Convection jet coupling thermal protection system and method suitable for wide-speed-range waverider configuration

Abstract

The invention discloses a convection jet flow coupling thermal protection system and method suitable for a wide-speed-range waverider configuration, and relates to the technical field of hypersonic aircraft thermal protection, the convection jet flow coupling thermal protection system comprises an outer wall surface arranged on the outer surface of a wide-speed-range waverider configuration aircraft, the outer wall surface covers the exterior of an internal structure, and an internal flow supply adjusting assembly is arranged in the internal structure; the internal flow supply adjusting assembly comprises a liquid working medium storage box, a gasification device and an adjusting valve, a nozzle is formed in the head position of the wide-speed-range waverider configuration aircraft, and the nozzle communicates with the adjusting valve. According to the convection jet flow coupling thermal protection system and method suitable for the wide-speed-range waverider configuration, a reverse jet flow thermal protection method is adopted in a head key thermal protection area for heat reduction; heat is transferred to a convective heat transfer pipeline for heat protection by adopting a convective heat transfer heat protection method in a secondary key heat protection area with a small sweepback angle and a high aspect ratio at the tail part; the two areas are matched by arranging an adjusting valve, and effective thermal protection is achieved.

Description

Technical Field

[0001] The present invention relates to the technical field of hypersonic vehicle thermal protection, and in particular to a convective jet coupling thermal protection system and method suitable for a wide speed range waverider configuration. Background Art

[0002] Hypersonic aircraft will be subjected to very serious aerodynamic heating during operation, and certain thermal protection measures need to be taken to ensure that its overall temperature is within a safe range. At present, hypersonic thermal protection methods can be divided into two categories: passive and active. Passive thermal protection methods try to reduce the heat flux density on the surface of the aircraft by increasing the heated area, adding thermal insulation materials, etc., to ensure the stability of the internal temperature. The advantages are simple structure, large area use and good maintenance of the aerodynamic shape. The disadvantages are low heat protection efficiency, limited heat bearing capacity, and inability to work for a long time. The active thermal protection method effectively solves the above-mentioned shortcomings. It requires additional injection of energy or mass to achieve the purpose of heat protection by changing the flow field or thermal field. There are many ways to implement active thermal protection. Here, two methods are introduced specifically according to the degree of relevance to this patent, namely reverse jet and convection cooling methods. Reverse jet is an active flow control technology, which sets a small nozzle in the nose cone or head of a hypersonic aircraft, and ejects high-pressure working fluid in the opposite direction of the incoming flow to counteract the high-speed incoming flow. The purpose of heat protection is achieved by isolating the high-temperature gas by destroying the flow field structure and the high-temperature boundary layer. After the stable flow field is re-formed, a stable low-temperature area will appear around the nozzle, achieving efficient thermal protection in a specific area, and the size of the heat protection area can also be controlled by adjusting parameters such as nozzle pressure and nozzle flow. Convection cooling does not need to destroy the integrity of the aircraft shape. Convection heat exchange pipelines are arranged inside the aircraft structure, especially in the area that is severely heated and adjacent to the surface. After the outer surface is heated, the heat is absorbed by the aircraft wall structure and conducted to the heat exchange pipeline, and then absorbed and transferred by the heat exchange working fluid in the pipeline, so that the outer surface temperature is always maintained at a low level. This method can also achieve different degrees of heat protection effects by controlling parameters such as pressure, flow rate, and flow rate of the cooling working fluid.

[0003] The two heat protection methods of reverse jet and convection cooling have simple structures and can both achieve effective heat protection in local areas of hypersonic aircraft. Different methods can be selected according to actual conditions. However, both methods have the problems of low working fluid utilization, energy and mass waste. The corresponding working fluid is carried inside the aircraft to supply these two heat protection methods. However, the working fluid cannot be reused after completing the corresponding heat protection task, which does not meet the requirements of hypersonic aircraft for extreme space utilization. At the same time, the wide-speed range waverider configuration is an important development direction for future hypersonic aircraft. Its aerodynamic heat conditions are more complicated than those of general hypersonic aircraft. A single thermal protection method can no longer meet the corresponding thermal protection requirements. It is necessary to develop and explore new thermal protection methods suitable for wide-speed range waveriders on the basis of existing thermal protection methods. Summary of the invention

[0004] The purpose of the present invention is to provide a convective jet coupled thermal protection system and method suitable for a wide-speed range waverider configuration, to solve the problems raised in the above-mentioned background technology, and to achieve the reuse of working fluid energy and effective thermal protection in a wide-speed range waverider configuration aircraft.

[0005] To achieve the above-mentioned object, the present invention provides a convective jet coupling thermal protection system suitable for a wide-speed range waverider configuration, comprising an outer wall surface arranged on the outer surface of a wide-speed range waverider configuration aircraft, the outer wall surface covering the outside of an internal structure, an internal flow supply regulating component arranged in the internal structure, the internal flow supply regulating component comprising a liquid working medium storage tank, a gasification device and a regulating valve, A nozzle is arranged at the head position of the wide-speed range waverider configuration aircraft, and the nozzle is communicated with a regulating valve.

[0006] Preferably, the regulating valve is configured as a three-way structure, the first interface of the regulating valve is connected to the nozzle through a reverse jet pipeline, the second interface and the third interface of the regulating valve are respectively connected to the gasification device through a connecting pipeline 1 and a convection heat exchange pipeline, and the gasification device is connected to the liquid working medium storage tank through a connecting pipeline 2; The convection heat exchange pipeline is arranged at the wing tip position of the wide speed range waverider configuration aircraft.

[0007] Preferably, a heat exchange medium flows between the liquid medium storage tank, the gasification device, the regulating valve and the nozzle. The heat exchange medium is stored in the liquid medium storage tank and is finally ejected through the nozzle.

[0008] Preferably, if the heat exchange medium flow rate flowing in from the third interface is less than the heat exchange medium flow rate required by the nozzle flowing out of the first interface, the heat exchange medium is supplemented into the regulating valve through the second interface, and merged with the heat exchange medium flowing in from the third interface to jointly supply the reverse jet pipeline; If the heat exchange medium flow rate flowing in from the third interface is greater than the heat exchange medium flow rate required by the nozzle flowing out of the first interface, a portion of the heat exchange medium is diverted from the second interface and stored, and the remaining heat exchange medium is supplied to the reverse jet pipeline; If the two are equal, the second interface of the regulating valve is closed, and the heat exchange medium does not need to be supplemented or diverted, and is directly supplied to the reverse jet pipeline.

[0009] A method for a convective jet coupled thermal protection system suitable for a wide speed range waverider configuration comprises the following steps: Step S1, arranging an internal flow supply regulating component in the internal structure of the wide speed range waverider configuration aircraft; Step S2: The head of the wide-speed range waverider configuration aircraft adopts a reverse jet thermal protection method, and a nozzle and a reverse jet pipeline are arranged at the head position; Step S3, a convective heat exchange heat protection method is adopted at the wing tip position of the wide speed range waverider configuration, and a convective heat exchange pipeline is arranged at the wing tip position; Step S4, the low-temperature working fluid first flows through the convection heat exchange pipeline at the wing tip position, fully absorbs the aerodynamic heat energy of the outer wall during the flow from the tail to the head, and then turns into high-pressure gas and flows out of the convection heat exchange pipeline, and then the high-pressure gas is transported to the nozzle of the head, directly providing working fluid and energy for the reverse jet heat protection.

[0010] Preferably, the specific steps of step S2 include: setting a small nozzle on the head, and connecting the two ends of the reverse jet pipeline to the nozzle and the first interface of the regulating valve respectively; During operation, the high-pressure heat exchange medium in the reverse jet pipeline is ejected from the nozzle. After the heat exchange medium and the hypersonic free flow interact with each other, a stable reflux area is formed. The reflux area isolates the high-temperature gas from the outer wall of the aircraft head, reduces the wall temperature, and achieves heat protection.

[0011] Preferably, the specific steps of step S3 include: arranging a convection heat exchange pipeline along the leading edge line of the small sweep angle area, and connecting the two ends of the convection heat exchange pipeline to the outlet of the gasification device and the third interface of the regulating valve respectively; During operation, the low-temperature heat exchange medium in the convection heat exchange pipeline flows from the tail to the head. During the flow in the convection heat exchange pipeline, the heat exchange medium conducts convection heat exchange with the tube wall close to the outer wall, absorbs the heat generated by the aerodynamic heating of the outer wall, reduces the temperature of the outer wall, and achieves heat protection.

[0012] Preferably, when arranging the convection heat exchange pipeline in step S3, the convection heat exchange pipeline is arranged close to the outer wall surface.

[0013] Therefore, the present invention adopts the above-mentioned convective jet coupling thermal protection system and method suitable for wide-speed range waverider configuration, which has the following beneficial effects: (1) The present invention adopts a reverse jet heat protection method to reduce heat in the key heat protection area of ​​the head, and adopts a convection heat transfer heat protection method to transfer the heat in the secondary heat protection area with a small sweep angle and a large aspect ratio in the tail to the convection heat transfer pipeline for heat protection. The two areas are matched by arranging a regulating valve.

[0014] (2) The jet / convection coupled heat protection system of the present invention takes into account the reality that aircraft need to carry low-temperature coolant, and makes full use of the heat absorption and temperature rise of the coolant before it is ejected to cool down the secondary key heat protection area. The heat protection process does not involve complex phase change processes, so the overall system design is simple, reasonable and compact.

[0015] (3) The present invention not only utilizes the existing research foundation and related technologies of jet heat protection, but also takes into account the reality that real aircraft can only carry liquid cryogenic coolants. It plays a very positive role in the practical application of wide-speed range waverider configuration aircraft.

[0016] (4) The flow of the cooling fluid drives the transport of aerodynamic heating energy, so the system has the possibility of recycling aerodynamic thermal energy, providing a new idea for the refined energy management of hypersonic vehicles.

[0017] The technical solution of the present invention is further described in detail below through the accompanying drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram of a reverse jet thermal protection method of an embodiment of a convective jet coupled thermal protection system and method applicable to a wide-speed range waverider configuration of the present invention; Figure 2 It is a schematic diagram of a convective heat exchange thermal protection method of an embodiment of a convective jet coupled thermal protection system and method applicable to a wide speed range waverider configuration of the present invention; Figure 3 It is a schematic diagram of the structure of a thermal protection system of an embodiment of a convective jet coupled thermal protection system and method applicable to a wide speed range waverider configuration of the present invention; Figure 4 for Figure 3 A schematic diagram of the enlarged structure at point A; Figure 5 It is a schematic diagram of the flow of heat exchange medium in the thermal protection system of the convective jet coupled thermal protection system and method applicable to the wide speed range waverider configuration of the present invention; Figure numerals: 1. Hypersonic free flow; 2. Reverse jet; 3. Recirculation area; 4. Flow field shock wave structure; 5. Heat exchange medium; 6. Aerodynamic heat transfer direction; 21. Outer wall; 22. Internal structure; 23. Nozzle; 24. Convective heat exchange pipeline; 25. Control valve; 26. Third interface; 27. First interface; 28. Second interface; 29. ​​Gasification device; 30. Liquid medium storage tank; 31. Internal flow supply adjustment component. DETAILED DESCRIPTION

[0019] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0020] Unless otherwise defined, the technical terms or scientific terms used in the present invention should be understood by people with ordinary skills in the field to which the present invention belongs. The words "first", "second" and similar words used in the present invention do not indicate any order, quantity or importance, but are only used to distinguish different components. "Include" or "comprise" and similar words mean that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, without excluding other elements or objects. "Connect" or "connected" and similar words are not limited to physical or mechanical connections, but may include electrical connections, whether direct or indirect. "Up", "down", "left", "right" and the like are only used to indicate relative positional relationships. When the absolute position of the described object changes, the relative positional relationship may also change accordingly.

[0021] Example See also Figure 1-5 The present invention provides a convection jet coupling thermal protection system suitable for a wide-speed range waverider configuration, including an outer wall surface 21 arranged on the outer surface of a wide-speed range waverider configuration aircraft, the outer wall surface 21 is coated on the outside of an internal structure 22, an internal flow supply regulating component 31 is arranged in the internal structure 22, the internal flow supply regulating component 31 includes a liquid working medium storage tank 30, a vaporization device 29 and a regulating valve 25, the regulating valve 25 is added in the process of the high-pressure working medium being transported from the outlet of the convection heat exchange pipeline 24 to the head nozzle 23, the nozzle 23 is arranged at the head position of the wide-speed range waverider configuration aircraft, and the nozzle 23 and the regulating valve 25 are connected.

[0022] The parameters such as the flow rate and pressure of the high-pressure working fluid are adjusted to meet the heat protection requirements of the reverse nozzle 23, and the function in step S2 is not affected on the basis of realizing the function in step S4. The process of adjusting the regulating valve 25 is dynamic adjustment, matching the parameters of the inflowing working fluid with the parameters of the outflowing working fluid. If the flow rate flowing into the regulating valve 25 is insufficient, the working fluid needs to be supplemented. If the flow rate is excessive, the high-pressure working fluid can be recycled and stored for reuse to avoid waste.

[0023] The regulating valve 25 is set to a three-way structure. The first interface 27 of the regulating valve 25 is connected to the nozzle 23 through the reverse jet pipeline. The first interface 27 is used to flow out the high-pressure working fluid that meets the heat protection requirements of the nozzle 23. The second interface 28 and the third interface 26 of the regulating valve 25 are respectively connected to the gasification device 29 through the connecting pipe 1 and the convection heat exchange pipeline 24. The second interface 28 is used for dynamic adjustment and two-way circulation, and is used to dynamically adjust the working fluid flow parameters in real time to meet the reverse jet requirements. The third interface 26 is used to flow in the high-pressure working fluid that absorbs heat through the convection heat exchange pipeline 24.

[0024] If the flow rate of the heat exchange medium 5 flowing in from the third interface 26 is less than the flow rate of the heat exchange medium 5 required by the nozzle 23 flowing out of the first interface 27, the heat exchange medium 5 is supplemented to the regulating valve 25 through the second interface 28, and merged with the heat exchange medium 5 flowing in from the third interface 26, and jointly supplied to the reverse jet pipeline; if the flow rate of the heat exchange medium 5 flowing in from the third interface 26 is greater than the flow rate of the heat exchange medium 5 required by the nozzle 23 flowing out of the first interface 27, a part of the heat exchange medium 5 is diverted from the second interface 28 and stored, and the remaining heat exchange medium 5 is supplied to the reverse jet pipeline; if the two are equal, the second interface 28 of the regulating valve 25 is closed, and the heat exchange medium 5 does not need to be supplemented or diverted, and is directly supplied to the reverse jet pipeline.

[0025] High-pressure gaseous working fluid is often used in reverse jet thermal protection. In order to avoid the influence of phase change on the heat protection and transportation process, convective heat exchange also uses gaseous working fluid. In order to facilitate storage and carrying and reduce volume occupation, the gaseous working fluid usually needs to be liquefied and stored, and then gasified and supplied when used, so a gasification device 29 and a liquid working fluid storage tank 30 are also provided in the system. The gasification device 29 is connected to the liquid working fluid storage tank 30 through a connecting pipe 2. The liquid working fluid storage tank 30 is responsible for storing and carrying liquid working fluid, and has only one outlet connected to the gasification device 29 and supplies to the gasification device 29.

[0026] The gasification device 29 supplies or recovers gaseous working fluid to the dynamic regulating valve 25 to realize the dynamic regulating function. This is a dynamic regulating port of the gasification device 29; the outlet on the other side is connected to the inlet of the convection heat exchange pipeline 24, and gaseous low-temperature working fluid is supplied thereto for convection heat absorption with the pipe wall to realize the function in step S3; and the inlet on one side is connected to the liquid working fluid storage tank 30, and the liquid working fluid is supplied to the gasification device 29 and then converted into gas for use by the entire heat protection system.

[0027] The heat exchange medium 5 flows among the liquid medium storage tank 30 , the gasification device 29 , the regulating valve 25 and the nozzle 23 . The heat exchange medium 5 is stored in the liquid medium storage tank 30 and is finally ejected through the nozzle 23 .

[0028] In hypersonic aircraft, the smaller the sweep angle, the more severe the aerodynamic heating is, and the more important thermal protection is needed. The wide-speed range waverider configuration has the characteristics of large aspect ratio and small sweep angle. In addition to the minimum sweep angle area at the head, which requires key thermal protection, there is also a smaller sweep angle area at the tail wing tip, which requires thermal protection measures. Since the heating conditions and shapes of the two areas are different, different heat protection methods can be selected to deal with them respectively in order to achieve better heat protection effects. The method of a convective jet coupled thermal protection system suitable for a wide-speed range waverider configuration includes the following steps: Step S1, arranging an internal flow supply regulating component 31 in the internal structure 22 of the wide-speed range waverider configuration aircraft; Step S2: The head of the wide-speed range waverider configuration aircraft adopts a reverse jet thermal protection method, and a nozzle and a reverse jet pipeline are arranged at the head position. Specifically, it includes: a small nozzle 23 is set at the head, and the two ends of the reverse jet pipeline are connected to the nozzle 23 and the second interface 28 of the regulating valve 25. When working, the high-pressure heat exchange medium 5 in the reverse jet pipeline is ejected from the nozzle 23, and the reverse jet 2 of the heat exchange medium 5 is as follows: Figure 1 As shown in the figure, the arrow indicates the direction of the reverse jet 2. After the heat exchange medium 5 and the hypersonic free flow 1 interact with each other, a stable reflow area 3 is formed. The new stable flow field shock wave structure 4 formed in the reflow area 3 isolates the high-temperature gas from the outer wall 21 of the aircraft head, reduces the wall temperature, and realizes heat protection.

[0029] Step S3, the wing tip position of the wide-speed waveriding configuration, that is, the area with a sweep angle second only to the head, adopts a convective heat exchange thermal protection method, and arranges a convective heat exchange pipeline 24 at the wing tip position. Specifically comprising: arranging the convective heat exchange pipeline 24 along the leading edge line of the small sweep angle area, and when arranging the convective heat exchange pipeline 24, the convective heat exchange pipeline 24 is arranged close to the outer wall surface 21. The two ends of the convective heat exchange pipeline 24 are respectively connected to the outlet of the gasification device 29 and the third interface 26 of the regulating valve 25. During operation, the low-temperature heat exchange medium 5 in the convective heat exchange pipeline 24 flows from the tail to the head direction, that is, it flows in the opposite direction of the free flow, such as Figure 4 As shown in the figure, the arrow indicates the flow direction of the heat exchange medium 5. During the flow of the heat exchange medium 5 in the convection heat exchange pipeline 24, the heat exchange medium 5 performs convection heat exchange with the pipe wall close to the outer wall surface 21, absorbs the heat generated by the aerodynamic heating of the outer wall surface 21, and reduces the temperature of the outer wall surface 21 to maintain it at a safe level, thereby achieving heat protection. The aerodynamic heat transfer direction 6 is shown in FIG. Figure 4 shown.

[0030] After realizing the combined heat protection using different heat protection methods in different heated areas, the two originally independent heat protection methods are connected in series based on the characteristic that both active thermal protection methods require flowing working fluids. A coupled heat protection system is constructed to control the comprehensive heat protection effect by adjusting parameters such as the flow rate and pressure of the working fluid, and realize the reuse of working fluids and energy.

[0031] Step S4, the low-temperature working fluid first flows through the convection heat exchange pipeline 24 at the wing tip position, fully absorbs the aerodynamic heat energy of the outer wall 21 during the flow from the tail to the head, and realizes the function in step S3, and then turns into high-pressure gas and flows out of the convection heat exchange pipeline 24, and then the high-pressure gas is transported to the nozzle 23 of the head, directly providing working fluid and energy for the reverse jet heat protection, and realizing the function in step S2.

[0032] Step S4 eliminates the process of pressurizing the jet fluid in the single reverse jet thermal protection, and replaces it with the process of the fluid directly absorbing aerodynamic heat energy during the convective heat exchange process, thereby realizing the utilization of aerodynamic heat energy, avoiding the problem that the fluid cannot be reused after convective heat exchange, and saving the energy required for pressurizing the reverse jet fluid, thereby improving the overall energy utilization efficiency and avoiding the redundant design of the internal space of the aircraft. If the fluid after absorbing heat and pressurizing through the convective heat exchange pipeline 24 does not meet the pressure and flow rate parameters required by the reverse jet nozzle 23, it can be adjusted by a pump or a valve.

[0033] Therefore, the present invention adopts the above-mentioned convection jet coupled thermal protection system and method suitable for wide-speed range waverider configuration. The head key heat protection area adopts the reverse jet thermal protection method to reduce heat; the secondary key heat protection area with a small sweep angle and a large aspect ratio at the tail is protected by transferring the heat here to the convection heat exchange pipeline through the convection heat transfer method; the two areas are matched by arranging regulating valves; the jet / convection coupled thermal protection system takes into account the actual situation that the aircraft needs to carry low-temperature coolant, and makes full use of the heat absorption and temperature rise of the coolant before it is ejected to cool the secondary key heat protection area. The heat protection process does not involve complex phase change processes, so the overall system design is simple, reasonable and compact.

[0034] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. A convection jet coupled thermal protection system suitable for a wide speed range waverider configuration, characterized by: It includes an outer wall surface arranged on the outer surface of a wide-speed range waverider configuration aircraft, the outer wall surface covers the outside of an internal structure, an internal flow supply regulating component is arranged in the internal structure, and the internal flow supply regulating component includes a liquid working medium storage tank, a gasification device and a regulating valve, A nozzle is arranged at the head position of the wide-speed range waverider configuration aircraft, and the nozzle is communicated with a regulating valve.

2. The convection jet coupled thermal protection system suitable for a wide speed range waverider configuration according to claim 1, characterized in that: The regulating valve is set to a three-way structure, the first interface of the regulating valve is connected to the nozzle through the reverse jet pipeline, the second interface and the third interface of the regulating valve are respectively connected to the gasification device through the connecting pipeline 1 and the convection heat exchange pipeline, and the gasification device is connected to the liquid working medium storage tank through the connecting pipeline 2; The convection heat exchange pipeline is arranged at the wing tip position of the wide speed range waverider configuration aircraft.

3. The convection jet coupled thermal protection system suitable for a wide speed range waverider configuration according to claim 2, characterized in that: A heat exchange medium flows between the liquid medium storage tank, the gasification device, the regulating valve and the nozzle. The heat exchange medium is stored in the liquid medium storage tank and is finally ejected through the nozzle.

4. The convection jet coupled thermal protection system suitable for a wide speed range waverider configuration according to claim 3, characterized in that: If the heat exchange medium flow rate flowing in from the third interface is less than the heat exchange medium flow rate required by the nozzle flowing out of the first interface, the heat exchange medium is supplemented into the regulating valve through the second interface, and merged with the heat exchange medium flowing in from the third interface to jointly supply the reverse jet pipeline; If the heat exchange medium flow rate flowing in from the third interface is greater than the heat exchange medium flow rate required by the nozzle flowing out of the first interface, a portion of the heat exchange medium is diverted from the second interface and stored, and the remaining heat exchange medium is supplied to the reverse jet pipeline; If the two are equal, the second interface of the regulating valve is closed, and the heat exchange medium does not need to be supplemented or diverted, and is directly supplied to the reverse jet pipeline.

5. A method for applying the convective jet coupled thermal protection system suitable for a wide speed range waverider configuration as described in any one of claims 1 to 4, characterized in that: The following steps are involved: Step S1, arranging an internal flow supply regulating component in the internal structure of the wide-speed range waverider configuration aircraft; Step S2: The head of the wide-speed range waverider configuration aircraft adopts a reverse jet thermal protection method, and a nozzle and a reverse jet pipeline are arranged at the head position; Step S3, a convective heat exchange heat protection method is adopted at the wing tip position of the wide speed range waverider configuration, and a convective heat exchange pipeline is arranged at the wing tip position; Step S4, the low-temperature working fluid first flows through the convection heat exchange pipeline at the wing tip position, fully absorbs the aerodynamic heat energy of the outer wall during the flow from the tail to the head, and then turns into high-pressure gas and flows out of the convection heat exchange pipeline, and then the high-pressure gas is transported to the nozzle of the head, directly providing working fluid and energy for the reverse jet heat protection.

6. The method of the convective jet coupled thermal protection system applicable to a wide speed range waverider configuration according to claim 5, characterized in that: The specific steps of step S2 include: setting a small nozzle on the head, and connecting the two ends of the reverse jet pipeline to the nozzle and the first interface of the regulating valve respectively; During operation, the high-pressure heat exchange medium in the reverse jet pipeline is ejected from the nozzle. After the heat exchange medium and the hypersonic free flow interact with each other, a stable reflux area is formed. The reflux area isolates the high-temperature gas from the outer wall of the aircraft head, reduces the wall temperature, and achieves heat protection.

7. The method of the convective jet coupled thermal protection system applicable to a wide speed range waverider configuration according to claim 6, characterized in that: The specific steps of step S3 include: arranging a convection heat exchange pipeline along the leading edge line of the small sweep angle area, and connecting the two ends of the convection heat exchange pipeline to the outlet of the gasification device and the third interface of the regulating valve respectively; During operation, the low-temperature heat exchange medium in the convection heat exchange pipeline flows from the tail to the head. During the flow in the convection heat exchange pipeline, the heat exchange medium conducts convection heat exchange with the tube wall close to the outer wall, absorbs the heat generated by the aerodynamic heating of the outer wall, reduces the temperature of the outer wall, and achieves heat protection.

8. The method of the convective jet coupled thermal protection system applicable to a wide speed range waverider configuration according to claim 7, characterized in that: When arranging the convection heat exchange pipeline in step S3, the convection heat exchange pipeline is arranged close to the outer wall surface.

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