Multi-mode combined adjustable thermal protection device and protection method for reentry vehicle

Abstract

The application provides a reentry vehicle multi-mode combined adjustable heat protection device and a protection method. The heat protection device comprises: a load cabin, a head portion provided with an inwardly recessed windward recess; a head protection member provided on the head portion of the load cabin and provided with a head opening communicated with the windward recess; a moving member movably arranged in the windward recess and provided with a first jet hole; and a jet flow device arranged on the load cabin and communicated with the first jet hole; wherein jet flow gas sprayed by the jet flow device can push the moving member to move towards the head portion of the load cabin, so that the first jet hole is exposed outside the head opening. The application can realize switching of multiple heat protection modes, and the heat protection effect is more efficient and reliable compared with the single mode of the traditional mode.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more specifically, to a multi-mode adjustable thermal protection device and protection method for reentry vehicles. Background Technology

[0002] With the development of the space industry, space transportation and deep space exploration missions will be the focus of future research. Compared with traditional reentry deceleration methods and inflatable reentry vehicles, mechanically deployable reentry vehicles have received widespread attention both domestically and internationally in recent years due to their advantages such as small envelope constraint, high payload efficiency, and good deceleration effect. During the reentry process, the reentry vehicle successively passes through rarefied flow, transitional flow, and continuous flow regions. A large amount of aerodynamic heat is generated during high-speed flight, causing ablation of the vehicle surface and the overall structure. Therefore, how to effectively and reasonably protect the reentry vehicle from thermal damage is one of the urgent problems to be solved.

[0003] In recent years, many scholars at home and abroad have proposed a number of drag reduction and heat protection methods, such as: reverse jet, adding drag reduction rods, adding pneumatic discs, windward concave cavity, energy deposition, and many combinations thereof.

[0004] However, all existing drag reduction methods suffer from limited thermal protection capabilities and poor thermal protection effectiveness. Summary of the Invention

[0005] The purpose of this application is to provide a multi-mode adjustable thermal protection device and method for reentry vehicles, which solves the problem of single thermal protection methods and poor thermal protection effect in related technologies.

[0006] This application provides a multi-mode adjustable thermal protection device for a reentry vehicle, comprising: a payload bay with an inwardly recessed windward cavity at its head; a head guard disposed at the head of the payload bay with a head opening communicating with the windward cavity; a movable component movably disposed within the windward cavity and having a first jet nozzle; and a jetting device disposed in the payload bay and communicating with the first jet nozzle for ejecting jetting gas. The jetting gas ejected by the jetting device can push the movable component towards the head of the payload bay, exposing the first jet nozzle outside the head opening.

[0007] In this embodiment, a movable component is installed within the windward cavity. Simultaneously, the movable component is moved by a jet device, causing it to actively eject air. This process enables multiple modes of thermal protection, offering more efficient and reliable thermal protection compared to the single-mode approach of traditional methods. Furthermore, using a jet device to propel the movable component avoids the intervention of electric motors or other electrical devices, resulting in a more compact and lightweight aircraft structure.

[0008] In some embodiments, the moving component has a channel inside, the first jet hole is disposed on the outer peripheral surface of the moving component, and the jetting device communicates with the first jet hole through the channel.

[0009] In this embodiment, high-pressure gas ejected from the jet nozzle of the jet device enters the channel to propel the moving component forward. At the same time, the high-pressure gas is ejected from multiple first jet holes through the channel. Without the need to add various pipelines, the channel is directly formed inside the moving component, reducing space occupation.

[0010] In some embodiments, the outer peripheral surface of the moving component includes a first conical surface, wherein, as the moving component moves toward the head of the payload compartment, the gap between the first conical surface and the head opening gradually decreases.

[0011] In this embodiment, due to the structure of the first conical surface, the head opening becomes narrower and narrower, which changes the annular area of ​​the head opening, changes the incoming air field structure, and the first conical surface of the moving component forms a guide for the incoming flow, thereby the moving component and the windward concave cavity together form a dual heat protection mode.

[0012] In some embodiments, the outer peripheral surface of the moving component further includes a second conical surface connected to the first conical surface. The second conical surface is located behind the first conical surface. As the moving component moves toward the head of the load compartment until the second conical surface passes the head opening, the gap between the second conical surface and the head opening gradually increases.

[0013] In this embodiment, the moving component is formed into a double-conical structure. As the component moves forward, the double-conical structure causes the head opening to gradually narrow and then gradually widen, resulting in a changing annular area of ​​the head opening. This continuously alters the incoming airflow structure, thereby creating thermal protection. In other words, multiple methods are used to change the flow field at the head opening, further enhancing the aircraft's thermal protection effect. Furthermore, this double-conical structure reduces the component's weight, making it easier to drive and minimizing its impact on the aircraft's center of gravity.

[0014] In some embodiments, the outer peripheral surface of the moving component is further provided with a second jet hole and a third jet hole that communicate with the channel, wherein the first jet hole, the second jet hole and the third jet hole are arranged sequentially at intervals from the head to the tail along the axial direction of the moving component.

[0015] In this embodiment, the second and third jet holes can inject gas into the windward concave cavity, making the pressure difference inside the windward concave cavity greater than the external air pressure, thereby further providing driving force for the moving component to move forward.

[0016] In some embodiments, the jetting device includes a jetting bottle and a one-way valve disposed at the jetting nozzle of the jetting bottle.

[0017] In this embodiment, a one-way valve is used to control the flow direction of high-pressure gas inside the jet bottle. The gas flow direction within the one-way valve is from the jet bottle to the moving part, preventing high-temperature, high-speed external gas from entering the payload chamber and acting as a blockage mechanism, allowing only the gas inside the jet bottle to flow out through the one-way valve. The gas flowing out of the one-way valve is guided into the channel through a connecting pipe.

[0018] In some embodiments, an elastic member is provided inside the connecting pipe, and the elastic member is disposed between the inner wall of the windward concave cavity and the moving member.

[0019] In this embodiment, the spring is compressed when the moving part moves backward and unfolded when it moves forward. The connecting tube wraps around the spring, which serves a positioning function.

[0020] In some embodiments, the system further includes: a linkage assembly disposed within the windward concave cavity, the linkage assembly comprising a plurality of linkage groups distributed around the movable component, each linkage group comprising a first linkage and a second linkage, the first linkage and the second linkage being hinged together, the first linkage being hinged to the movable component, and the second linkage being hinged to the inner wall of the windward concave cavity.

[0021] In this embodiment, the linkage assembly provides support for the moving component on the one hand, and makes the movement of the moving component more stable and flexible on the other hand.

[0022] This application also provides a multi-mode adjustable thermal protection method for reentry vehicles, applied to the thermal protection device described in any of the above embodiments. The thermal protection method includes: in the initial mode, the moving part is hidden in the windward cavity, and thermal protection is performed through the windward cavity; the moving part is moved towards the head of the payload compartment by jetting jet gas through the jetting device, so that the first jet hole is exposed outside the head opening, and thermal protection is performed on the head of the vehicle through the first jet hole.

[0023] The embodiments of this application can achieve thermal protection effects with multiple modes of switching, which are more efficient and reliable than the traditional single-mode approach.

[0024] In some embodiments, the step of using the jetting device to propel the moving component toward the head of the payload compartment, exposing the first jet nozzle outside the head opening, and providing thermal protection to the aircraft head through the first jet nozzle includes: using the jetting device to propel the moving component toward the head of the payload compartment, gradually reducing the gap between the first conical surface of the moving component and the head opening, and providing thermal protection through the cooperation of the first conical surface and the windward concave cavity; continuing to use the jetting device to propel the moving component toward the head of the payload compartment, exposing the first jet nozzle outside the head opening, and providing thermal protection to the aircraft head through the first jet nozzle.

[0025] The embodiments of this application can switch between multiple modes, such as the windward concave cavity thermal protection mode, the moving part + windward concave cavity thermal protection mode, and the moving part + windward concave cavity thermal protection + first jet hole active jet thermal protection mode, so that the thermal protection effect is more comprehensive. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments of this application will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0027] Figure 1 A perspective view of a multi-mode adjustable thermal protection device for a reentry vehicle provided in this application embodiment;

[0028] Figure 2 A cross-sectional view of a multi-mode adjustable thermal protection device for a reentry vehicle provided in this application embodiment;

[0029] Figure 3 A partially enlarged schematic diagram of a multi-mode combined adjustable thermal protection device for a reentry vehicle provided in this application embodiment;

[0030] Figure 4 A flowchart of a multi-mode combined adjustable thermal protection method for reentry vehicles provided in this application embodiment;

[0031] Figure 5 This is a schematic diagram illustrating the mode combination switching process of the thermal protection device provided in the embodiments of this application. Detailed Implementation

[0032] The technical solutions in the embodiments of this application will now be described with reference to the accompanying drawings.

[0033] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, in the description of this application, terms such as "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0034] Reference Figure 1 and Figure 2 , Figure 1 A perspective view of a multi-mode adjustable thermal protection device for a reentry vehicle provided in this application embodiment; Figure 2 This is a cross-sectional view of a multi-mode adjustable thermal protection device for a reentry vehicle, provided as an embodiment of this application.

[0035] This application provides a multi-mode combined adjustable thermal protection device for reentry vehicles, including: a payload bay 10, a head protection component 20, a moving component 30, and a jet device 40.

[0036] The payload compartment 10 has an inwardly recessed windward cavity 11 at its head. The payload compartment 10 provides payload space during flight. The payload compartment 10 can be cylindrical, with the front end forming the payload compartment's head. The windward cavity 11 absorbs and cools the heat flow during flight, providing thermal protection. For example, to improve the heat resistance of the windward cavity 11 to high-temperature incoming flow, an ablation-resistant, high-temperature insulating material can be applied to the inner wall of the windward cavity 11 for thermal protection.

[0037] The head protection component 20 is located at the head of the payload compartment 10, and the head protection component 20 has a head opening 21 that communicates with the windward cavity 11. The head protection component 20 can be in the form of a conical umbrella structure, which can be deployed to form a head cone thermal protection during the reentry of the aircraft.

[0038] The movable component 30 is movably disposed within the windward cavity 11, and the movable component 30 is provided with a first jet hole 31.

[0039] The jetting device 40 is disposed inside the payload chamber and communicates with the first jet nozzle 31 for jetting jet gas. The jet gas jetted by the jetting device 40 can push the moving part 30 to move towards the head (forward) of the payload chamber 10, so that the first jet nozzle 31 is exposed outside the head opening 21.

[0040] In the initial mode, the moving part 30 is hidden in the windward cavity 11. During the flight of the aircraft, the windward cavity 11 at the front provides thermal protection, that is, the main shock wave is absorbed into the windward cavity 11, reducing the surface heat flux density of other parts of the aircraft. The mode switching is achieved by spraying jet gas through the jet device 40. The jet gas sprayed by the jet device 40 pushes the moving part 30 towards the head (forward) of the load chamber 10. When the first jet hole 31 is located in the windward concave cavity 11 and has not passed the head opening 21, the jet gas is ejected from the first jet hole 31 and flows into the windward concave cavity 11. At this time, the flow field inside the windward concave cavity 11 is changed by the cooperation between the shape of the moving part 30 and the head opening 21 and the jet ejected from the first jet hole 31. Thus, the moving part 30 and the windward concave cavity 11 together form a dual heat protection mode. Another mode switching is achieved by continuing to spray jet gas through the jet device 40. That is, the jet gas sprayed by the jet device 40 continues to push the moving part 30 towards the head (forward) of the load chamber 10, so that the first jet hole 31 is exposed outside the head opening 21. The jet ejected from the first jet hole 31 compresses the external flow and changes the external flow field structure, achieving another active jet heat protection effect.

[0041] The reentry vehicle multi-mode adjustable thermal protection device of this application embodiment, by setting a movable component 30 in the windward cavity 11, and by actively jetting air through the jetting device 40 while the movable component 30 is moved, can achieve thermal protection effects that can switch between multiple modes. Compared with the traditional single-mode method, the thermal protection effect is more efficient and reliable. In addition, by using the jetting device 40 to propel the movable component 30, the intervention of electric devices such as motors is avoided, making the entire aircraft structure more compact and lighter.

[0042] In some embodiments, refer to Figure 2 The aforementioned moving component 30 has a channel 32 inside, and a first jet hole 31 is disposed on the outer peripheral surface of the moving component 30. The jetting device 40 is connected to the first jet hole 31 through the channel 32. Multiple first jet holes 31 can be disposed around the outer peripheral surface of the moving component 30, and each of the multiple first jet holes 31 is connected to the channel 32. The channel 32 can extend to the tail (rear end) of the moving component 30, connecting to the jet outlet of the jetting device 40. High-pressure gas ejected from the jet outlet of the jetting device 40 enters the channel 32, propelling the moving component 30 forward, while simultaneously, the high-pressure gas is ejected from the multiple first jet holes 31 through the channel 32.

[0043] In some embodiments, refer to Figure 2The outer peripheral surface of the moving component 30 includes a first conical surface 301. As the moving component 30 moves toward the head (forward) of the load chamber 10, the gap between the first conical surface 301 and the head opening 21 gradually decreases. The front end of the first conical surface 301 is pointed, and the rear end gradually widens. As the moving component 30 moves forward, the structure of the first conical surface 301 makes the head opening 21 narrower and narrower. At this time, the first conical surface 301 of the moving component 30 guides the incoming flow, so that the moving component 30 and the windward cavity 11 together form a dual heat protection mode.

[0044] In some embodiments, refer to Figure 2 Furthermore, the outer peripheral surface of the moving component 30 also includes a second conical surface 302 connected to the first conical surface 301. The second conical surface 302 is located behind the first conical surface 301. As the moving component 30 moves towards the head of the payload bay 10 until the second conical surface 302 passes the head opening 21, the gap between the second conical surface 302 and the head opening 21 gradually increases. The front end of the first conical surface 301 is pointed and the rear end gradually widens, while the front end of the second conical surface 302 is wide and the rear end gradually tapers, resulting in the moving component 30 forming a double-conical structure. As the moving component 30 moves forward, the double-conical structure causes the head opening 21 to first gradually narrow and then gradually widen, forming another thermal protection mode, that is, using multiple methods to change the flow field at the head opening 21, further improving the thermal protection effect of the aircraft. In addition, this double-conical structure of the moving component 30 also reduces its own weight, making it easier to drive and reducing the impact on the center of gravity of the aircraft itself.

[0045] In some embodiments, refer to Figure 3 The outer peripheral surface of the aforementioned moving component 30 is further provided with a second jet hole 33 and a third jet hole 34 that communicate with the channel 32. The first jet hole 31, the second jet hole 33, and the third jet hole 34 are arranged sequentially at intervals from the head to the tail (front-to-back direction) along the axial direction of the moving component 30. The first jet hole 31 may be located at the first conical surface 301, the second jet hole 33 may be located at the junction of the first conical surface 301 and the second conical surface 302, and the third jet hole 34 may be located on the second conical surface 302. The second jet hole 33 and the third jet hole 34 can inject gas into the windward cavity 11, making the pressure difference inside the windward cavity 11 greater than the external air pressure, thereby further providing driving force for the moving component 30 to move forward.

[0046] In some embodiments, refer to Figure 3The jetting device 40 includes a jetting bottle 41 and a one-way valve 42 disposed at the jetting port of the jetting bottle 41. The one-way valve 42 is connected to the channel 32 of the moving part 30 via a connecting pipe 43. The one-way valve 42 controls the flow direction of the high-pressure gas in the jetting bottle 41. The gas flow direction within the one-way valve 42 is from the jetting bottle 41 to the moving part 30, preventing high-temperature, high-speed external gas from entering the payload chamber, thus acting as a blockage and allowing only the gas in the jetting bottle 41 to flow out through the one-way valve 42. The gas flowing out of the one-way valve 42 is guided into the channel 32 through the connecting pipe 43. In one example, one end of the connecting pipe 43 is fixed to the one-way valve 42, and the other end is slidably disposed in the channel 32. In another example, one end of the connecting pipe 43 is fixed to the one-way valve 42, and the other end is fixed in the channel 32, wherein the connecting pipe 43 is a flexible hose, such as a corrugated pipe.

[0047] In some embodiments, a further elastic member is provided inside the connecting tube 43, which is disposed between the inner wall of the windward cavity 11 and the moving member 30. For example, the elastic member may be a spring, with one end connected to the inner wall of the windward cavity and the other end connected to the rear end of the channel 32. When the moving member 30 moves backward, the spring is compressed, and when it moves forward, the spring is extended. The connecting tube 43 encloses the spring, which serves a positioning function.

[0048] In some embodiments, refer to Figure 2 and Figure 3 The protective device further includes: a connecting rod assembly disposed in the windward concave cavity. The connecting rod assembly includes a plurality of connecting rod groups 50 distributed around the moving part 30. Each connecting rod group 50 includes a first connecting rod 51 and a second connecting rod 52. The first connecting rod 51 and the second connecting rod 52 are hinged together, and the first connecting rod 51 is hinged to the moving part 30, and the second connecting rod 52 is hinged to the inner wall of the windward concave cavity 11.

[0049] Reference Figure 4 and Figure 5 This application also provides a multi-mode combined adjustable thermal protection method for reentry vehicles, which is applied to the thermal protection device described in any of the above embodiments. The thermal protection method includes steps S11 and S12.

[0050] In step S11, in the initial mode, the moving part is hidden in the windward cavity, and thermal protection is provided through the windward cavity.

[0051] For example, in the initial mode, the moving parts of the reentry vehicle are hidden in the windward concave cavity of the vehicle's nose. At this time, the spring is in a compressed state. During the flight of the vehicle, the windward concave cavity created by the nose provides thermal protection, that is, the main shock wave is absorbed into the concave cavity, reducing the surface heat flux density of other parts of the vehicle.

[0052] In step S12, jet gas is injected through the jet device to push the moving component toward the head of the payload compartment, so that the first jet hole is exposed outside the head opening, and the head of the aircraft is thermally protected through the first jet hole.

[0053] As described above, mode switching is achieved by spraying jet gas through the jet device. The jet gas sprayed by the jet device 40 pushes the moving part 30 towards the head (forward) of the load chamber 10. When the first jet hole 31 is located in the windward concave cavity 11 and has not passed the head opening 21, the jet gas is ejected from the first jet hole 31 and flows into the windward concave cavity 11. At this time, the flow field inside the windward concave cavity 11 is changed by the cooperation between the shape of the moving part 30 and the head opening 21 and the jet ejected from the first jet hole 31. Thus, the moving part 30 and the windward concave cavity 11 together form a dual heat protection mode. Another mode switching is achieved by continuing to spray jet gas through the jet device 40. That is, the jet gas sprayed by the jet device 40 continues to push the moving part 30 towards the head (forward) of the load chamber 10, so that the first jet hole 31 is exposed outside the head opening 21. The jet ejected from the first jet hole 31 compresses the external flow, changing the external flow field structure and achieving another active jet heat protection effect.

[0054] In some embodiments, refer to Figure 4 and Figure 5 Step S12 includes: using a jetting device to spray jet gas to push the moving component toward the head of the load chamber, so that the gap between the first conical surface of the moving component and the head opening gradually decreases, and thermal protection is achieved by the cooperation of the first conical surface and the windward concave cavity.

[0055] The mode switching is achieved by jetting gas from the gas cylinder outward. At this time, the gas enters the windward concave cavity through the one-way valve and simultaneously enters the double-cone moving component (double-cone rod). The gas pressure inside the windward concave cavity is greater than the external gas pressure. The thrust generated by the pressure difference pushes the double-cone moving component away from the spring. Therefore, the double-cone moving component can move outward from the nose of the aircraft. Due to the configuration of the double-cone moving component, the inlet area of ​​the windward concave cavity gradually decreases. At this time, although the jet already exists, it only exists in the nose of the aircraft and the windward concave cavity and does not play a role in changing the external flow field of the aircraft. Therefore, this mode is the double-cone component + concave cavity heat protection mode.

[0056] Continue to propel the moving component toward the head of the payload compartment by jetting gas through the jetting device, so that the first jet hole is exposed outside the head opening, and the head of the aircraft is thermally protected through the first jet hole.

[0057] As the double-cone moving component moves outward continuously, and the first jet hole is fully exposed outside the aircraft, the gas jet is ejected through the one-way valve, the double-cone moving component, and the windward concave cavity via the first jet hole. At this time, the airflow and the incoming flow are compressed, which changes the flow field structure. Therefore, the active jet also plays a role in thermal protection. At this time, the three thermal protection methods of the double-cone moving component, the windward concave cavity heat protection, and the active jet from the first jet hole are working simultaneously, resulting in a more comprehensive thermal protection effect.

[0058] In the several embodiments provided in this application, it should be understood that the disclosed apparatus and methods can also be implemented in other ways. The apparatus embodiments described above are merely illustrative. For example, the flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods, and computer program products according to various embodiments of this application. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions marked in the blocks may occur in a different order than those marked in the drawings. For example, two consecutive blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in a block diagram and / or flowchart, and combinations of blocks in block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or action, or using a combination of dedicated hardware and computer instructions.

[0059] In addition, the functional modules in the various embodiments of this application can be integrated together to form an independent part, or each module can exist independently, or two or more modules can be integrated to form an independent part.

[0060] If the aforementioned functions are implemented as software functional modules and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0061] The above description is merely an embodiment of this application and is not intended to limit the scope of protection of this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application. It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0062] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the rights protection as described above.

[0063] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

Claims

1. A multi-mode combined adjustable thermal protection system for a reentry vehicle, comprising: include: The load compartment has an inwardly recessed windward cavity at its head. A head protection device is provided at the head of the load chamber, and the head protection device is provided with a head opening that communicates with the windward concave cavity; A movable component is movably disposed within the windward concave cavity, and the movable component is provided with a first air jet hole; A jetting device, disposed within the payload chamber and connected to the first jet orifice, is used to jettison jet gas; wherein the jetting gas jetted by the jetting device can push the moving component toward the head of the payload chamber, exposing the first jet orifice outside the head opening.

2. The reentry vehicle multi-mode combined adjustable thermal protection device according to claim 1, characterized in that, The moving component has a channel inside, and the first jet hole is located on the outer peripheral surface of the moving component. The jetting device communicates with the first jet hole through the channel.

3. The reentry vehicle multi-mode combined adjustable thermal protection device according to claim 2, characterized in that, The outer peripheral surface of the moving component includes a first conical surface, wherein, as the moving component moves toward the head of the payload compartment, the gap between the first conical surface and the head opening gradually decreases.

4. The reentry vehicle multi-mode combined adjustable thermal protection device according to claim 3, characterized in that, The outer peripheral surface of the moving component also includes a second conical surface connected to the first conical surface. The second conical surface is located behind the first conical surface. As the moving component moves toward the head of the load compartment until the second conical surface passes the head opening, the gap between the second conical surface and the head opening gradually increases.

5. The reentry vehicle multi-mode combined adjustable thermal protection device according to claim 2, characterized in that, The outer peripheral surface of the moving component is also provided with a second jet hole and a third jet hole that communicate with the channel, wherein the first jet hole, the second jet hole and the third jet hole are arranged sequentially at intervals from the head to the tail of the moving component.

6. The reentry vehicle multi-mode combined adjustable thermal protection device according to claim 2, characterized in that, The jet device includes a jet bottle and a one-way valve disposed at the jet nozzle of the jet bottle. The one-way valve is connected to the channel of the moving component through a connecting pipe.

7. The reentry vehicle multi-mode combined adjustable thermal protection device according to claim 6, characterized in that, An elastic component is provided inside the connecting pipe, and the elastic component is disposed between the inner wall of the windward concave cavity and the moving component.

8. The reentry vehicle multi-modal combined adjustable thermal protection device of any of claims 1-7, wherein, Also includes: A linkage assembly is disposed within the windward concave cavity. The linkage assembly includes multiple linkage groups distributed around the moving component. Each linkage group includes a first linkage and a second linkage. The first linkage and the second linkage are hinged together, with the first linkage hinged to the moving component and the second linkage hinged to the inner wall of the windward concave cavity.

9. A method of multi-mode combined adjustable thermal protection for a reentry vehicle, characterized by, The thermal protection method, applied to the thermal protection device as described in any one of claims 1-8, comprises: In the initial mode, the moving part is hidden in the windward recess, which provides thermal protection. The jetting device propels the moving component toward the head of the payload compartment by spraying jet gas, exposing the first jet hole outside the head opening, and providing thermal protection for the head of the aircraft through the first jet hole.

10. The multi-mode combined adjustable thermal protection method for reentry vehicles according to claim 9, characterized in that, The step of propelling the moving component toward the head of the payload compartment by ejecting jet gas through the jetting device, thereby exposing the first jet nozzle outside the head opening, and providing thermal protection to the head of the aircraft through the first jet nozzle includes: The jetting device propels the moving component toward the head of the payload compartment by spraying jet gas, thereby gradually reducing the gap between the first conical surface of the moving component and the head opening. Thermal protection is achieved through the cooperation of the first conical surface and the windward concave cavity. The jetting device continues to propel the moving component toward the head of the payload compartment by spraying jet gas, exposing the first jet hole outside the head opening, and providing thermal protection for the head of the aircraft through the first jet hole.

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