Thermal protection structure of aircraft and aircraft

Abstract

The embodiment of the invention provides a thermal protection structure of an aircraft and the aircraft, and relates to the technical field of thermal protection structures of aircrafts, the thermal protection structure of the aircraft comprises a shell, a storage unit and a control assembly, the front end of the shell is provided with a first air nozzle, and the side wall of the rear end of the shell is internally provided with at least one cooling medium channel; each cooling medium channel is connected with a conveying mechanism for storing a cooling medium in the aircraft, the storage unit is arranged in an inner cavity of the shell and connected with the corresponding cooling medium channel, and the control assembly is connected with the storage unit and the first air jet opening and used for controlling the air jet opening when the temperature of the outer surface of the shell reaches the preset temperature. And the control storage unit is communicated with the first air nozzle. In the embodiment of the invention, the cooling medium is gasified and reversely jetted on the outer surface of the shell after heat exchange in the cooling medium channel to form a protective barrier, so that efficient thermal protection of the aircraft shell is realized, the thermal stress in a high-temperature environment is remarkably reduced, and the safety of an aircraft is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft thermal protection, and in particular to a thermal protection structure of an aircraft and the aircraft. Background Art

[0002] With the continuous advancement of aerospace technology, aircraft are developing towards higher speeds, longer ranges and more complex mission capabilities. However, during high-speed flight, the intense friction between the aircraft shell and the air will generate extremely high heat, causing the shell temperature to rise sharply. This aerodynamic heating phenomenon threatens the structural integrity and performance of the aircraft and reduces the safety of the aircraft.

[0003] In the existing technology, passive protective materials are generally used for thermal protection, such as multi-layer insulation materials and ceramic-based composite materials, which can slow down the transfer of heat to the interior of the aircraft to a certain extent. However, as the flight speed continues to increase, its thermal protection effect gradually shows limitations, especially at the leading edge of the aircraft. Due to the faster airflow speed and more intense friction, traditional passive protective materials often cannot withstand such a high heat load, and the safety of the aircraft is reduced. Summary of the invention

[0004] The embodiments of the present invention provide a thermal protection structure of an aircraft and an aircraft, so as to solve the technical problem in the related art that the aircraft adopts passive thermal protection materials, and the passive thermal protection materials have limited ability to withstand heat loads, thus affecting the safety of the aircraft.

[0005] In a first aspect, the present invention provides a thermal protection structure for an aircraft, the thermal protection structure for the aircraft comprising:

[0006] A shell, a first jet port is provided at the front end of the shell, at least one cooling medium channel is provided in the rear end side wall of the shell, and each cooling medium channel is connected to a conveying mechanism for storing cooling medium in the aircraft;

[0007] A storage unit, which is disposed in the inner cavity of the shell and connected to each of the cooling medium channels;

[0008] A control component is connected to the storage unit and the first air jet port, and is used to control the storage unit to be connected to the first air jet port when the temperature of the outer surface of the shell reaches a preset temperature.

[0009] In some embodiments, the storage unit includes:

[0010] At least one air inlet pipe, each of the air inlet pipes is connected to all of the cooling medium channels;

[0011] A gas storage cylinder is arranged in the inner cavity of the shell, and the gas storage cylinder is connected to each of the air inlet pipes.

[0012] In some embodiments, the housing further comprises:

[0013] A ventilation groove is arranged on the rear end side wall of the shell, and a plurality of cooling medium channels are arranged at intervals along the circumference of the shell, each of the cooling medium channels is connected to the cooling medium stored in the aircraft and the ventilation groove, and the ventilation groove is connected to the storage unit.

[0014] In some embodiments, the gas storage cylinder is a double-layer structure with an inner liner and an outer cylinder spaced apart.

[0015] In some embodiments, the outer cylinder is made of carbon fiber.

[0016] In some embodiments, the control component includes:

[0017] an air supply pipe connected to the storage unit;

[0018] A solenoid valve connected to the air supply pipe;

[0019] A controller, the controller being electrically connected to the solenoid valve;

[0020] A delivery pipe is connected to the solenoid valve and the first air injection port.

[0021] In some embodiments, the control component further includes:

[0022] A split air bag, the split air bag is arranged in the middle of the delivery pipe and is connected to the delivery pipe;

[0023] A plurality of jet tubes are arranged at intervals along the circumference of the sub-airbag, one end of each of the jet tubes is connected to the sub-airbag, a plurality of second jet ports are arranged on the shell around the first jet port, and the other end of each of the jet tubes is connected to a corresponding second jet port.

[0024] In some embodiments, the outer surface of the delivery tube is provided with glass wool.

[0025] In some embodiments, the outer surface of the front end of the shell is a smooth arc-shaped curved surface from front to back.

[0026] In a second aspect, the present invention further provides an aircraft, comprising the aforementioned thermal protection structure of the aircraft.

[0027] The beneficial effects brought about by the technical solution provided by the present invention include:

[0028] The embodiment of the present invention provides a thermal protection structure of an aircraft and an aircraft, wherein the thermal protection structure of the aircraft comprises a shell, a storage unit and a control component, wherein a first jet port is provided at the front end of the shell, at least one cooling medium channel is provided in the rear end side wall of the shell, each cooling medium channel is connected to a conveying mechanism storing cooling medium in the aircraft, a storage unit is provided in the inner cavity of the shell and connected to each cooling medium channel, a control component is connected to the storage unit and the first jet port, and the control component is used to control the storage unit to communicate with the first jet port when the temperature of the outer surface of the shell reaches a preset temperature. In the embodiment of the present invention, the cooling medium exchanges heat in the cooling medium channel, is stored in the storage unit after being vaporized, and when the outer surface of the front end of the shell reaches a preset temperature, the control component controls the storage unit to communicate with the first jet port, so that the gas in the storage unit is reversely sprayed on the outer surface of the shell through the first jet port and forms a protective barrier, thereby realizing efficient thermal protection of the shell of the aircraft, significantly reducing thermal stress in a high temperature environment, and improving the safety of the aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following briefly introduces the drawings required for use in the description of the embodiments. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0030] Figure 1 A schematic diagram of a first cross-sectional structure of a thermal protection structure of an aircraft provided by an embodiment of the present invention;

[0031] Figure 2 A schematic diagram of the three-dimensional structure of a thermal protection structure of an aircraft provided by an embodiment of the present invention;

[0032] Figure 3 A second cross-sectional structural schematic diagram of a thermal protection structure of an aircraft provided by an embodiment of the present invention;

[0033] Figure 4 An AA cross-sectional view of a thermal protection structure of an aircraft provided by an embodiment of the present invention;

[0034] Figure 5 A BB cross-sectional view of a thermal protection structure of an aircraft provided by an embodiment of the present invention;

[0035] Reference numerals:

[0036] 1. Shell; 11. First jet port; 12. Cooling medium channel; 13. Second jet port; 14. Ventilation groove;

[0037] 2. Storage unit; 21. Air intake pipe; 22. Gas storage cylinder;

[0038] 3. Control component; 31. Air supply pipe; 32. Solenoid valve; 33. Delivery pipe; 34. Air bag; 35. Jet pipe. DETAILED DESCRIPTION

[0039] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0040] The embodiments of the present invention provide a thermal protection structure of an aircraft and an aircraft, which can solve the technical problem in the related art that the aircraft uses passive thermal protection materials, and the passive thermal protection materials have limited ability to withstand heat loads, which affects the safety of the aircraft.

[0041] See also Figure 1 As shown, an embodiment of the present invention provides a thermal protection structure of an aircraft, the thermal protection structure of the aircraft includes a shell 1, a storage unit 2 and a control component 3, the shell 1 is provided with a first jet port 11 at the front end, at least one cooling medium channel 12 is provided in the rear end side wall of the shell 1, each of the cooling medium channels 12 is connected to a conveying mechanism for storing cooling medium in the aircraft, the storage unit 2 is provided in the inner cavity of the shell 1 and is connected to each of the cooling medium channels 12, the control component 3 is connected to the storage unit 2 and the first jet port 11, the control component 3 calculates the outer surface temperature of the shell 1 according to the flight speed and altitude of the aircraft, and when the outer surface temperature of the shell 1 reaches a preset temperature, the control component 3 controls the storage unit 2 to be connected to the first jet port 11. In an embodiment of the present invention, the cooling medium exchanges heat in the cooling medium channel 12 and is stored in the storage unit 2 after being vaporized. When the outer surface of the front end of the shell 1 reaches a preset temperature, the control component 3 controls the storage unit 2 to be connected with the first jet port 11, so that the gas in the storage unit 2 is reversely sprayed onto the outer surface of the shell 1 through the first jet port 11 and forms a protective barrier, thereby achieving efficient thermal protection of the aircraft shell, significantly reducing thermal stress in a high temperature environment, and improving the safety of the aircraft.

[0042] In an embodiment of the present invention, a thermal protection structure of an aircraft is provided, the thermal protection structure comprises a shell, a storage unit and a control component, the front end of the shell is provided with a first jet port, the rear end side wall of the shell is provided with at least one cooling medium channel, each of the cooling medium channels is connected to a conveying mechanism storing cooling medium in the aircraft, the storage unit is provided in the inner cavity of the shell and connected to each of the cooling medium channels, the control component is connected to the storage unit and the first jet port, and the control component is used to control the storage unit to communicate with the first jet port when the temperature of the outer surface of the shell reaches a preset temperature. In an embodiment of the present invention, the cooling medium exchanges heat in the cooling medium channel, is vaporized and stored in the storage unit, and when the outer surface of the front end of the shell reaches a preset temperature, the control component controls the storage unit to communicate with the first jet port, so that the gas in the storage unit is reversely sprayed on the outer surface of the shell through the first jet port and forms a protective barrier, thereby realizing efficient thermal protection of the aircraft shell, significantly reducing thermal stress in a high temperature environment, and improving the safety of the aircraft.

[0043] As an optional implementation, in an embodiment of the invention, see Figure 1 As shown, the storage unit 2 is provided with at least one air inlet pipe 21 and a gas cylinder 22, each of the air inlet pipes 21 is connected to all of the cooling medium channels 12, the gas cylinder 22 is arranged in the inner cavity of the housing 1, and the gas cylinder 22 is connected to each of the air inlet pipes 21. In the embodiment of the present invention, each of the air inlet pipes 21 is fixedly connected to the gas cylinder 22, and the cooling medium is collected into at least one of the air inlet pipes 21 after being gasified, and finally enters the interior of the gas cylinder 22 through the air inlet pipe 21 for subsequent use. The storage unit has a simple structure, which ensures the stability of the transportation and storage of the cooling medium after gasification.

[0044] As an optional implementation, in an embodiment of the invention, see Figure 3 and Figure 4 As shown, the shell 1 is further provided with a ventilation groove 14, which is provided on the rear end side wall of the shell 1, and a plurality of cooling medium channels 12 are arranged at intervals along the circumference of the shell 1, and each cooling medium channel 12 is connected to the cooling medium stored in the aircraft and the ventilation groove 14, and the ventilation groove 14 is connected to the storage unit 2. In the embodiment of the present invention, each cooling medium channel 12 is connected through the annular ventilation groove 14, and the gasified cooling medium enters the air intake pipe 21 at the rear end through the ventilation groove 14, and the ventilation groove improves the stability and efficiency of gas transportation.

[0045] As an optional implementation, in one embodiment of the invention, the gas storage cylinder 22 is a double-layer structure with an inner liner and an outer cylinder arranged at intervals. The inner liner is made of low-temperature resistant alloy steel to ensure the low temperature of the gas and withstand the pressure and low temperature of the cooling medium. The outer cylinder is a protective layer of the inner liner. A certain distance is maintained between the outer cylinder and the inner liner to form an insulating space to keep the gasified cooling medium inside warm, which is conducive to the storage of the gasified cooling medium.

[0046] As an optional implementation, in one embodiment of the invention, the outer cylinder is made of carbon fiber. The outer cylinder made by winding carbon fiber is light in weight and has good thermal insulation performance, which is conducive to preserving the gasified cooling medium.

[0047] As an optional implementation, in an embodiment of the invention, see Figure 1 As shown, the control component 3 is provided with an air supply pipe 31, a solenoid valve 32, a controller and a delivery pipe 33, the air supply pipe 31 is connected to the storage unit 2, the solenoid valve 32 is connected to the air supply pipe 31, the controller is electrically connected to the solenoid valve 32, and the delivery pipe 33 is connected to the solenoid valve 32 and the first jet port 11. In the embodiment of the present invention, the outlet end of the gas storage bottle 22 is fixedly connected with the gas delivery pipe 31, the gas delivery end of the gas delivery pipe 31 is connected with the gas inlet end of the electromagnetic valve 32, the exhaust end of the electromagnetic valve 32 is fixedly connected with the delivery pipe 33, the delivery pipe 33 is connected with the first jet port 11, and the controller is electrically connected with the electromagnetic valve 32, and the temperature of the outer surface of the shell 1 is converted according to the flight speed and altitude of the aircraft. When the outer surface of the shell 1 of the aircraft reaches a preset temperature, the controller controls the electromagnetic valve 32 to continuously extract the gas inside the gas storage bottle 22, so that the gas is sprayed to the first jet port 11 through the delivery pipe 33, and the delivery efficiency of the electromagnetic valve 32 is controlled within a certain efficiency limit to avoid the temperature rise caused by the excessive gas flow rate, thereby affecting the protection effect on the outer surface of the shell 1 of the aircraft. The control component pressurizes and sprays the gas to ensure the working stability of the thermal protection structure.

[0048] As an optional implementation, in an embodiment of the invention, see Figure 3 and Figure 5As shown, the control component 3 is further provided with a sub-airbag 34 and a plurality of jet tubes 35. The sub-airbag 34 is provided in the middle of the delivery tube 33 and is connected to the delivery tube 33. The plurality of jet tubes 35 are arranged at intervals along the circumference of the sub-airbag 34. One end of each jet tube 35 is connected to the sub-airbag 34. The shell 1 is provided with a plurality of second jet ports 13 around the first jet port 11. The other end of each jet tube 35 is connected to a corresponding second jet port 13. The control component 3 in the embodiment of the present invention is further provided with the sub-airbag 34 and the plurality of jet tubes 35, which improves the cooling effect of the thermal protection structure.

[0049] As an optional implementation, in one embodiment of the invention, the outer surface of the delivery pipe 33 is provided with glass wool to keep the gas warm during the delivery process. The delivery pipe 33 is wrapped with glass wool to prevent the external environment from affecting the gas inside the delivery pipe 33, thereby ensuring the working stability of the thermal protection structure.

[0050] As an optional implementation, in an embodiment of the invention, see Figure 1 As shown, the outer surface of the front end of the shell 1 is a smooth arc-shaped curved surface from front to back, which is used to guide the exhausted cooling medium gas when the aircraft is flying. When the gas is sprayed, the arc-shaped curved surface can ensure that the cooling medium gas is in full contact with the shell 1 of the aircraft, forming a protective barrier to prevent the shell 1 of the aircraft from heating up too quickly due to friction with the air.

[0051] An embodiment of the present invention further provides an aircraft, comprising the aforementioned thermal protection structure of an aircraft, wherein the thermal protection structure of the aircraft comprises a shell 1, a storage unit 2 and a control component 3, wherein a first jet port 11 is provided at the front end of the shell 1, and at least one cooling medium channel 12 is provided in the rear end side wall of the shell 1, each of the cooling medium channels 12 is connected to a conveying mechanism for storing cooling medium in the aircraft, the storage unit 2 is provided in the inner cavity of the shell 1 and is connected to each of the cooling medium channels 12, the control component 3 is connected to the storage unit 2 and the first jet port 11, and the control component 3 is used to control the storage unit 2 to be connected to the first jet port 11 when the outer surface temperature of the shell 1 reaches a preset temperature. In an embodiment of the present invention, the cooling medium exchanges heat in the cooling medium channel 12 and is stored in the storage unit 2 after being vaporized. When the outer surface of the front end of the shell 1 reaches a preset temperature, the control component 3 controls the storage unit 2 to be connected with the first jet port 11, so that the gas in the storage unit 2 is reversely sprayed onto the outer surface of the shell 1 through the first jet port 11 and forms a protective barrier, thereby achieving efficient thermal protection of the aircraft shell, significantly reducing thermal stress in a high temperature environment, and improving the safety of the aircraft.

[0052] As an optional implementation, in an embodiment of the invention, see Figure 1 As shown, the storage unit 2 is provided with at least one air inlet pipe 21 and a gas cylinder 22, each of the air inlet pipes 21 is connected to all of the cooling medium channels 12, the gas cylinder 22 is arranged in the inner cavity of the housing 1, and the gas cylinder 22 is connected to each of the air inlet pipes 21. In the embodiment of the present invention, each of the air inlet pipes 21 is fixedly connected to the gas cylinder 22, and the cooling medium is collected into at least one of the air inlet pipes 21 after being gasified, and finally enters the interior of the gas cylinder 22 through the air inlet pipe 21 for subsequent use. The storage unit has a simple structure, which ensures the stability of the transportation and storage of the cooling medium after gasification.

[0053] As an optional implementation, in an embodiment of the invention, see Figure 3 and Figure 4 As shown, the shell 1 is further provided with a ventilation groove 14, which is provided on the rear end side wall of the shell 1, and a plurality of cooling medium channels 12 are arranged at intervals along the circumference of the shell 1, and each cooling medium channel 12 is connected to the cooling medium stored in the aircraft and the ventilation groove 14, and the ventilation groove 14 is connected to the storage unit 2. In the embodiment of the present invention, each cooling medium channel 12 is connected through the annular ventilation groove 14, and the gasified cooling medium enters the air intake pipe 21 at the rear end through the ventilation groove 14, and the ventilation groove improves the stability and efficiency of gas transportation.

[0054] As an optional implementation, in one embodiment of the invention, the gas storage cylinder 22 is a double-layer structure with an inner liner and an outer cylinder arranged at intervals. The inner liner is made of low-temperature resistant alloy steel to ensure the low temperature of the gas and withstand the pressure and low temperature of the cooling medium. The outer cylinder is a protective layer of the inner liner. A certain distance is maintained between the outer cylinder and the inner liner to form an insulating space to keep the gasified cooling medium inside warm, which is conducive to the storage of the gasified cooling medium.

[0055] As an optional implementation, in one embodiment of the invention, the outer cylinder is made of carbon fiber. The outer cylinder made by winding carbon fiber is light in weight and has good thermal insulation performance, which is conducive to preserving the gasified cooling medium.

[0056] As an optional implementation, in an embodiment of the invention, see Figure 1As shown, the control component 3 is provided with an air supply pipe 31, a solenoid valve 32, a controller and a delivery pipe 33, the air supply pipe 31 is connected to the storage unit 2, the solenoid valve 32 is connected to the air supply pipe 31, the controller is electrically connected to the solenoid valve 32, and the delivery pipe 33 is connected to the solenoid valve 32 and the first jet port 11. In the embodiment of the present invention, the gas outlet end of the gas storage bottle 22 is fixedly connected with the gas delivery pipe 31, the gas delivery end of the gas delivery pipe 31 is connected with the gas inlet end of the electromagnetic valve 32, the exhaust end of the electromagnetic valve 32 is fixedly connected with the delivery pipe 33, the delivery pipe 33 is connected with the first jet port 11, and the controller is electrically connected with the electromagnetic valve 32. When the outer surface of the shell 1 of the aircraft reaches a preset temperature, the controller controls the electromagnetic valve 32 to continuously extract the gas inside the gas storage bottle 22, so that the gas is sprayed to the first jet port 11 through the delivery pipe 33, and the delivery efficiency of the electromagnetic valve 32 is controlled within a certain efficiency limit to avoid the temperature rise caused by the excessive gas flow rate, thereby affecting the protection effect on the outer surface of the shell 1 of the aircraft. The control component pressurizes and sprays the gas to ensure the working stability of the aircraft.

[0057] In the description of the present invention, it should be noted that the terms "upper", "lower", etc. indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific position, be constructed and operated in a specific position, and therefore cannot be understood as a limitation on the present invention. Unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be an indirect connection through an intermediate medium, or it can be a connection between the two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to the specific circumstances.

[0058] It should be noted that, in the present invention, relational terms such as "first" and "second" are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device. In the absence of further restrictions, the elements defined by the sentence "comprise a ..." do not exclude the existence of other identical elements in the process, method, article or device including the elements.

[0059] The above description is only a specific embodiment of the present invention, so that those skilled in the art can understand or implement the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but should conform to the widest scope consistent with the principles and novel features of the present invention.

Claims

1. A thermal protection structure for an aircraft, characterized in that: include: A shell (1) having a first jet port (11) at its front end, and at least one cooling medium channel (12) arranged in a rear end side wall of the shell (1), each cooling medium channel (12) being connected to a conveying mechanism for storing cooling medium in the aircraft; A storage unit (2), which is arranged in the inner cavity of the shell (1) and connected to each of the cooling medium channels (12); A control component (3) is connected to the storage unit (2) and the first air jet port (11), and the control component (3) is used to control the storage unit (2) to be connected to the first air jet port (11) when the temperature of the outer surface of the shell (1) reaches a preset temperature.

2. The thermal protection structure of an aircraft according to claim 1, characterized in that: The storage unit (2) comprises: at least one air intake pipe (21), each of the air intake pipes (21) being connected to all of the cooling medium channels (12); A gas storage bottle (22), the gas storage bottle (22) is arranged in the inner cavity of the shell (1), and the gas storage bottle (22) is connected to each of the air inlet pipes (21).

3. The thermal protection structure of an aircraft according to claim 2, characterized in that: The housing (1) further comprises: A ventilation groove (14) is provided on the rear end side wall of the shell (1), a plurality of cooling medium channels (12) are arranged at intervals along the circumference of the shell (1), each cooling medium channel (12) is connected to the cooling medium stored in the aircraft and the ventilation groove (14), and the ventilation groove (14) is connected to the storage unit (2).

4. The thermal protection structure of an aircraft according to claim 2, characterized in that: The gas storage cylinder (22) is a double-layer structure with an inner liner and an outer cylinder arranged at intervals.

5. The thermal protection structure of an aircraft according to claim 4, characterized in that: The outer cylinder is made of carbon fiber.

6. The thermal protection structure of an aircraft according to claim 1, characterized in that: The control component (3) comprises: an air supply pipe (31), the air supply pipe (31) being connected to the storage unit (2); A solenoid valve (32), the solenoid valve (32) being connected to the air supply pipe (31); A controller, the controller being electrically connected to the solenoid valve (32); A delivery pipe (33), wherein the delivery pipe (33) is connected to the solenoid valve (32) and the first air jet port (11).

7. The thermal protection structure of an aircraft according to claim 6, characterized in that: The control component (3) further comprises: A split air bag (34), the split air bag (34) is arranged in the middle of the delivery pipe (33) and is in communication with the delivery pipe (33); A plurality of jet tubes (35) are arranged at intervals along the circumference of the sub-airbag (34), one end of each of the jet tubes (35) is connected to the sub-airbag (34), a plurality of second jet ports (13) are arranged on the shell (1) around the first jet port (11), and the other end of each of the jet tubes (35) is connected to a corresponding one of the second jet ports (13).

8. The thermal protection structure of an aircraft according to claim 6, characterized in that: The outer surface of the delivery pipe (33) is provided with glass wool.

9. The thermal protection structure of an aircraft according to claim 1, characterized in that: The outer surface of the front end of the shell (1) is a smooth arc-shaped curved surface from front to back.

10. An aircraft, characterized in that: A thermal protection structure for an aircraft comprising any one of claims 1-9.

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