, Nth zone according to the direction of incoming flow, which is convenient for marking different independent partitions 2.

[0079] In step S2, the construction material can be selected according to the actual needs, such as high-temperature alloy or ceramic. When building the injection control layer 4, first make the first porous section and the first regular section, and assemble them according to the design requirements. The second porous section and the second regular section of the injection control layer 6 are also constructed in a similar way. The intermediate layer 5 is entirely constructed with regular structural materials to ensure the stability of the structure. The cooling cavity 7 is designed and manufactured according to the size of the partition and the required amount of coolant.

[0080] In step S3, when arranging the injection control layer 4, the porous structure and the regular structure are installed in sequence. The arrangement of the injection port needs to be optimized according to the thermal and force load conditions to ensure that the coolant can be effectively injected. The injection port can be circular or square in shape, and its size and number are determined according to actual needs.

[0081] In step S4, the arrangement of the injection control layer 6 is similar to that of the injection control layer 4, and the porous structure and the regular structure are installed in sequence. The position and size of the injection port are designed according to the injection requirements of the coolant to ensure that the coolant can be uniformly injected into the injection area.

[0082] In step S5, the intermediate layer 5 is made of regular structural materials such as high-temperature alloy or ceramic, which is machined or cast into the required structure shape, and then installed to ensure the integrity and stability of the intermediate layer.

[0083] In step S6, the coolant delivery channel 8 uses high-temperature alloy or ceramic pipes, and multiple layers of pipes are arranged coaxially together and the sealing between the pipes is ensured. Each delivery channel is connected to the corresponding cooling cavity 7 by welding or sealing connection to ensure smooth delivery of the coolant.

[0084] The design method of the alternating ejecting / alternating injecting thermal protection structure provided above can construct a thermal protection structure adapting to uneven thermal and force load on the surface of the aircraft through scientific and reasonable partition, material selection and structure arrangement. The steps are related to each other, from the partition design to the construction of each layer structure, and to the setting of the coolant delivery channel, which ensures that the thermal protection structure can realize the on-demand supply and effective control of the coolant, improves the thermal protection performance of the aircraft, and is more perfect and effective than the existing design method.

[0085] The present application also provides an aircraft comprising the alternating ejecting / alternating injecting thermal protection structure described above, which can also be designed by the design method of the alternating ejecting / alternating injecting thermal protection structure described above. The thermal protection structure is installed on the outer surface of the aircraft, especially in the regions with uneven thermal and force load, such as the stagnation point region. The main body of the thermal protection structure is fixed to the structural frame of the aircraft by bolt connection or welding, etc., to ensure the stability of the structure. The coolant delivery channel is connected to the coolant storage system of the aircraft, and the coolant is delivered into the cooling cavity 7 of the thermal protection structure by the delivery pump. The rest of the structure of the aircraft is the same as the prior art, which will not be described here.

[0086] Each embodiment in the specification is described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the embodiments can be referred to each other.

[0087] The alternating ejecting / alternating injecting thermal protection structure, the design method and the aircraft provided by the present application are described in detail above. The principles and implementation modes of the present application are described by applying specific examples in this paper. The above description of the embodiments is only used to help understand the method of the present application and its core idea. It should be pointed out that for ordinary skilled in the art, without departing from the principles of the present application, some improvements and modifications can be made to the present application, and these improvements and modifications also fall within the protection scope of the present application.

Claims

1. A thermal protection structure with alternating ejection / alternating injection, characterized in that, Includes a main body (1), which has multiple independent partitions (2) arranged sequentially along the flow direction according to the heating conditions, and a partition (3) is provided between two adjacent independent partitions (2) to completely separate them; Each independent partition (2) is provided with an ejector control layer (4), an intermediate layer (5), an injection control layer (6) and a cooling chamber (7) from the outside to the inside. The injection control layer (6) and the ejector control layer (4) are arranged alternately with porous structure and conventional structure along the incoming flow direction. The intermediate layer (5) is composed of conventional structure. The main body (1) is provided with a plurality of mutually isolated coolant delivery channels (8), which are used to introduce coolant. Each coolant delivery channel (8) is individually connected to the cooling chamber (7) in the corresponding independent partition (2).

2. The thermal protection structure according to claim 1, characterized in that, The ejector control layer (4) includes two first porous sections arranged at intervals along the incoming flow direction, and a first conventional section is provided between the two first porous sections, so that the ejector control layer (4) forms two ejector zones and a closed zone (9). The first porous segment is composed of a porous structure, and the first conventional segment is composed of a conventional structure.

3. The thermal protection structure according to claim 2, characterized in that, The injection control layer (6) includes a second porous section and a second conventional section arranged in sequence, so that the injection control layer (6) forms an injection area and a closed area (9). The second porous section is composed of a porous structure, and the second conventional section is composed of a conventional structure.

4. The alternating ejection / alternating injection thermal protection structure according to claim 3, characterized in that, The injection area is provided with a first injection port (10), and the two ejection areas are respectively provided with a first ejection port (11) and a second ejection port (12). A first flow path (13) is formed between the first injection port (10) and the first ejector port (11), and a second flow path (14) is formed between the first injection port (10) and the second ejector port (12). The lengths of the first flow path (13) and the second flow path (14) are arranged according to the conditions at the first ejector port (11) and the second ejector port (12).

5. The alternating ejection / alternating injection thermal protection structure according to any one of claims 1-4, characterized in that, The ejection control layer (4), the intermediate layer (5), and the injection control layer (6) are made of high-temperature alloys or ceramics.

6. The alternating ejection / alternating injection thermal protection structure according to any one of claims 1-4, characterized in that, The porous structure is formed by sintering high-temperature alloy powder or ceramic powder.

7. The alternating ejection / alternating injection thermal protection structure according to any one of claims 1-4, characterized in that, The coolant is either a gaseous coolant or a liquid coolant.

8. The alternating ejection / alternating injection thermal protection structure according to any one of claims 1-4, characterized in that, Multiple coolant delivery channels (8) are arranged coaxially.

9. A design method for an alternating ejection / alternating injection thermal protection structure, characterized in that, include: Based on the heating conditions of the outer surface of the structure, the structure is divided into N independent partitions that are isolated from each other, and metal partitions are set between adjacent independent partitions to completely separate them. Select matching construction materials and construct an ejector control layer (4), an intermediate layer (5), an injection control layer (6), and a cooling chamber (7) from the outside to the inside in each independent partition; In the ejector control layer (4), a porous structure, a conventional structure, and a porous structure are arranged sequentially along the incoming flow direction to form two ejector zones and a closed zone, and an ejector port is arranged in each ejector zone; In the injection control layer (6), a porous structure and a conventional structure are arranged in sequence along the incoming flow direction to form an injection zone and a closed zone, and an injection port is arranged in the injection zone; The intermediate layer (5) is entirely composed of conventional structures; Multiple coaxially arranged and mutually isolated coolant delivery channels (8) are constructed within the structure, with each coolant delivery channel (8) corresponding to a cooling chamber.

10. An aircraft, characterized in that, Including the alternating ejection / alternating injection thermal protection structure as described in any one of claims 1-8.

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