A hypersonic vehicle nose cone and a hypersonic vehicle having the nose cone

Abstract

The present invention relates to the technical field of thermal protection for hypersonic aircraft, and provides a hypersonic aircraft nose cone and a hypersonic aircraft having the nose cone. The nose cone includes a conical outer shell and an inner shell. The middle of the head ends of the outer shell and the inner shell are connected by a connecting pipe, and jet holes penetrating the head ends of the inner and outer shells are provided in the middle of the connecting pipe; the tail ends of the outer shell and the inner shell are sealed by a tail plate to form a heat-dissipating outer cavity, and side ribs are arranged along the radial direction to divide the outer cavity into multiple sub-chambers. A capillary structure layer is provided on the inner wall of the sub-chambers, and an alkali metal working medium is filled in the sub-chambers; a rear end cover is provided at the tail of the inner shell, a cooling pipe is installed in the middle mounting hole of the rear end cover, a hemispherical head is provided at the head end of the cooling pipe, and impinging jet pipes are arranged along the radial direction on the part of the cooling pipe located inside the inner shell. The present invention can realize the coupling among the heat pipe guidance passive heat protection, cavity passive heat protection, jet impingement active heat protection, and reverse jet active heat protection modes according to the aerodynamic heat environment with a simple structure, and improve the thermal protection efficiency and effect.

Description

Technical Field

[0001] The present invention relates to the technical field of hypersonic aircraft thermal protection, and in particular to a hypersonic aircraft nose cone and a hypersonic aircraft having the nose cone. Background Art

[0002] When a hypersonic vehicle is flying at high speed, the surface temperature of its nose cone can reach 2000 to 3000 degrees Celsius without thermal protection measures, and it is impossible to keep the component's shape and structure intact at high temperatures. Therefore, the nose cone needs to be thermally protected. Local thermal protection technology suitable for long-duration, wide-speed range, and hypersonic flight is also the key point for the application of future key technologies related to hypersonic vehicles.

[0003] The existing thermal protection technologies for the nose cone of hypersonic aircraft mainly include ablation passive thermal protection technology, heat pipe conduction thermal protection technology, and convection active cooling thermal protection technology:

[0004] (1) The ablative passive thermal protection technology coats the shell surface that needs to be protected from heat with ablative materials. During the thermal decomposition and oxidative combustion of the ablative materials, the heat is removed from the shell surface through the continuous loss of pyrolysis gas and combustion products, thereby achieving a thermal protection effect. This technology is difficult to maintain the integrity of the component shape for a long time due to the loss of ablative materials.

[0005] (2) Heat pipe passive thermal protection technology attaches a capillary structure layer in the high-temperature metal cavity and fills the cavity with alkali metal working fluid. When the outer surface of the head cone is aerodynamically heated, the outer wall of the cone heat pipe with the capillary structure layer acts as the evaporation end. The alkali metal working fluid forms a thin film structure in the capillary structure and evaporates to absorb heat. The metal vapor flows to the inner wall of the cone heat pipe under the pressure difference in the cavity, condenses and releases heat at the condensation end, and the condensed liquid flows to the evaporation end under the action of capillary force, thus forming a fluid flow and heat exchange cycle. Due to the high efficiency of this phase change heat transfer, the cone heat pipe generally presents good temperature uniformity, which not only reduces the temperature of the cone head, but also reduces the thermal stress caused by the temperature gradient inside the structure. However, on the one hand, due to its working limits, this technology is difficult to operate stably when flying at higher Mach numbers and facing higher aerodynamic thermal environments; on the other hand, the existing heat pipe passive thermal protection technology forms a conical heat-relief cavity in the entire nose cone body. Under this conical heat pipe configuration, when the liquid working fluid evaporates at the head of the cone and flows to the tail end of the cone, the cavity space increases sharply, resulting in insufficient steam density and pressure, making it difficult to form a circulating flow of the working fluid, and thus difficult to apply to the thermal protection of the nose cone.

[0006] (3) Among the convective active cooling thermal protection technologies, reverse jet thermal protection is an active and efficient cooling method that can push the shock wave at the cone head away from the heated components, improve the heating environment, and generate convective heat transfer on the cone surface to alleviate the severity of aerodynamic heating. It has high cooling efficiency and is more suitable for cooling components under high Mach numbers and high heat flux densities. However, it needs to carry a large amount of cooling fluid during long-term flight, and the load cost is relatively high. Summary of the invention

[0007] In view of the problems existing in the prior art, the present invention provides a hypersonic aircraft nose cone and a hypersonic aircraft having the nose cone, which cleverly combines a heat pipe guidance passive thermal protection structure, a concave cavity passive thermal protection structure, a jet impact active thermal protection structure, and a reverse jet active thermal protection structure in one device with a simple structure, and can couple different thermal protection methods according to the severity of the aerodynamic thermal environment during high-speed flight to achieve adaptive active and passive composite thermal protection of the nose cone, greatly improve the thermal protection efficiency, and enhance the thermal protection effect.

[0008] The technical solution of the present invention is:

[0009] A hypersonic aircraft nose cone, comprising an outer shell 1, an inner shell 2 is arranged inside the outer shell 1, the outer shell 1 and the inner shell 2 are both conical, the middle part of the head end of the outer shell 1 is connected to the middle part of the head end of the inner shell 2 through a connecting pipe 7, and a jet hole penetrating the head end of the outer shell 1 and the head end of the inner shell 2 is opened in the middle part of the connecting pipe 7;

[0010] The tail end of the outer shell 1 is sealed with the tail end of the inner shell 2 through an annular tail plate 9. A heat dissipation outer cavity is formed between the outer shell 1, the inner shell 2, the connecting pipe 7 and the tail plate 9, and a side rib 8 is arranged radially. There are a plurality of side ribs 8 and they are evenly distributed along the circumference of the outer shell 1. The side ribs 8 divide the heat dissipation outer cavity into a plurality of sub-chambers. The inner walls of the sub-chambers are provided with a capillary structure layer. The sub-chambers are filled with an alkali metal working medium.

[0011] A rear end cover 3 is provided on the inner side wall of the tail end of the inner shell 2, and an impact jet inner cavity is formed between the inner shell 2 and the rear end cover 3. A mounting hole coaxial with the jet hole is opened in the middle of the rear end cover 3, and a cooling pipe 4 is provided in the mounting hole. The outer diameter of the cooling pipe 4 is smaller than the inner diameter of the mounting hole. The head end of the cooling pipe 4 is located inside the inner shell 2, and the tail end extends out of the inner shell 2 after passing through the mounting hole. The head end of the cooling pipe 4 is closed and provided with a hemispherical head 6. The outer diameter of the hemispherical head 6 is larger than the inner diameter of the jet hole. The part of the cooling pipe 4 located inside the inner shell 2 is radially extended outward with an impact jet tube 5. There are more than two impact jet tubes 5 and they are evenly distributed along the circumference of the cooling pipe 4.

[0012] Further, there are four impact jet tubes 5.

[0013] Further, there are four side ribs 8.

[0014] Further, the outer housing 1, the inner housing 2, the connecting pipe 7, the side ribs 8, and the tail plate 9 are integrally formed.

[0015] Further, the materials of the outer housing 1, the inner housing 2, the connecting pipe 7, the side ribs 8, the tail plate 9, and the rear end cover 3 are all superalloys.

[0016] Further, the material of the cooling pipe 4 is metal.

[0017] Further, it includes a temperature sensor, a drive transmission device, and a controller; the temperature sensor is arranged in one of the sub-chambers, the output end of the temperature sensor is connected to the input end of the controller, the drive transmission device is connected to the outer wall of the tail of the cooling pipe 4, the input end of the power element of the drive transmission device is electrically connected to the output end of the controller, the temperature sensor is used to measure the temperature inside the sub-chamber and transmit the measured temperature data to the controller, the controller is used to send a first control signal to the power element when the temperature is lower than a preset temperature threshold, and send a second control signal to the power element when the temperature is equal to or higher than the preset temperature threshold, and the drive transmission device is used to control the cooling pipe 4 to move towards the direction close to the jet hole when receiving the first control signal, and control the cooling pipe 4 to move away from the jet hole when receiving the second control signal.

[0018] A hypersonic aircraft, the hypersonic aircraft nose cone as described above is installed at the front end of the hypersonic aircraft.

[0019] The beneficial effects of the present invention are:

[0020] (1) By arranging a conical inner housing inside the conical outer housing, a connecting pipe between the head ends of the inner and outer housings, sealing and connecting the tail ends of the inner and outer housings with a tail plate to form a heat-dissipating outer cavity, arranging side ribs to divide the heat-dissipating outer cavity into multiple sub-chambers, arranging a capillary structure layer on the inner wall of the sub-chambers, and filling an alkali metal working fluid in the sub-chambers, multiple conforming metal heat pipe outer cavities are formed. On the one hand, heat pipe guidance passive heat protection is realized, which can quickly conduct heat from the nose cone, reduce the temperature peak value in the stagnation area where aerodynamic heating is the most severe, and make the outer surface of the nose cone show better temperature uniformity, reducing both the temperature gradient and the thermal stress caused by the temperature gradient inside the metal structure. On the other hand, compared with the heat pipe guidance passive heat protection technology that forms a conical heat-dissipating cavity inside the entire nose cone body in the prior art, the larger space inside the outer housing is divided into multiple smaller sub-chambers by the inner and outer housings and the side rib structure, so that the working fluid of the heat pipe is enclosed in a more limited space. When the liquid working fluid evaporates at the head of the cone and flows to the tail of the cone, there is sufficient steam density and pressure, which is easy to form a working fluid circulation flow, solving the technical problem that in the existing cone heat pipe configuration, when the liquid working fluid evaporates at the head of the cone and flows to the tail of the cone, the cavity space increases sharply, resulting in insufficient steam density and pressure and making it difficult to form a working fluid circulation flow, and greatly improving the efficiency of heat pipe guidance passive heat protection and greatly enhancing the heat protection effect.

[0021] (2) By opening a jet hole penetrating the head ends of the inner and outer housings in the connecting pipe, arranging a rear end cover at the tail of the inner housing, opening an installation hole in the middle of the rear end cover, arranging a cooling pipe with an outer diameter smaller than the inner diameter of the installation hole in the installation hole, and closing the head end of the cooling pipe and arranging a hemispherical head, it is possible to control the movement of the cooling pipe towards the jet hole direction during low Mach number flight, so that the hemispherical head moves forward and abuts against the tail end of the jet hole, presenting a closed state of the jet hole, forming an openable concave cavity in the stagnation area, realizing concave cavity passive heat protection, and thus using the energy dissipation caused by the oscillation of the oncoming flow in the concave cavity to reduce the heat flux on the surface of the aircraft, further enhancing the heat protection effect.

[0022] (3) In the present invention, an impact jet inner cavity is formed by arranging a rear end cover on the inner side wall of the tail of the inner shell. An impact jet device is formed by opening an installation hole in the middle of the rear end cover, arranging a cooling tube with an outer diameter smaller than the inner diameter of the installation hole in the installation hole, and evenly arranging impact jet tubes pointing to the inner shell circumferentially around the cooling tube, so as to form a jet impact active cooling inner cavity. During high Mach number flight, the movement of the cooling tube away from the jet hole can be controlled, making the hemispherical head and the tail end of the jet hole in an open state. On the one hand, the impact jet device can send cooling gas into the impact jet tubes through the cooling tube and impact the inner surface of the inner shell through the jet holes, achieving impact strengthening cooling of the inner shell, realizing jet impact active heat protection, and at the same time accelerating the condensation heat release of the steam in the outer cavity of the conformal metal heat pipe at the condensation end, accelerating the working fluid flow and heat transfer cycle in the outer cavity of the conformal metal heat pipe, greatly improving the heat conduction efficiency of the outer cavity of the conformal metal heat pipe and expanding the high-temperature working range of the outer cavity of the conformal metal heat pipe. On the other hand, the cooling gas jetting into the inner shell is ejected reversely from the jet holes in the stagnation region after the impact process, performing convective cooling on the outer surface of the nose cone. Specifically, the reversely ejected cooling gas can change the flow field outside the nose cone, making the detached shock wave far away from the outer shell, reducing the severity of aerodynamic heating in the stagnation region, promoting the reduction of the stagnation temperature, and at the same time forming a protective gas film on the surface of the outer shell, realizing reverse jet active heat protection, further improving the cooling efficiency and strengthening the cooling effect.

[0023] (4) The present invention ingeniously combines the heat pipe conduction passive heat protection structure, the cavity passive heat protection structure, the jet impact active heat protection structure, and the reverse jet active heat protection structure in one device by using a simple structure. It can control the opening and closing of the jet holes according to the severity of the aerodynamic heat environment during high-speed flight, carry out the coupling between different heat protection methods, make the best use of their advantages, and achieve the adaptive main-passive composite heat protection of the nose cone, greatly improving the heat protection efficiency, enhancing the heat protection effect, reducing the thermal stress on the structure, and opening the reverse jet heat protection according to environmental requirements, saving the usage amount of the cooling working fluid, solving the technical problem that the existing reverse jet heat protection technology needs to carry a large amount of cooling working fluid during long-term flight, resulting in a high load cost. It has high reliability and flexibility and is suitable for the heat protection of reusable hypersonic aircraft with long endurance and wide speed range.

[0024] (5) The present invention can automatically control the forward and backward movement of the cooling pipe according to the temperature inside the sub-chamber by arranging a temperature sensor in the sub-chamber, arranging a driving transmission device on the outer wall of the tail of the cooling pipe, and connecting a controller to the temperature sensor and the power element of the driving transmission device, so as to realize the automatic switching of different heat protection methods, that is, when the temperature is lower than the preset temperature threshold, the cooling pipe is controlled to move towards the direction close to the jet hole to close the jet hole for cavity passive heat protection, and when the temperature is equal to or higher than the preset temperature threshold, the cooling pipe is controlled to move away from the jet hole to open the jet hole for jet impingement active heat protection and reverse jet active heat protection. Description of the Drawings

[0025] Figure 1 It is the front view of the hypersonic vehicle nose cone of the present invention in the specific embodiment.

[0026] Figure 2 It is Figure 1 the sectional view taken along the line A-A of

[0027] Figure 3 It is Figure 2 the sectional view taken along the line B-B of

[0028] Figure 4 It is Figure 2 the sectional view taken along the line C-C of

[0029] Figure 5 It is the three-dimensional structure schematic diagram of the impinging jet channel in the hypersonic vehicle nose cone of the present invention in the specific embodiment.

[0030] In the figure, 1 - outer shell, 2 - inner shell, 3 - rear end cover, 4 - cooling pipe, 5 - impinging jet pipe, 6 - hemispherical head, 7 - connecting pipe, 8 - side rib, 9 - tail plate. Specific Embodiments

[0031] The present invention will be further described below in conjunction with the drawings and specific embodiments.

[0032] As Figure 1 , Figure 2 , Figure 3 shown, the hypersonic vehicle nose cone of the present invention includes an outer shell 1, an inner shell 2 is arranged inside the outer shell 1, both the outer shell 1 and the inner shell 2 are conical, the middle of the head end of the outer shell 1 is connected to the middle of the head end of the inner shell 2 through a connecting pipe 7, and a jet hole penetrating the head end of the outer shell 1 and the head end of the inner shell 2 is opened in the middle of the connecting pipe 7;

[0033] The tail end of the outer housing 1 is hermetically connected to the tail end of the inner housing 2 through an annular tail plate 9. A heat-dissipating outer cavity is formed between the outer housing 1, the inner housing 2, the connecting pipe 7, and the tail plate 9, and side ribs 8 are arranged radially. There are multiple side ribs 8, which are evenly distributed along the circumference of the outer housing 1. The side ribs 8 divide the heat-dissipating outer cavity into multiple sub-chambers. The inner wall of the sub-chamber is provided with a capillary structure layer (not shown in the figure), and the sub-chamber is filled with an alkali metal working fluid;

[0034] A rear end cover 3 is arranged on the inner side wall of the tail part of the inner housing 2. An impinging jet inner cavity is formed between the inner housing 2 and the rear end cover 3. An installation hole coaxial with the jet hole is opened in the middle of the rear end cover 3, and a cooling pipe 4 is arranged in the installation hole. The outer diameter of the cooling pipe 4 is smaller than the inner diameter of the installation hole. As Figure 4 shown, the head end of the cooling pipe 4 is located inside the inner housing 2, and the tail end passes through the installation hole and extends out of the inner housing 2. The head end of the cooling pipe 4 is closed and provided with a hemispherical head 6. The outer diameter of the hemispherical head 6 is larger than the inner diameter of the jet hole. The part of the cooling pipe 4 located inside the inner housing 2 extends radially outward to form impinging jet pipes 5. There are more than two impinging jet pipes 5, which are evenly distributed along the circumference of the cooling pipe 4.

[0035] In the present invention, by arranging a conical inner housing 2 inside the conical outer housing 1, arranging a connecting pipe 7 between the head ends of the inner and outer housings, hermetically connecting the tail ends of the inner and outer housings with a tail plate 9 to form a heat-dissipating outer cavity, arranging side ribs 8 to divide the heat-dissipating outer cavity into multiple sub-chambers, arranging a capillary structure layer on the inner wall of the sub-chamber, and filling the sub-chamber with an alkali metal working fluid, multiple conforming metal heat pipe outer cavities are formed. On the one hand, heat pipe guidance passive heat protection is realized, and rapid heat guidance can be carried out on the nose cone, so that the temperature peak value in the stagnation area with the most serious aerodynamic heating is reduced, and the nose cone outer surface shows better temperature uniformity, which not only reduces the temperature gradient but also reduces the thermal stress caused by the temperature gradient inside the metal structure; on the other hand, compared with the heat pipe guidance passive heat protection technology in the prior art that forms a conical heat dissipation cavity inside the entire nose cone body, the larger space inside the outer housing is divided into multiple smaller sub-chambers through the inner and outer housings and the side rib structure, so that the working fluid of the heat pipe is enclosed in a more limited space, making it easy to form a working fluid circulation flow when the liquid working fluid evaporates at the cone head and flows to the cone tail, because there is enough steam density and pressure. This solves the technical problem in the existing cone heat pipe configuration that when the liquid working fluid evaporates at the cone head and flows to the cone tail, the cavity space increases sharply, resulting in insufficient steam density and pressure and making it difficult to form a working fluid circulation flow, and greatly improves the efficiency of heat pipe guidance passive heat protection and greatly enhances the heat protection effect.

[0036] Each part of the conformal metal heat pipe's outer cavity can be formed separately and then connected together, or it can be integrally formed. In this embodiment, the outer shell 1, the inner shell 2, the connecting pipe 7, the side ribs 8, and the tail plate 9 are integrally formed.

[0037] In the present invention, by opening a jet hole penetrating the head ends of the inner and outer shells in the connecting pipe 7, arranging a rear end cover 3 at the tail of the inner shell 2, opening an installation hole in the middle of the rear end cover 3, arranging a cooling pipe 4 with an outer diameter smaller than the inner diameter of the installation hole in the installation hole, and closing the head end of the cooling pipe 4 and arranging a hemispherical head 6, it is possible to control the movement of the cooling pipe 4 towards the jet hole direction during low Mach number flight, so that the hemispherical head 6 moves forward to abut against the tail end of the jet hole, presenting a closed state of the jet hole, forming a concave cavity with an openable stagnation region, realizing passive heat protection of the concave cavity, and thus using the energy dissipation caused by the oscillation of the oncoming flow in the concave cavity to reduce the heat flux on the surface of the aircraft, further enhancing the heat protection effect.

[0038] In the present invention, a rear end cover 3 is arranged on the inner side wall at the tail of the inner shell 2 to form an impinging jet inner cavity. By opening an installation hole in the middle of the rear end cover 3, arranging a cooling pipe 4 with an outer diameter smaller than the inner diameter of the installation hole in the installation hole, and evenly arranging impinging jet pipes 5 pointing towards the inner shell 2 in the circumferential direction of the cooling pipe 4 to form an impinging jet device, thereby forming an impinging jet actively cooled inner cavity body. During high Mach number flight, it is possible to control the movement of the cooling pipe 4 in a direction away from the jet hole, so that the hemispherical head 6 is in an open state with the tail end of the jet hole. On the one hand, it is possible to use the impinging jet device to send the cooling gas into the impinging jet pipes 5 through the cooling pipe 4 and impact the inner surface of the inner shell 2 through the jet holes, performing impinging jet enhanced cooling on the inner shell 2, realizing impinging jet active heat protection, and at the same time accelerating the condensation heat release of the steam in the outer cavity of the conformal metal heat pipe at the condensation end, accelerating the working fluid flow and heat transfer cycle in the outer cavity of the conformal metal heat pipe, greatly improving the heat conduction efficiency of the outer cavity of the conformal metal heat pipe, and expanding the high-temperature working range of the outer cavity of the conformal metal heat pipe; on the other hand, the cooling gas impinging into the inner shell 2 is reversely ejected from the jet holes in the stagnation region after the impinging process, performing convective cooling on the outer surface of the nose cone. Specifically, the reversely ejected cooling gas can change the flow field outside the nose cone, making the detached shock wave away from the outer shell 1, reducing the severity of aerodynamic heating in the stagnation region, promoting the reduction of the stagnation temperature, and at the same time forming a protective gas film on the surface of the outer shell 1, realizing reverse jet active heat protection, further improving the cooling efficiency and strengthening the cooling effect.

[0039] Among them, the number of impinging jet pipes 5 can be set according to requirements. In this embodiment, as Figure 4 shown, four impinging jet pipes 5 are arranged, and the material of the cooling pipe 4 is metal.

[0040] The number of the side ribs 8 can be set according to requirements. By adjusting the number of the side ribs 8, the number of the separated sub-chambers can be adjusted, so as to adjust the space size of the sub-chambers. In this embodiment, as Figure 3 shown, 4 side ribs 8 are provided, and the heat-dissipating outer cavity is separated into 4 sub-chambers with more limited space.

[0041] In this embodiment, the outer housing 1, the inner housing 2, the connecting pipe 7, the side ribs 8, the tail plate 9, and the rear end cover 3 are all made of superalloy materials, which can improve the heat protection effect.

[0042] The present invention ingeniously combines a heat pipe diversion passive heat protection structure, a concave cavity passive heat protection structure, a jet impingement active heat protection structure, and a reverse jet active heat protection structure in a device with a simple structure. It can control the opening and closing of the jet holes according to the severity of the aerodynamic heat environment during high-speed flight, and carry out the coupling between different heat protection methods, making the best use of their advantages, realizing the adaptive active and passive composite heat protection of the nose cone, greatly improving the heat protection efficiency, enhancing the heat protection effect, reducing the thermal stress on the structure, and opening the reverse jet heat protection according to the environmental requirements, saving the usage amount of the cooling working medium, solving the technical problem that the existing reverse jet heat protection technology needs to carry a large amount of cooling working medium during long-term flight, resulting in a high load cost. It has high reliability and flexibility, and is applicable to the heat protection of the next-generation reusable hypersonic aircraft with long endurance and wide speed range.

[0043] The working principle of the present invention will be described below with reference to the accompanying drawings:

[0044] The nose cone of the present invention can combine different cooling methods according to the severity of the aerodynamic heat environment during high-speed flight. During low Mach number flight, the heat flux density is low, and the heat pipe diversion passive heat protection method with a conformal metal heat pipe outer cavity is used for the dominant heat protection, and the concave cavity passive heat protection can also be additionally used. As the Mach number continues to increase and the heat flux density increases, the nose cone faces an extreme heating environment, and jet impingement active heat protection and reverse jet active heat protection can be additionally used. The cold flow first intensively impacts and cools the condensation end wall surface of the diversion heat pipe, further improving the heat diversion efficiency of the diversion heat pipe, and then the cold air flows out reversely from the head of the cone. Through the actions of pushing away the head shock wave and forming convective cooling on the cone surface, a better heat protection effect is achieved. Among them, the jet holes at the head of the cone are opened and closed under the axial movement of the central cooling pipe in the jet impingement active cooling inner cavity, and can form a concave cavity passive heat protection structure during low Mach number flight and a reverse jet active heat protection structure during high Mach number flight. This method of controlling the start and stop of the active cooling method and the flow rate of the cooling working medium according to the flight state and the severity of the aerodynamic heating, combined with the heat pipe diversion passive heat protection method and the concave cavity passive heat protection method, can solve the local heat protection problem during long endurance, wide speed range, and hypersonic flight.

[0045] In order to achieve the automatic coupling between different heat protection methods, in this embodiment, a temperature sensor, a driving transmission device, and a controller are further provided. The temperature sensor is disposed in one of the sub-chambers. The output end of the temperature sensor is connected to the input end of the controller. The driving transmission device is connected to the outer wall of the tail of the cooling pipe 4. The input end of the power element of the driving transmission device is electrically connected to the output end of the controller. The temperature sensor is used to measure the temperature inside the sub-chamber and transmit the measured temperature data to the controller. The controller is used to send a first control signal to the power element when the temperature is lower than a preset temperature threshold, and send a second control signal to the power element when the temperature is equal to or higher than the preset temperature threshold. The driving transmission device is used to control the cooling pipe 4 to move towards the direction close to the jet hole when receiving the first control signal, and control the cooling pipe 4 to move away from the jet hole when receiving the second control signal. Among them, the driving transmission device can be in various forms as long as it can realize the linear reciprocating motion of the cooling pipe 4. The driving transmission device includes a power element and a transmission mechanism, and can be a motor-driven cam transmission mechanism or a gear-rack transmission mechanism, or can also be a hydraulic driving transmission mechanism.

[0046] In addition, the pressure of the cooling working medium entering the cooling pipe 4 can also be controlled according to requirements, so as to control the jet velocity of the impinging jet pipe 5 and the jet velocity of the jet hole, and realize the control of the heat protection intensity of the jet impingement active heat protection and the reverse jet active heat protection.

[0047] The present invention also provides a hypersonic vehicle, and the front end of the hypersonic vehicle is equipped with the hypersonic vehicle nose cone described above.

[0048] Obviously, the above embodiments are only a part of the embodiments of the present invention, rather than all embodiments. The above embodiments are only used to explain the present invention and do not constitute a limitation on the protection scope of the present invention. Based on the above embodiments, all other embodiments obtained by those skilled in the art without creative work, that is, all modifications, equivalent replacements, and improvements made within the spirit and principle of this application, fall within the protection scope required by the present invention.

Claims

1. A hypersonic vehicle nose cone, characterized in that, It includes an outer shell (1), an inner shell (2) is arranged inside the outer shell (1). Both the outer shell (1) and the inner shell (2) are conical. The middle of the head end of the outer shell (1) is connected to the middle of the head end of the inner shell (2) through a connecting pipe (7). A jet hole is opened in the middle of the connecting pipe (7) and penetrates through the head end of the outer shell (1) and the head end of the inner shell (2). The tail end of the outer shell (1) is hermetically connected to the tail end of the inner shell (2) through an annular tail plate (9). A heat-dissipating outer cavity is formed between the outer shell (1), the inner shell (2), the connecting pipe (7) and the tail plate (9), and side ribs (8) are arranged radially. There are multiple side ribs (8) and they are evenly distributed along the circumferential direction of the outer shell (1). The side ribs (8) divide the heat-dissipating outer cavity into multiple sub-chambers. The inner wall of the sub-chamber is provided with a capillary structure layer, and an alkali metal working medium is filled in the sub-chamber. The outer shell (1), the inner shell (2), the connecting pipe (7), the side ribs (8) and the tail plate (9) are integrally formed. A rear end cover (3) is arranged on the inner side wall of the tail part of the inner shell (2). An impinging jet inner cavity is formed between the inner shell (2) and the rear end cover (3). An installation hole coaxial with the jet hole is opened in the middle of the rear end cover (3). A cooling pipe (4) is arranged in the installation hole. The outer diameter of the cooling pipe (4) is smaller than the inner diameter of the installation hole. The head end of the cooling pipe (4) is located inside the inner shell (2), and the tail end passes through the installation hole and extends out of the inner shell (2). The head end of the cooling pipe (4) is closed and provided with a hemispherical head (6). The outer diameter of the hemispherical head (6) is larger than the inner diameter of the jet hole. The part of the cooling pipe (4) located inside the inner shell (2) extends radially outward to form impinging jet pipes (5). There are more than four impinging jet pipes (5) and they are evenly distributed along the circumferential direction of the cooling pipe (4).

2. The hypersonic vehicle nose cone according to claim 1, characterized in that, There are four side ribs (8).

3. The hypersonic vehicle nose cone according to claim 1, characterized in that, The materials of the outer shell (1), the inner shell (2), the connecting pipe (7), the side ribs (8), the tail plate (9) and the rear end cover (3) are all superalloys.

4. The hypersonic vehicle nose cone according to claim 1, characterized in that, The material of the cooling pipe (4) is metal.

5. The hypersonic vehicle nose cone according to claim 1, characterized in that, It includes a temperature sensor, a driving transmission device, and a controller; the temperature sensor is arranged in one of the sub-chambers, the output end of the temperature sensor is connected to the input end of the controller, the driving transmission device is connected to the outer wall of the tail of the cooling pipe (4), the input end of the power element of the driving transmission device is electrically connected to the output end of the controller, the temperature sensor is used to measure the temperature inside the sub-chamber and transmit the measured temperature data to the controller, the controller is used to send a first control signal to the power element when the temperature is lower than a preset temperature threshold, and send a second control signal to the power element when the temperature is equal to or higher than the preset temperature threshold, and the driving transmission device is used to control the cooling pipe (4) to move towards the direction close to the jet hole when receiving the first control signal, and control the cooling pipe (4) to move away from the jet hole when receiving the second control signal.

6. A hypersonic vehicle, characterized in that, The front end of the hypersonic vehicle is equipped with the hypersonic vehicle nose cone according to any one of claims 1 to 5.

Images