A reentry vehicle air-breathing ejector-type thermal protection device and its control method

Abstract

This application provides a reentry vehicle air-breathing ejector-type thermal protection device and its control method. The thermal protection device includes: a payload compartment; a protective component disposed at the front end of the payload compartment, the front end of the protective component forming the nose of the vehicle, and the rear end of the protective component forming the shoulder of the vehicle, wherein the nose is provided with a nose air intake and the shoulder is provided with a shoulder ejection port; a guiding assembly, the nose air intake being connected to the shoulder ejection port through the guiding assembly, for guiding the incoming air absorbed by the nose air intake to the shoulder ejection port for ejection, thereby forming thermal protection on the shoulder. This application embodiment does not require carrying additional working fluid, relying on the nose to absorb incoming air and guide it to the shoulder for thermal protection of the vehicle's shoulder, while also solving the problem of nose burns.

Description

Technical Field

[0001] This application relates to the field of aircraft technology, and more specifically, to a reentry vehicle air-breathing ejector thermal protection device and its control method. Background Technology

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

[0003] In recent years, many scholars both domestically and internationally have proposed various methods for drag reduction and heat protection, such as: reverse jetting, adding drag-reducing rods, adding pneumatic discs, windward concave cavities, energy deposition, and many combinations thereof. For example, related technologies employ drag-reducing rods combined with pneumatic discs for drag reduction and heat protection.

[0004] Existing methods of thermal protection have many problems. If jet heat protection is used, the working fluid will occupy a large space inside the aircraft. If additional devices are installed, the exposed outer end of the aircraft will suffer severe ablation and will affect the shape and center of gravity of the reentry vehicle. Summary of the Invention

[0005] The purpose of this application is to provide a reentry vehicle air-breathing ejector thermal protection device and its control method, so as to solve the problem that the working fluid carried in the prior art occupies a large space inside the vehicle and has poor protection effect.

[0006] This application provides a reentry vehicle air-breathing ejector-type thermal protection device, comprising: a payload compartment; a protective member disposed at the front end of the payload compartment, the front end of the protective member constituting the head of the vehicle, and the rear end of the protective member constituting the shoulder of the vehicle, wherein the head is provided with a head air intake and the shoulder is provided with a shoulder ejector; and a guiding assembly, wherein the head air intake is connected to the shoulder ejector through the guiding assembly, for guiding the incoming air absorbed by the head air intake to the shoulder ejector for ejection, thereby forming thermal protection on the shoulder.

[0007] In this embodiment, a head air intake and a shoulder jet are respectively provided on the head and shoulder of the aircraft. The head air intake and the shoulder jet are connected by a guide assembly. The head air intake is used to absorb incoming air, and the incoming air is ejected from the shoulder jet through the guide assembly to form thermal protection for the shoulder of the aircraft. There is no need to carry additional working fluid, which reduces the space occupied by the aircraft. At the same time, the problem of head burn is avoided because the aircraft head absorbs the incoming air.

[0008] In some embodiments, a plurality of shoulder jet holes are provided, the plurality of shoulder jet holes are distributed along the circumference of the shoulder, and the plurality of shoulder jet holes are interconnected.

[0009] In this embodiment, the incoming air absorbed by the head air intake is guided to the shoulder jet holes by the guide component. Since the multiple shoulder jet holes are interconnected, the gas guided by the guide component can be ejected from the multiple shoulder jet holes, making the gas distribution at each shoulder jet hole more uniform, thereby forming all-round thermal protection for the shoulder of the aircraft.

[0010] In some embodiments, an annular connecting channel is provided within the shoulder portion, and a plurality of shoulder jet holes are connected through the annular connecting channel.

[0011] Optionally, multiple head air intake holes and multiple guide components are provided, with each guide component corresponding to one of the multiple head air intake holes, wherein the multiple guide components are connected to some of the shoulder jet holes.

[0012] In this embodiment, since multiple shoulder jet holes are connected by an annular connecting channel, the number of guiding components does not need to correspond to the number of shoulder jet holes. All shoulder jet holes can be provided with jet thermal protection by using fewer guiding components than the number of shoulder jet holes, thus providing comprehensive thermal protection for the shoulder of the aircraft while minimizing the space occupied by the guiding components.

[0013] Optionally, the shoulder jet orifice includes a plurality of first shoulder jet orifices and a plurality of second shoulder jet orifices connected through the annular connecting channel. The plurality of first shoulder jet orifices correspond one-to-one with the plurality of guide components, and each guide component is connected to the corresponding head air intake orifice and the corresponding first shoulder jet orifice.

[0014] Optionally, a plurality of the first shoulder jet holes are arranged at equal intervals in the circumference of the shoulder.

[0015] In some embodiments, the guiding component includes a connecting pipe disposed within the protective member and a control valve disposed on the connecting pipe, wherein the head air intake is connected to the first shoulder jet hole through the connecting pipe.

[0016] Optionally, both ends of the control valve are connected to the connecting pipe via adapters, the front end of the connecting pipe is connected to the head air intake port, and the rear end of the connecting pipe is connected to the first shoulder jet port.

[0017] This application also provides a control method for a reentry vehicle air-intake ejector-type thermal protection device, applied to the thermal protection device described in any of the above embodiments. The method includes: during the flight of the vehicle, in response to a shoulder thermal protection command, controlling the control valve of the guiding component to connect the head air intake port and the shoulder ejector port, so that the incoming air absorbed by the head air intake port is guided to the shoulder ejector port through the guiding component, thereby forming thermal protection on the shoulder.

[0018] In some embodiments, the method further includes: during the flight of the aircraft, when the aircraft has an angle of attack, controlling a control valve corresponding to the shoulder jet orifice facing the direction of incoming flow, so that the shoulder jet orifice facing the direction of incoming flow forms thermal protection. Attached Figure Description

[0019] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments of this application will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 A perspective view of a reentry vehicle air-breathing ejector-type thermal protection device provided in this application embodiment;

[0021] Figure 2 A cross-sectional view of a reentry vehicle air-breathing ejector-type thermal protection device provided in this application embodiment;

[0022] Figure 3 A partial cross-sectional view of an air-breathing ejector-type thermal protection device for a reentry vehicle provided in this application embodiment;

[0023] Figure 4 A partial cross-sectional view of the shoulder of a reentry vehicle air-breathing ejector-type thermal protection device provided in this application embodiment;

[0024] Figure 5 Another partial cross-sectional view of a reentry vehicle air-breathing ejector-type thermal protection device provided in an embodiment of this application;

[0025] Figure 6 A flowchart illustrating a control method for a reentry vehicle air-breathing ejector-type thermal protection device provided in this application embodiment;

[0026] Figure 7 This is a schematic diagram illustrating the working process of a reentry vehicle air-breathing ejector-type thermal protection device provided in an embodiment of this application. Detailed Implementation

[0027] The technical solutions in the embodiments of this application will now be described with reference to the accompanying drawings.

[0028] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, in the description of this application, terms such as "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0029] This application provides a reentry vehicle air-breathing ejector-type thermal protection device. This device does not require carrying additional working fluid. It relies on absorbing and guiding incoming air to the shoulder to provide thermal protection for the shoulder of the aircraft, while also solving the problem of head burns.

[0030] Reference Figure 1 and Figure 2 , Figure 1 A perspective view of a reentry vehicle air-breathing ejector-type thermal protection device provided in this application embodiment; Figure 2 This is a cross-sectional view of a reentry vehicle air-breathing ejector-type thermal protection device provided in an embodiment of this application.

[0031] This application provides a reentry vehicle air-breathing ejector-type thermal protection device, including: a payload compartment 10, a protective component 20, and a guidance assembly 30.

[0032] The interior of the load chamber 10 is used to provide loads, and the load chamber 10 may be cylindrical, for example.

[0033] A protective component 20 is disposed at the front end of the payload compartment 10. The front end of the protective component 20 forms the nose 201 of the aircraft, and the tail end of the protective component 20 forms the shoulder 202 of the aircraft. The nose 201 is provided with one or more nose air intakes 21, and the shoulder 202 is provided with one or more shoulder jet holes 22. The protective component 20 can be umbrella-shaped to provide thermal protection for the nose of the aircraft during flight. For example, the multiple shoulder jet holes 22 can be evenly distributed along the circumference of the protective component 20.

[0034] The guide assembly 30 is optionally connected to the head air intake 21 and the shoulder jet 22, and is used to guide the incoming air absorbed by the head air intake 21 to the shoulder jet 22 to form thermal protection on the shoulder 202 of the aircraft. "Optional connection" means that the guide assembly 30 can open or close the communication channel between the head air intake 21 and the shoulder jet 22. In one example, when head thermal protection is required, the communication channel between the head air intake 21 can be opened via the guide assembly 30, and the incoming air absorbed from the head air intake 21 can be ejected from the shoulder jet 22 through the guide assembly 30 to form thermal protection on the shoulder of the aircraft.

[0035] The reentry vehicle air-intake ejector thermal protection device of this application embodiment provides a head air intake port 21 and a shoulder jet port 22 on the head and shoulder of the vehicle, respectively. The head air intake port 21 and the shoulder jet port 22 are connected by a guide component 30. The head air intake port 21 is used to absorb incoming air, and the incoming air is ejected from the shoulder jet port 22 through the guide component 30 to form thermal protection for the shoulder of the vehicle. There is no need to carry additional working fluid, reducing the space occupied by the vehicle. At the same time, the problem of head burn is avoided because the head of the vehicle absorbs the incoming air.

[0036] In some embodiments, a plurality of shoulder jet holes 22 are provided, the plurality of shoulder jet holes 22 are distributed along the circumference of the shoulder 202, and the plurality of shoulder jet holes 22 are interconnected.

[0037] The incoming air intake 21 is guided by the guide assembly 30 to the shoulder jet 202. Since the multiple shoulder jet 22 are interconnected, the gas guided by the guide assembly 30 can be ejected from the multiple shoulder jet 22, making the gas distribution at each shoulder jet 22 more uniform, thereby forming all-round thermal protection for the aircraft shoulder 202.

[0038] In one example, refer to Figure 4 , Figure 5 , Figure 4 A partial cross-sectional view of the shoulder of a reentry vehicle air-breathing ejector-type thermal protection device provided in this application embodiment; Figure 5 This is a partial cross-sectional view from another perspective of a reentry vehicle air-breathing ejector-type thermal protection device provided in an embodiment of this application.

[0039] An annular connecting channel 34 is provided inside the shoulder section 202 of the aircraft, and multiple shoulder jet holes 22 are connected through the annular connecting channel 34. A hollow annular connecting channel 34 is formed at the tail position of the protective component 20 to connect multiple shoulder jet holes 22.

[0040] Optionally, multiple head air intakes 21 and guide components 30 are provided, with each guide component 30 corresponding one-to-one with a specific head air intake 21. These guide components 30 are also connected to some of the shoulder jet holes 22. Since the multiple shoulder jet holes 22 are connected via an annular connecting channel 34, the number of guide components 30 does not need to correspond to the number of shoulder jet holes 22. A smaller number of guide components 30 can achieve jet thermal protection for all shoulder jet holes 22, providing comprehensive thermal protection for the aircraft's shoulders while minimizing the space occupied by the guide components 30.

[0041] In one example, refer to Figure 5 The shoulder jet orifice 22 includes a plurality of first shoulder jet orifices 221 and a plurality of second shoulder jet orifices 222 connected by an annular connecting channel 23. The plurality of first shoulder jet orifices 221 correspond one-to-one with the plurality of the guide components 30, and each guide component 30 is connected to the corresponding head air intake orifice 21 and the corresponding first shoulder jet orifice 221.

[0042] For example, four head air intakes 21 can be provided, and four corresponding guide components 30 can also be provided. Sixteen shoulder jet holes 22 can be provided, including four first shoulder jet holes 22 and twelve second shoulder jet holes 22. The four head air intakes 21 are connected to the corresponding four first shoulder jet holes 221 through the four guide components 30, and the other twelve second shoulder jet holes 22 are connected to the four first shoulder jet holes 22 through an annular connecting channel 23. The four first shoulder jet holes 22 can be arranged at equal intervals around the shoulder of the aircraft.

[0043] In one example, refer to Figure 3 , Figure 3 This is a partial cross-sectional view of a reentry vehicle air-breathing ejector-type thermal protection device provided in an embodiment of this application.

[0044] The guiding assembly 30 includes a connecting pipe 31 disposed within the protective component 20 and a control valve 32 disposed on the connecting pipe 31. The head intake port 21 is connected to the first shoulder jet port 221 via the connecting pipe 31. Both ends of the control valve 32 are connected to the connecting pipe 31 via adapters 33. The front end of the connecting pipe 31 is connected to the head intake port 21, and the rear end is connected to the first shoulder jet port 221. The adapters 33 collect and buffer gas inflow and outflow. The control valve 32 can be, for example, a DN4 direct-acting solenoid valve, which controls the opening and closing of the circuit via a signal. Both ends of the control valve 32 are threaded to the adapters, and the solenoid valve can be opened and closed multiple times.

[0045] For example, solenoid valves, such as solenoid valve A1, solenoid valve A2, solenoid valve A3, and solenoid valve A4, are installed on four connecting pipes 31.

[0046] In summary, in the preferred embodiment of this application, reference is made to... Figure 7 , Figure 7 This is a schematic diagram illustrating the working process of an air-breathing ejector-type thermal protection device for a reentry vehicle, provided as an embodiment of this application. The working process of the vehicle is as follows:

[0047] ① Initial flight phase: During the initial flight phase, solenoid valves A1-A4 are closed. At the start of flight, since the air intake port at the head of the aircraft shell is always open, gas is absorbed at this time. The gas is blocked in front of the solenoid valve, i.e., in the adapter and connecting pipe.

[0048] ② Full Jet Stage: When the sensor indicates that the heat flux density on the shoulder of the aircraft is high and / or reaches the specified altitude and / or specified speed, the solenoid valve is opened. At this time, the incoming air absorbed by the nose air intake will be ejected from the shoulder jet hole through the solenoid valve via the adapter and connecting pipe. Part of the jet is ejected from the first shoulder jet hole directly connected to the connecting pipe, and part of the jet is ejected through the connecting channel inside the aircraft protective shell through the second shoulder jet hole which is not directly connected to the connecting pipe, so as to achieve more comprehensive jet thermal protection.

[0049] ③ Jet Flow Adjustment Stage Based on Angle of Attack: During flight, if there is an angle of attack, the heat flux density distribution on the aircraft surface will be uneven, with a higher heat flux density on the shoulder facing the incoming flow direction, requiring more direct thermal protection. In this case, only some solenoid valves facing the incoming flow direction can be opened for air intake and thermal protection, while the other solenoid valves remain closed. For example, when the angle of attack is positive, solenoid valves A1 and A2 can be opened; when the angle of attack is negative, solenoid valves A3 and A4 can be opened.

[0050] ④ Flight End Phase: When the flight ends, close the solenoid valve to block the intake and jet process.

[0051] The air-breathing ejector-type thermal protection device for reentry vehicles according to the embodiments of this application has the following advantages: it eliminates the need to carry excess gaseous working fluid, simplifying the structure and reducing added mass, making it easier to carry more effective payload; compared with drag reduction methods such as drag-reducing rods and pneumatic discs, its thermal protection method is more stable and controllable, eliminating the need to consider ablation and changes to the shape and center of gravity of the vehicle, allowing for reusability, high safety, and better thermal protection; the jet can be started and stopped by switching on and off using a solenoid valve, facilitating reasonable control based on the environment in which the vehicle is located; by inhaling air from the head to the shoulder jet, it more conveniently solves the problem of concentrated heat flux density in the shoulder, and can directly adjust for uneven heat flux density distribution during angle-of-attack flight, resulting in high controllability.

[0052] This application also provides a control method for a reentry vehicle air-breathing ejector-type thermal protection device, applied to the thermal protection device mentioned above, with reference to... Figure 6 and Figure 7 The method includes step S11.

[0053] In step S11, during the flight of the aircraft, in response to the aircraft shoulder thermal protection command, the control valve of the control guide assembly connects the head air intake port and the shoulder jet port, so that the incoming air absorbed by the head air intake port is guided to the shoulder jet port through the guide assembly to form thermal protection on the shoulder.

[0054] The aircraft shoulder thermal protection command can be triggered when the sensor detects a high heat flux density (above a set value) on the aircraft shoulder and / or when it reaches a specified altitude and / or speed.

[0055] The method further includes: during the flight of the aircraft, when the aircraft has an angle of attack, controlling the control valve corresponding to the shoulder jet hole facing the direction of the incoming flow, so that the shoulder jet hole facing the direction of the incoming flow forms thermal protection.

[0056] Reference Figure 7 If an aircraft has an angle of attack during flight, the heat flux density distribution on the aircraft surface will be uneven, with a higher heat flux density on the shoulder facing the incoming flow direction, requiring more direct thermal protection. In this case, only the solenoid valves facing the incoming flow direction can be opened for air intake and thermal protection, while the other solenoid valves remain closed.

[0057] In the several embodiments provided in this application, it should be understood that the disclosed apparatus and methods can also be implemented in other ways. The apparatus embodiments described above are merely illustrative. For example, the flowcharts and block diagrams in the accompanying drawings illustrate the architecture, functionality, and operation of possible implementations of apparatus, methods, and computer program products according to various embodiments of this application. In this regard, each block in a flowchart or block diagram may represent a module, segment, or portion of code containing one or more executable instructions for implementing a specified logical function. It should also be noted that in some alternative implementations, the functions marked in the blocks may occur in a different order than those marked in the drawings. For example, two consecutive blocks may actually be executed substantially in parallel, and they may sometimes be executed in reverse order, depending on the functions involved. It should also be noted that each block in a block diagram and / or flowchart, and combinations of blocks in block diagrams and / or flowcharts, can be implemented using a dedicated hardware-based system that performs the specified function or action, or using a combination of dedicated hardware and computer instructions.

[0058] In addition, the functional modules in the various embodiments of this application can be integrated together to form an independent part, or each module can exist independently, or two or more modules can be integrated to form an independent part.

[0059] If the aforementioned functions are implemented as software functional modules and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or a portion of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this application. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, or optical disks.

[0060] The above description is merely an embodiment of this application and is not intended to limit the scope of protection of this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this application should be included within the scope of protection of this application. It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0061] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the rights protection as described above.

[0062] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

Claims

1. A reentry vehicle air-breathing ejector-type thermal protection device, characterized in that, include: Payload compartment; A protective component is disposed at the front end of the payload compartment. The front end of the protective component constitutes the head of the aircraft, and the tail end of the protective component constitutes the shoulder of the aircraft. The head is provided with a head air intake, and the shoulder is provided with a shoulder jet hole. The guide assembly connects the head air intake to the shoulder jet hole, and guides the incoming air absorbed by the head air intake to the shoulder jet hole for ejection, so as to form thermal protection on the shoulder. The shoulder jet holes are provided in a plurality of manner, and the plurality of shoulder jet holes are distributed along the circumference of the shoulder and are interconnected with each other. The protective component is provided with an annular connecting channel, and the multiple shoulder jet holes are interconnected through the annular connecting channel. Multiple head air intake holes and multiple guide components are provided, with each guide component corresponding to one of the multiple head air intake holes. The multiple guide components are connected to some of the shoulder jet holes. The shoulder jet orifice includes a plurality of first shoulder jet orifices and a plurality of second shoulder jet orifices connected through the annular connecting channel. The plurality of first shoulder jet orifices correspond one-to-one with the plurality of guide components, and each guide component is connected to the corresponding head inhalation port and the corresponding first shoulder jet orifice. The guiding component includes a connecting pipe disposed within the protective component and a control valve disposed on the connecting pipe, and the head air intake is connected to the first shoulder jet hole through the connecting pipe.

2. The air-breathing ejector-type thermal protection device for reentry vehicles according to claim 1, characterized in that, Multiple first shoulder jet holes are arranged at equal intervals around the shoulder.

3. The air-breathing ejector-type thermal protection device for reentry vehicles according to claim 1, characterized in that, The two ends of the control valve are connected to the connecting pipe via adapters. The front end of the connecting pipe is connected to the head air intake port, and the rear end of the connecting pipe is connected to the first shoulder jet port.

4. A control method for a reentry vehicle's air-breathing ejector-type thermal protection device, characterized in that, The method, applied to the thermal protection device as described in any one of claims 1-3, comprises: During flight, in response to a command for heat protection on the shoulder of the aircraft, the control valve of the guiding assembly is opened to connect the head air intake port with the shoulder jet port, so that the incoming air absorbed by the head air intake port is guided by the guiding assembly to be ejected from the shoulder jet port, thereby forming heat protection on the shoulder.

5. The control method for the air-breathing ejector-type thermal protection device for reentry vehicles according to claim 4, characterized in that, The method further includes: During the flight of the aircraft, when the aircraft has an angle of attack, the control valve corresponding to the shoulder jet hole facing the direction of the incoming flow is opened to provide thermal protection for the shoulder jet hole facing the direction of the incoming flow.

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