Recoverable rocket bottom thermal protection device
By designing a recyclable rocket bottom thermal protection device, using the evaporation and condensation mechanism of the steam cavity and capillary core structure, the problem of insufficient insulation effect of traditional thermal protection methods in high temperature environments is solved, and more efficient heat management and rockets are achieved Performance improvement.
Patent Information
- Application Number
- CN202411884321.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2024-12-19
- Publication Date
- 2025-02-11
AI Technical Summary
The traditional rocket thermal protection method has limited thermal insulation when facing the tail flame of the high-temperature engine, resulting in excessive temperature at the bottom of the arrow body, affecting structural integrity and safety, and increasing the weight of the rocket, reducing the payload and carrying capacity.
A recyclable rocket bottom thermal protection device is designed, including an evaporation part and a condensation part. Using the steam cavity and capillary core structure, effective heat conduction and condensation is achieved through the evaporation and condensation of the working medium.
It improves the effect of the rocket's thermal protection, reduces the thermal load at the bottom of the arrow body, reduces the weight of the rocket, improves the payload and carrying capacity, and improves the safety and stability of the rocket during the recycling process.
Smart Images
Figure CN119413017A_ABST
Abstract
Description
Technical Field
[0001] The present application relates to the field of aerospace technology, and in particular to a thermal protection device for the bottom of a recoverable rocket. Background Art
[0002] At present, in the field of rocket technology, the thermal protection of the bottom of the rocket body mainly adopts traditional thermal insulation materials and thermal protection coatings, which are passive thermal protection. For example, some rockets use high-temperature resistant ceramic materials or special thermal insulation coatings to reduce the thermal shock and radiation of the engine tail flame on the bottom of the rocket body.
[0003] However, these thermal protection methods may have limited insulation effects when facing the engine tail flame, especially during the rocket recovery process, when the heat of the engine tail flame is extremely high. Traditional thermal protection methods are difficult to completely block the transfer of heat, which may cause the temperature at the bottom of the rocket body to be too high, affecting the integrity and safety of the rocket body structure, and may cause problems such as damage to the thermal insulation material and performance degradation. In addition, traditional thermal insulation materials are heavy, and the large-scale use of thermal insulation materials and coatings will increase the weight of the rocket and reduce the rocket's payload and carrying capacity.
[0004] In addition, traditional thermal insulation materials and coatings may deteriorate in performance after repeated use. With the repeated use of rockets, thermal insulation materials and coatings may experience problems such as wear and aging, reducing the thermal protection effect.
[0005] Therefore, how to improve the thermal protection effect of recoverable rockets and enhance the payload and carrying capacity of recoverable rockets is a technical problem that technical personnel in this field urgently need to solve. Summary of the invention
[0006] The present application provides a thermal protection device for the bottom of a recoverable rocket to improve the thermal protection effect of the recoverable rocket and enhance the payload and carrying capacity of the recoverable rocket.
[0007] In order to solve the above technical problems, this application provides the following technical solutions:
[0008] A heat protection device for the bottom of a recoverable rocket comprises: an evaporation part and a condensation part; the evaporation part is arranged at the bottom of the rocket, and a nozzle mounting hole is provided in the middle part of the evaporation part for the nozzle to extend from the inside of the rocket to the bottom of the rocket; the condensation part is arranged at the side of the tail section of the rocket, and the lower end of the condensation part is connected and communicated with the outer end of the evaporation part.
[0009] The recoverable rocket bottom thermal protection device as described above, wherein preferably, the evaporation part and the condensation part both include: an inner plate, a capillary wick on the lower plate, a lower capillary wick and a working medium; the inner plate and the lower plate are arranged in parallel, and an installation cavity is formed between the inner plate and the lower plate; the upper surface of the upper capillary wick is in contact and fixed with the inner surface of the inner plate, the lower surface of the lower capillary wick is in contact and fixed with the inner surface of the lower plate, and a steam cavity is formed between the lower surface of the upper capillary wick and the upper surface of the lower capillary wick; the liquid working medium is located in the upper capillary wick and the lower capillary wick, and the gaseous working medium is located in the steam cavity.
[0010] The recyclable rocket bottom thermal protection device as described above, wherein, preferably, the outer edge of the inner plate of the evaporation part is fixedly docked with the lower edge of the inner plate of the condensation part, and the outer edge of the lower plate of the evaporation part is fixedly docked with the lower edge of the lower plate of the condensation part; the outer edge of the upper capillary wick of the evaporation part is connected to the lower edge of the upper capillary wick of the condensation part, and the outer edge of the lower capillary wick of the evaporation part is connected to the lower edge of the lower capillary wick of the condensation part; the steam chamber of the evaporation part is connected to the steam chamber of the condensation part.
[0011] The recyclable rocket bottom thermal protection device as described above, wherein preferably, the evaporation part and the condensation part also include: a plurality of load-bearing columns; each load-bearing column passes through the upper capillary core and the lower capillary core, and is fixedly connected to the upper capillary core and the lower capillary core, one end of each load-bearing column is connected to the inner surface of the inner layer plate, and the other end of each load-bearing column is connected to the inner surface of the lower layer plate.
[0012] The recyclable rocket bottom thermal protection device as described above, wherein preferably, the evaporation part and the condensation part both comprise: an inner plate, a lower plate, a tube shell, a capillary wick and a working medium; the inner surface of the inner plate has an inwardly concave groove, the inner surface of the lower plate has an inwardly concave groove, the inner surface of the inner plate and the inner surface of the lower plate are in contact and fixed, and the groove of the inner plate and the groove of the lower plate are butt-jointed and connected to form an installation cavity;
[0013] The tube shell is clamped in the installation cavity, the capillary core is arranged in the tube shell, and the outer surface of the capillary core is fixedly connected to the inner surface of the tube shell; a steam cavity is formed in the middle of the capillary core, the liquid working medium is located in the capillary core, and the gaseous working medium is located in the steam cavity.
[0014] The recyclable rocket bottom thermal protection device as described above, wherein, preferably, the outer edge of the inner plate of the evaporation part is butt-jointed and fixed with the lower edge of the inner plate of the condensation part, the outer edge of the lower plate of the evaporation part is butt-jointed and fixed with the lower edge of the lower plate of the condensation part; the outer edge of the tube shell of the evaporation part is butt-jointed and fixed with the lower edge of the tube shell of the condensation part; the outer edge of the capillary core of the evaporation part is connected with the lower edge of the capillary core of the condensation part, and the steam chamber of the evaporation part is connected with the steam chamber of the condensation part.
[0015] The recyclable rocket bottom thermal protection device as described above, wherein preferably, the inner surfaces of the inner plates of the evaporation part and the condensation part are formed with a plurality of grooves, the inner surfaces of the lower plates of the evaporation part and the condensation part are formed with a plurality of grooves, and the evaporation part and the condensation part are formed with a plurality of installation cavities to set a plurality of tube shells and capillary cores.
[0016] The recoverable rocket bottom thermal protection device as described above, wherein preferably, the working medium is liquid metal.
[0017] The recyclable rocket bottom thermal protection device as described above, wherein preferably, the cooling structure includes: a cooling cover plate and fins; the edge of the cooling cover plate is fixedly connected to the inner plate of the condensation part, and a cavity is formed between the cooling cover plate and the inner plate of the condensation part; the fins extend from the outer surface of the inner plate of the condensation part into the cavity, dividing the cavity into a plurality of cooling channels extending up and down; the upper part of the cooling cover plate is provided with a coolant inlet to introduce rocket fuel into the cooling channel, and the lower part of the cooling cover plate is provided with a coolant outlet to transport the rocket fuel that absorbs heat in the cooling channel to the engine combustion chamber.
[0018] The recyclable rocket bottom thermal protection device as described above, wherein, preferably, the upper part of the cooling cover plate protrudes toward the inside of the rocket near the upper edge, and the protrusion extends a full circle along the circumference to form a coolant supply device; the coolant inlet is arranged on the coolant supply device, and the coolant inlet is arranged along the tangent direction of the coolant supply device; the lower part of the cooling cover plate protrudes toward the inside of the rocket near the lower edge, and the protrusion extends a full circle along the circumference to form a coolant collecting device; the coolant outlet is arranged on the coolant supply device, and the coolant outlet is arranged along the tangent direction of the coolant supply device and opposite to the direction of the coolant inlet.
[0019] Compared with the above-mentioned background technology, the thermal protection device at the bottom of the recoverable rocket provided in the present application can improve the thermal protection effect of the recoverable rocket, and enhance the payload and carrying capacity of the recoverable rocket. BRIEF DESCRIPTION OF THE DRAWINGS
[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.
[0021] Figure 1 is a three-dimensional diagram of a heat protection device for the bottom of a recoverable rocket provided in an embodiment of the present application;
[0022] Figure 2is a top view of a thermal protection device for the bottom of a recoverable rocket provided in an embodiment of the present application;
[0023] Figure 3 is a perspective view of a heat protection device for the bottom of a recoverable rocket provided in an embodiment of the present application;
[0024] Figure 4 This is a schematic diagram of the interior of the heat protection device at the bottom of the recoverable rocket provided in the embodiment of the present application. Figure 1 ;
[0025] Figure 5 This is a schematic diagram of the interior of the heat protection device at the bottom of the recoverable rocket provided in the embodiment of the present application. Figure 2 ;
[0026] Figure 6 is a longitudinal cross-sectional view of the cooling structure on the inner side of the condensation end of the thermal protection device at the bottom of the recoverable rocket provided in an embodiment of the present application;
[0027] Figure 7 It is a transverse cross-sectional view of the cooling structure on the inner side of the condensation end of the thermal protection device at the bottom of a recoverable rocket provided in an embodiment of the present application. DETAILED DESCRIPTION
[0028] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be interpreted as limiting the present invention.
[0029] like Figures 1 to 3 As shown, the present application provides a recoverable rocket bottom thermal protection device, including: an evaporator 110, a condenser 120 and a cooling structure 130; the evaporator 110 is arranged at the bottom of the rocket, and a nozzle mounting hole 111 is opened in the middle part of the evaporator 110, for the nozzle to extend from the inside of the rocket to the bottom of the rocket, and the evaporator 110 directly faces the impact and radiation of the engine tail flame; the condenser 120 is arranged at the outer side of the rocket tail section, and the lower end of the condenser 120 is connected and communicated with the outer end of the evaporator 110, so as to fully utilize the aerodynamic environment outside the side of the rocket body to achieve condensation; the cooling structure 130 is arranged at the inner side of the rocket tail section, and the cooling structure 130 is communicated with the rocket fuel tank, so as to utilize the rocket fuel as a coolant to achieve condensation.
[0030] When the tail flame of the engine generates high temperature, the working medium in the evaporation part 110 quickly absorbs heat and vaporizes, and quickly flows to the condensation part 120. Since the airflow around the outer side of the rocket body during flight can take away the heat of the condensation part 120, and the rocket fuel in the rocket fuel tank circulates to the cooling structure 130, it will also take away the heat of the condensation part 120. Therefore, the aerodynamic environment outside the side of the rocket body and the rocket fuel are used as coolants to achieve condensation, thereby transferring heat to the outside, thereby reducing the problem of local ablation. After condensing into a liquid state, the working medium will flow back to the evaporation part 110 to continue absorbing heat.
[0031] like Figure 4 As shown, the evaporation part 110 and the condensation part 120 both include: an inner plate 210, an upper capillary wick 230 of the lower plate 220, a lower capillary wick 240 and a working medium; the inner plate 210 and the lower plate 220 are arranged in parallel, and an installation cavity is formed between the inner plate 210 and the lower plate 220; the upper surface of the upper capillary wick 230 is in contact and fixed with the inner surface of the inner plate 210, and the lower surface of the lower capillary wick 240 is in contact and fixed with the inner surface of the lower plate 220. The capillary wick is a structural component with a capillary effect, which can enable the liquid working medium to be transmitted through the capillary phenomenon in the tiny pores or channels inside it; a steam cavity 250 is formed between the lower surface of the upper capillary wick 230 and the upper surface of the lower capillary wick 240, which can enable the gaseous working medium to flow inside it; the liquid working medium is located in the upper capillary wick 230 and the lower capillary wick 240, and the gaseous working medium is located in the steam cavity 250.
[0032] The outer edge of the inner plate 210 of the evaporation section 110 is fixedly docked with the lower edge of the inner plate 210 of the condensation section 120, and the outer edge of the lower plate 220 of the evaporation section 110 is fixedly docked with the lower edge of the lower plate 220 of the condensation section 120; the outer edge of the upper capillary wick 230 of the evaporation section 110 is connected to the lower edge of the upper capillary wick 230 of the condensation section 120, and the outer edge of the lower capillary wick 240 of the evaporation section 110 is connected to the lower edge of the lower capillary wick 240 of the condensation section 120, so that the steam chamber 250 of the evaporation section 110 is connected to the steam chamber 250 of the condensation section 120.
[0033] Optionally, the evaporation part 110 and the condensation part 120 further include: a plurality of bearing columns 260; each bearing column 260 passes through the upper capillary wick 230 and the lower capillary wick 240, and is fixedly connected to the upper capillary wick 230 and the lower capillary wick 240, one end of each bearing column 260 is connected to the inner surface of the inner plate 210, and the other end of each bearing column 260 is connected to the inner surface of the lower plate 220, and the bearing columns 260 can more firmly limit the position of the upper capillary wick 230 and the lower capillary wick 240 and ensure the stability of the spacing between the inner plate 210 and the lower plate 220. Optionally, all the bearing columns 260 are evenly distributed between the inner plate 210 and the lower plate 220, so as to more evenly limit the upper capillary wick 230 and the lower capillary wick 240 and the spacing between the inner plate 210 and the lower plate 220. Optionally, the inner plate 210, the lower plate 220 and the load-bearing column 260 are made of high-temperature resistant and high-strength materials to adapt to the harsh environment at the bottom of the rocket.
[0034] When the engine tail flame generates high temperature, the liquid working medium in the upper capillary wick 230 and the lower capillary wick 240 of the evaporation part 110 located at the bottom of the rocket quickly absorbs heat and vaporizes, and the vaporized gaseous working medium enters the steam chamber 250, and the gaseous working medium flows from the steam chamber 250 of the evaporation part 110 into the steam chamber 250 of the condensation part 120 located at the side of the tail section of the rocket; because the airflow around the outside of the side of the rocket body during flight can take away heat, the gaseous working medium located in the steam chamber 250 of the condensation part 120 condenses into liquid, and the liquid working medium is absorbed by the upper capillary wick 230 and the lower capillary wick 240 of the condensation part 120, and the liquid working medium flows from the upper capillary wick 230 and the lower capillary wick 240 of the condensation part 120 to the upper capillary wick 230 and the lower capillary wick 240 of the evaporation part 110 to continue absorbing heat.
[0035] like Figure 5As shown, the evaporation part 110 and the condensation part 120 both include: an inner plate 310, a lower plate 320, a tube shell 330, a capillary core 340 and a working medium; the inner surface of the inner plate 310 has an inwardly concave groove, and the inner surface of the lower plate 320 has an inwardly concave groove; the inner surface of the inner plate 310 and the inner surface of the lower plate 320 are in contact and fixed, and the groove of the inner plate 310 and the groove of the lower plate 320 are connected to form an installation cavity; the tube shell 330 is clamped in the installation cavity, and the capillary core 340 is The core 340 is arranged in the tube shell 330, and the outer surface of the capillary core 340 is fixedly connected to the inner surface of the tube shell 330. The capillary core is a structural component with capillary action, which can enable the liquid working medium to be transmitted through the tiny pores or channels inside it through capillary phenomenon; a steam chamber 350 is formed in the middle of the capillary core 340, which can enable the gaseous working medium to flow inside it; the liquid working medium is located in the capillary core 340, and the gaseous working medium is located in the steam chamber 350.
[0036] The outer edge of the inner plate 310 of the evaporation section 110 is docked and fixed to the lower edge of the inner plate 310 of the condensation section 120, and the outer edge of the lower plate 320 of the evaporation section 110 is docked and fixed to the lower edge of the lower plate 320 of the condensation section 120; the outer edge of the tube shell 330 of the evaporation section 110 is docked and fixed to the lower edge of the tube shell 330 of the condensation section 120; the outer edge of the capillary core 340 of the evaporation section 110 is connected to the lower edge of the capillary core 340 of the condensation section 120, so that the steam chamber 350 of the evaporation section 110 is connected to the steam chamber 350 of the condensation section 120.
[0037] Optionally, the inner surfaces of the inner plates 310 of the evaporation section 110 and the condensation section 120 are formed with a plurality of grooves, and the inner surfaces of the lower plates 320 of the evaporation section 110 and the condensation section 120 are also formed with a plurality of grooves, so that the evaporation section 110 and the condensation section 120 are formed with a plurality of installation cavities, and then a plurality of tube shells 330 and capillary cores 340 can be provided to improve the heat dissipation efficiency. Optionally, all the grooves formed by the inner plates 310 and the lower plates 320 are evenly distributed, so that the distribution of the tube shells 330 and the capillary cores 340 is also even, so that the heat dissipation efficiency is even. Optionally, the inner plates 310, the lower plates 320 and the tube shells 330 are made of high temperature resistant and high strength materials to adapt to the harsh environment at the bottom of the rocket.
[0038] Optionally, the evaporation part 110 is used as the bottom plate of the rocket bottom, and the inner plate 210 of the evaporation part 110 faces the inside of the rocket; the condensation part 120 is used as the skin of the side of the rocket tail section, and the inner plate 210 of the condensation part 120 faces the inside of the rocket, and the condensation part 120 is fastened to the adjacent arrow section. Also optionally, the inner plate 210 of the evaporation part 110 and the inner plate 210 of the condensation part 120 are both fixedly connected to the load-bearing parts of the rocket through mounting components, so as to ensure that they will not loosen or fall off during the launch and flight of the rocket. In addition, the mounting components have good thermal insulation properties, so as to avoid heat conduction from the mounting part to other parts of the rocket body. In addition, the mounting components need to be able to withstand various mechanical environments during the launch and flight of the rocket to ensure that they will not loosen or fall off during the working process.
[0039] Optionally, the working medium is a working fluid suitable for thermal protection of the rocket body, which has a suitable phase change temperature, high thermal conductivity, stability and reliability, and can efficiently transfer heat within a wide temperature range. Also optionally, the working medium is an alkali metal. Since the melting and boiling points of alkali metals are very high, the recoverable rocket bottom thermal protection device of the present application is suitable for high temperature and large heat flow heat transfer occasions. Also optionally, the working medium is other liquid metals, such as gallium-indium alloys. Since this liquid metal has an extremely low melting point and an extremely high boiling point, it can remain liquid within a wide temperature range, thereby achieving efficient heat transfer. In addition, the thermal conductivity of the liquid metal is also very high, and the heat absorbed by the evaporation part can be quickly transferred to the condensation part. Also optionally, the upper capillary wick 230, the lower capillary wick 240 and the capillary wick 340 can be porous nickel-based alloys, stainless steel wire mesh, nickel wire mesh, sintered metal powder, carbon fiber, porous ceramics, etc.
[0040] Optionally, the evaporation portion 110 is in the shape of a ring, and the condensation portion 120 is in the shape of a strip or a sheet. The shape, size, and distribution position of the evaporation end and the condensation end should be optimized and designed according to the structure of the rocket body and the characteristics of the engine tail flame, so as to ensure that the evaporation end can effectively absorb the heat of the engine tail flame, and the condensation end can make full use of the aerodynamic environment of the outer wall of the rocket body for condensation.
[0041] like Figure 3 , Figure 6 and Figure 7As shown, the cooling structure 130 includes: a cooling cover plate 131 and fins 132; the edge of the cooling cover plate 131 is fixedly connected to the inner plate 210 / 310 of the condensation section 120, and a cavity is formed between the cooling cover plate 131 and the inner plate 210 / 310 of the condensation section 120; the fins 132 extend from the outer surface of the inner plate 120 of the condensation section into the cavity, thereby dividing the cavity into a plurality of cooling channels 133 extending up and down; a coolant inlet 134 is provided at the upper portion of the cooling cover plate 131 to introduce rocket fuel into the cooling channel 133, and a coolant outlet 135 is provided at the lower portion of the cooling cover plate 131 to transport the rocket fuel that absorbs heat in the cooling channel 133 to the engine combustion chamber.
[0042] Optionally, the upper portion of the cooling cover 131 protrudes toward the inside of the rocket near the upper edge, and the protrusion extends a full circle along the circumference, thereby forming a coolant supply device 136; the coolant inlet 134 is arranged on the coolant supply device 136, and the coolant inlet 134 is arranged along the tangent direction of the coolant supply device 136, so that after the coolant enters the coolant inlet 134, the coolant will first flow circumferentially along the cavity in the coolant supply device 136 and gradually enter the cooling channel 133 extending up and down; the lower portion of the cooling cover 131 The position near the lower edge protrudes toward the inside of the rocket, and the protrusion extends circumferentially for a full circle, thereby forming a coolant collecting device 137; the coolant outlet 135 is arranged on the coolant supply device 137, and the coolant outlet 135 is arranged along the tangent direction of the coolant supply device 137, and is opposite to the direction of the coolant inlet 134, so that after the coolant flows into the coolant collecting device 137 from the cooling channel 133 extending up and down, the coolant will first flow circumferentially along the cavity in the coolant collecting device 137 and then flow out from the coolant outlet 135.
[0043] The present application utilizes the high thermal conductivity of the working medium to quickly transfer the heat from the bottom of the rocket body to the tail section of the rocket body, and utilizes the aerodynamic environment outside the rocket body to achieve condensation. The present application also utilizes rocket fuel as a coolant, and achieves condensation through a cooling channel arranged on the inner side of the condensation end. The combined effect of the inside and outside effectively reduces the temperature of the bottom of the rocket body and improves the thermal protection effect. The condensation part directly replaces the original skin structure, and the evaporation part directly replaces the original bottom plate. Compared with traditional insulation materials and coatings, the overall weight of the rocket is reduced, and the rocket's payload and carrying capacity are improved.
[0044] In addition, since the heat protection device at the bottom of the recoverable rocket of the present application has good heat protection effect and reliability, it can reduce the heat damage of the rocket body during the recovery process and improve the safety and reliability of the rocket recovery stage. And combined with the high-temperature phase change characteristics of the working medium, the stability and efficiency of the device at extreme temperatures are improved.
[0045] It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above and that the invention can be implemented in other specific forms without departing from the spirit or essential features of the invention. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description, and it is intended that all variations falling within the meaning and scope of the equivalent elements of the claims be included in the invention. Any reference numeral in a claim should not be considered as limiting the claim to which it relates.
[0046] In addition, it should be understood that although the present specification is described according to implementation modes, not every implementation mode contains only one independent technical solution. This description of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment may also be appropriately combined to form other implementation modes that can be understood by those skilled in the art.
Claims
1. A thermal protection device for the bottom of a recoverable rocket, characterized in that: include: Evaporation section, condensation section and cooling structure; The evaporator is arranged at the bottom of the rocket, and a nozzle installation hole is provided in the middle of the evaporator for the nozzle to extend from the inside of the rocket to the bottom of the rocket; The condensation part is arranged at the outer side of the rocket tail section, and the lower end of the condensation part is connected and communicated with the outer end of the evaporation part; The cooling structure is arranged at the inner side of the rocket tail section, and the cooling structure is communicated with the rocket fuel tank.
2. The recoverable rocket bottom thermal protection device according to claim 1, characterized in that: The evaporation part and the condensation part both include: an inner plate, a capillary wick on the lower plate, a lower capillary wick and a working medium; The inner plate and the lower plate are arranged in parallel, and a mounting cavity is formed between the inner plate and the lower plate; The upper surface of the upper capillary wick is fixedly contacted with the inner surface of the inner plate, the lower surface of the lower capillary wick is fixedly contacted with the inner surface of the lower plate, and a steam cavity is formed between the lower surface of the upper capillary wick and the upper surface of the lower capillary wick; The liquid working medium is located in the upper capillary wick and the lower capillary wick, and the gaseous working medium is located in the steam chamber.
3. The recoverable rocket bottom thermal protection device according to claim 2, characterized in that: The outer edge of the inner plate of the evaporation part is fixedly butted against the lower edge of the inner plate of the condensation part, and the outer edge of the lower plate of the evaporation part is fixedly butted against the lower edge of the lower plate of the condensation part; The outer edge of the upper capillary wick of the evaporation part is connected to the lower edge of the upper capillary wick of the condensation part, and the outer edge of the lower capillary wick of the evaporation part is connected to the lower edge of the lower capillary wick of the condensation part; The steam chamber of the evaporation part is communicated with the steam chamber of the condensation part.
4. The recoverable rocket bottom thermal protection device according to claim 2 or 3, characterized in that: Both the evaporation part and the condensation part further include: a plurality of load-bearing columns; Each load-bearing column passes through the upper capillary core and the lower capillary core and is fixedly connected to the upper capillary core and the lower capillary core. One end of each load-bearing column is connected to the inner surface of the inner layer board, and the other end of each load-bearing column is connected to the inner surface of the lower layer board.
5. The recoverable rocket bottom thermal protection device according to claim 1, characterized in that: The evaporation part and the condensation part both include: an inner plate, a lower plate, a tube shell, a capillary core and a working medium; The inner surface of the inner plate has an inwardly concave groove, the inner surface of the lower plate has an inwardly concave groove, the inner surface of the inner plate and the inner surface of the lower plate are in contact and fixed, and the groove of the inner plate and the groove of the lower plate are butted and connected to form an installation cavity; The tube shell is clamped in the installation cavity, the capillary core is arranged in the tube shell, and the outer surface of the capillary core is fixedly connected to the inner surface of the tube shell; A steam chamber is formed in the middle of the capillary core, a liquid working medium is located in the capillary core, and a gaseous working medium is located in the steam chamber.
6. The recoverable rocket bottom thermal protection device according to claim 5, characterized in that: The outer edge of the inner plate of the evaporation part is fixedly butted against the lower edge of the inner plate of the condensation part, and the outer edge of the lower plate of the evaporation part is fixedly butted against the lower edge of the lower plate of the condensation part; The outer edge of the tube shell of the evaporation part is butted and fixed with the lower edge of the tube shell of the condensation part; The outer edge of the capillary core of the evaporation part is connected to the lower edge of the capillary core of the condensation part, and the steam cavity of the evaporation part is communicated with the steam cavity of the condensation part.
7. The recoverable rocket bottom thermal protection device according to claim 5 or 6, characterized in that: The inner surfaces of the inner plates of the evaporation part and the condensation part are formed with a plurality of grooves, the inner surfaces of the lower plates of the evaporation part and the condensation part are formed with a plurality of grooves, and the evaporation part and the condensation part are formed with a plurality of installation cavities to set a plurality of tube shells and capillary cores.
8. The recoverable rocket bottom thermal protection device according to claim 2 or 5, characterized in that: The working medium is liquid metal.
9. The recoverable rocket bottom thermal protection device according to claim 2 or 5, characterized in that: The cooling structure includes: a cooling cover plate and fins; The edge of the cooling cover plate is fixedly connected to the inner plate of the condensation part, and a cavity is formed between the cooling cover plate and the inner plate of the condensation part; The fins extend from the outer surface of the inner plate of the condensation part into the cavity, dividing the cavity into a plurality of cooling channels extending up and down; The upper part of the cooling cover plate is provided with a coolant inlet for introducing rocket fuel into the cooling channel, and the lower part of the cooling cover plate is provided with a coolant outlet for transporting the rocket fuel that absorbs heat in the cooling channel to the combustion chamber.
10. The recoverable rocket bottom thermal protection device according to claim 9, characterized in that: The upper portion of the cooling cover plate protrudes toward the inside of the rocket near the upper edge, and the protrusion extends along the circumference of a whole circle to form a coolant supply device; The coolant inlet is arranged on the coolant supply device, and the coolant inlet is arranged along the tangent direction of the coolant supply device; The lower portion of the cooling cover plate protrudes toward the inside of the rocket near the lower edge, and the protrusion extends along the circumference of a whole circle to form a coolant collecting device; The coolant outlet is arranged on the coolant supply device, and the coolant outlet is arranged along the tangent direction of the coolant supply device and is opposite to the direction of the coolant inlet.