Hypersonic vehicle heat reduction and drag reduction method, device, equipment and storage medium

Abstract

The embodiments of this disclosure provide a method, apparatus, device, and storage medium for reducing heat and drag in hypersonic vehicles, including: acquiring target flight state data of the vehicle, wherein the target flight state data includes flight Mach number and angle of attack; acquiring target setting parameters corresponding to the target flight state data of the vehicle, wherein the target setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio, and number of lateral jet directions; and adjusting the target setting parameters of the vehicle based on the target flight state data, which can effectively reduce the aerodynamic heat and drag of the vehicle at non-zero angles of attack, improve the aerodynamic performance of the vehicle, and greatly increase its maneuverability.

Description

Technical Field

[0001] The embodiments disclosed herein relate to the field of aircraft design technology and related technical fields, specifically to a method, apparatus, device, and storage medium suitable for heat reduction and drag reduction of a hypersonic aircraft. Background Technology

[0002] Hypersonic vehicles have enormous economic and military value.

[0003] Due to the influence of the atmospheric environment, hypersonic vehicles face two major problems when flying at high speeds: enormous aerodynamic drag and severe aerodynamic heat, which seriously affect their performance. However, existing heat reduction and drag mitigation solutions are mostly proposed for the zero angle of attack of the vehicle. When deviating from zero angle of attack, especially at high angles of attack, the heat reduction and drag mitigation effects of these technologies deteriorate.

[0004] Given the problems existing in the current technology, how to achieve thermal drag reduction during descent of an aircraft at high angles of attack is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] The embodiments described herein provide a method, apparatus, device, and storage medium for reducing heat and drag in hypersonic vehicles, addressing the problems existing in the prior art.

[0006] Firstly, according to the content of this disclosure, a method for reducing heat and drag in hypersonic vehicles is provided, including:

[0007] Collect target flight status data of the aircraft, wherein the target flight status data includes flight Mach number and angle of attack;

[0008] Acquire target setting parameters corresponding to the target flight state data of the aircraft, wherein the target setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio, and number of lateral jet directions;

[0009] The target setting parameters of the aircraft are adjusted based on the target flight status data.

[0010] In some embodiments of this disclosure, before collecting the target flight status data of the aircraft, the method further includes:

[0011] Acquire first flow field characteristic data corresponding to a blunt-nosed body under a preset flight state and different first preset setting parameters, wherein the first preset setting parameters include shock bar size parameters and reverse jet pressure ratio, and the first flow field characteristic data includes at least the surface temperature, aerodynamic force, shock wave intensity, shock wave position and shock wave angle of the blunt-nosed body;

[0012] Based on the first flow field characteristic data, the first heat flux and the first resistance on the surface of the blunt body are determined under different first preset setting parameters;

[0013] Based on the first heat flow and the first resistance on the surface of the blunt-nosed body, the first target preset setting parameters of the blunt-nosed body in the preset flight state are determined.

[0014] In some embodiments of this disclosure, the method further includes:

[0015] Based on the first heat flow and the first resistance on the surface of the blunt body, a first correspondence is established between the blunt body in the preset flight state and the preset setting parameters of the first target.

[0016] In some embodiments of this disclosure, before collecting the target flight status data of the aircraft, the method further includes:

[0017] Acquire second flow field characteristic data corresponding to the blunt-nosed body under the preset flight state and different second preset setting parameters, wherein the second preset setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio and lateral jet direction, and the second flow field characteristic data includes at least the surface temperature, aerodynamic force, shock wave intensity, shock wave position and shock wave angle of the blunt-nosed body;

[0018] Based on the second flow field characteristic data, the second heat flow and the second resistance on the surface of the blunt body are determined under different second preset setting parameters;

[0019] Based on the second heat flow and the second resistance on the surface of the blunt-nosed body, the second target preset setting parameters of the blunt-nosed body in the preset flight state are determined.

[0020] In some embodiments of this disclosure, the method further includes:

[0021] Based on the second heat flow and the second resistance on the surface of the blunt body, a second correspondence is established between the blunt body and the preset parameters of the second target under the preset flight state.

[0022] In some embodiments of this disclosure, the method further includes:

[0023] A parameter table is constructed based on the first correspondence and the second correspondence. The parameter table includes a preset flight state, a first target preset setting parameter, a first heat flow, a first drag, a second target preset setting parameter, a second heat flow, and a second drag.

[0024] In some embodiments of this disclosure, before acquiring the target setting parameters corresponding to the target flight state data of the aircraft, the method further includes:

[0025] A target parameter table is selected based on the flight Mach number and the angle of attack number;

[0026] The acquisition of target setting parameters corresponding to the target flight state data of the aircraft includes:

[0027] Obtain the target setting parameters corresponding to the target flight status data from the target parameter table.

[0028] Secondly, according to the present disclosure, a heat reduction and drag reduction device for hypersonic vehicles is provided, comprising:

[0029] The target flight status data acquisition module is used to acquire the target flight status data of the aircraft, wherein the target flight status data includes flight Mach number and angle of attack.

[0030] The target setting parameter acquisition module is used to acquire target setting parameters corresponding to the target flight state data of the aircraft. The target setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio, and number of lateral jet directions.

[0031] The adjustment module is used to adjust the target setting parameters of the aircraft based on the target flight status data.

[0032] Thirdly, according to the present disclosure, a computer device is provided, including a memory and a processor, wherein the memory stores a computer program, and the processor executes the computer program to implement the steps of the method as described in any of the above embodiments.

[0033] Fourthly, according to the present disclosure, a computer-readable storage medium is provided, on which a computer program is stored, and when executed by a processor, the computer program implements the steps of the method as described in any of the above embodiments.

[0034] The hypersonic vehicle heat reduction and drag reduction method, apparatus, device, and storage medium provided in this disclosure employ an adaptive combination of shock bar, reverse jet, and lateral jet. Based on different flight Mach numbers and angles of attack of the vehicle, parameters such as shock bar length, reverse jet pressure ratio, lateral jet pressure ratio, and lateral jet direction are adaptively adjusted. This allows for adjustment of the bow-shaped shock wave position, reducing the risk of shock bar tip ablation, and adjusting the shock wave angle. Specifically, the lateral jets adjust the shock wave angles on the windward and leeward sides of the vehicle, reducing shock wave-shock wave interaction and minimizing the shock wave angle. For example, in non-zero positive angles of attack, increasing the lateral jet pressure ratio on the windward side increases the shock wave angle, causing the re-attached shock wave to move away from the vehicle shoulder, reducing shoulder ablation and drag. Conversely, decreasing the lateral jet pressure ratio on the leeward side reduces the shock wave angle and drag. The adaptive heat reduction and drag reduction method for hypersonic vehicles provided in this disclosure can not only reduce the heat and drag of the vehicle at zero angle of attack, but also effectively reduce the heat and drag of the vehicle at non-zero angle of attack, thereby improving the aerodynamic performance of the vehicle and greatly increasing its maneuverability.

[0035] The above description is merely an overview of the technical solutions of the embodiments of this application. In order to better understand the technical means of the embodiments of this application and to implement them in accordance with the contents of the specification, and to make the above and other objects, features and advantages of the embodiments of this application more obvious and understandable, specific implementation methods of this application are described below. Attached Figure Description

[0036] To more clearly illustrate the technical solutions of the embodiments of this disclosure, the accompanying drawings of the embodiments will be briefly described below. It should be understood that the drawings described below only relate to some embodiments of this disclosure and are not intended to limit this disclosure, wherein:

[0037] Figure 1 This is a schematic flowchart of a method for reducing heat and drag of a hypersonic vehicle according to an embodiment of this disclosure;

[0038] Figure 2 This is a schematic diagram of the structure of a heat reduction and drag reduction device for a hypersonic vehicle provided in an embodiment of this disclosure;

[0039] Figure 3 This is a schematic diagram of the structure of a computer device provided in an embodiment of this disclosure.

[0040] In the accompanying diagram, markers with the same last two digits correspond to the same elements. It should be noted that the elements in the diagram are schematic and not drawn to scale. Detailed Implementation

[0041] To make the objectives, technical solutions, and advantages of the embodiments of this disclosure clearer, the technical solutions of the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of this disclosure. All other embodiments obtained by those skilled in the art based on the described embodiments of this disclosure without creative effort are also within the scope of protection of this disclosure.

[0042] Unless otherwise defined, all terms used herein (including technical and scientific terms) shall have the same meaning as commonly understood by one of ordinary skill in the art to which this subject matter pertains. It will be further understood that terms such as those defined in commonly used dictionaries shall be interpreted as having the meaning consistent with their meaning in the context of the specification and in the relevant art, and shall not be interpreted in an idealized or overly formal form unless otherwise explicitly defined herein. As used herein, the statement of “connecting” or “coupling” two or more parts together shall mean that these parts are directly joined together or joined through one or more intermediate components.

[0043] The term "embodiment" as used herein means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of the phrase "embodiment" in various places throughout the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment mutually exclusive with other embodiments. It will be explicitly and implicitly understood by those skilled in the art that the embodiments described herein can be combined with other embodiments.

[0044] In this article, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can mean: A exists, A and B exist simultaneously, or B exists. Additionally, the character " / " in this article generally indicates that the preceding and following related objects have an "or" relationship.

[0045] Furthermore, in all embodiments of this disclosure, terms such as “first” and “second” are used only to distinguish one component (or part of a component) from another component (or another part of a component).

[0046] In the description of this application, unless otherwise stated, "multiple" means two or more (including two), and similarly, "multiple groups" means two or more (including two groups).

[0047] To enable those skilled in the art to better understand the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings.

[0048] Based on the problems existing in the current technology Figure 1This is a schematic flowchart of a method for reducing heat and drag of a hypersonic vehicle according to an embodiment of this disclosure, as shown below. Figure 1 As shown, the specific process of the hypersonic vehicle heat reduction and drag reduction method includes:

[0049] S110: Collect target flight status data of the aircraft.

[0050] The target flight status data includes flight Mach number and angle of attack.

[0051] Currently, the combined heat reduction and drag reduction scheme of shock bar-lateral jet-reverse jet has a good effect on heat reduction and drag reduction when the aircraft is at zero angle of attack. Its main principle is that the shock bar pushes the bow-shaped shock wave at the leading edge of the aircraft away from the aircraft surface, and the reverse jet at the end of the drag reduction bar pushes the bow-shaped shock wave away from the end of the drag reduction bar, reducing the temperature at the end of the drag reduction bar; the reverse jet on the side of the drag reduction bar expands the shock wave angle, thereby reducing the shock wave-shock wave interaction, thus reducing the temperature at the front of the aircraft and reducing the drag of the aircraft. However, as the angle of attack of the aircraft increases, especially at high angles of attack, the shock wave reattaches on the lower shoulder of the aircraft, and the reattachment position moves closer to the leading edge of the aircraft as the angle of attack increases, causing ablation of the aircraft shoulder and even the leading edge, and increasing drag.

[0052] Based on the problem that existing technologies have poor heat reduction and drag reduction effects when aircraft are at high angles of attack, this application embodiment first collects the target flight state data of the aircraft, which includes the flight Mach number and angle of attack. That is, when the aircraft is at a high flight Mach number and when there is an angle of attack during flight, the flight Mach number and angle of attack of the aircraft are first collected. Then, based on steps S120 and S130, the parameters of the aircraft are adjusted to reduce the temperature at the front of the aircraft and reduce the drag of the aircraft.

[0053] S120. Obtain the target setting parameters corresponding to the target flight status data of the aircraft.

[0054] The target setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio, and number of lateral jet directions.

[0055] S130. Adjust the target setting parameters of the aircraft based on the target flight status data.

[0056] In a specific implementation, after acquiring the target flight state data of the aircraft, the target setting parameters corresponding to the target flight state of the aircraft are obtained, and the target setting parameters of the aircraft are adjusted based on the target flight state data. That is, the parameters of any of the following can be adjusted: shock bar size, reverse jet pressure ratio, lateral jet pressure ratio, and lateral jet direction, in order to reduce the drag of the aircraft and lower the temperature at the front of the aircraft.

[0057] In a specific implementation, since the Mach number and angle of attack of the aircraft are constantly changing, the aircraft's settings are adaptively adjusted according to different Mach numbers and angles of attack to ensure that the aircraft has low drag and low front temperature during flight.

[0058] The hypersonic vehicle heat reduction and drag reduction method provided in this embodiment employs an adaptive combination of shock bar, reverse jet, and lateral jet. Based on different flight Mach numbers and angles of attack, it adaptively adjusts parameters such as shock bar length, reverse jet pressure ratio, lateral jet pressure ratio, and lateral jet direction. This allows for adjustment of the bow-shaped shock wave position, reducing the risk of shock bar tip ablation, and adjusting the shock wave angle. Specifically, the lateral jets adjust the shock wave angles on the windward and leeward sides of the vehicle, weakening shock wave-shock wave interaction and minimizing the shock wave angle. For example, in non-zero positive angles of attack, increasing the lateral jet pressure ratio on the windward side increases the shock wave angle, causing the re-attached shock wave to move away from the vehicle shoulder, reducing shoulder ablation and drag. Conversely, decreasing the lateral jet pressure ratio on the leeward side reduces the shock wave angle and drag. The adaptive heat reduction and drag reduction method for hypersonic vehicles provided in this disclosure can not only reduce the heat and drag of the vehicle at zero angle of attack, but also effectively reduce the heat and drag of the vehicle at non-zero angle of attack, thereby improving the aerodynamic performance of the vehicle and greatly increasing its maneuverability.

[0059] As one specific implementation, before step S110, the following steps are included:

[0060] Acquire first flow field characteristic data corresponding to a blunt-nosed body under a preset flight state and different first preset setting parameters. The first preset setting parameters include shock bar size parameters and reverse jet pressure ratio. The first flow field characteristic data includes at least the surface temperature, aerodynamic force, shock wave intensity, shock wave position, and shock wave angle of the blunt-nosed body.

[0061] Based on the first flow field characteristic data, the first heat flow and the first resistance on the surface of the blunt body are determined under different first preset setting parameters.

[0062] Based on the first heat flow and the first drag on the surface of the blunt-nosed body, the first target preset setting parameters of the blunt-nosed body in the preset flight state are determined.

[0063] The preset flight state includes the flight state of the aircraft corresponding to the preset Mach number and preset angle of attack. For example, Mach number 2, angle of attack 0°; Mach number 2, angle of attack 2°; Mach number 2, angle of attack 4°; ..., Mach number 2, angle of attack 28°; Mach number 2, angle of attack 30°; or, for example, Mach number 4, angle of attack 0°; Mach number 4... Angle of attack of 2°, flight Mach number of 4, angle of attack of 4°, ..., flight Mach number of 4, angle of attack of 28°, flight Mach number of 4, angle of attack of 30°, or flight Mach number of 6, angle of attack of 0°, flight Mach number of 6, angle of attack of 2°, flight Mach number of 6, angle of attack of 4°, ..., flight Mach number of 6, angle of attack of 28°, flight Mach number of 6, angle of attack of 30°.

[0064] In the specific implementation process, the first flow field characteristic data of the blunt-nosed body under the preset flight state and different first preset setting parameters are the first flow field characteristic data of the blunt-nosed body under different shock bar size parameters and reverse jet pressure ratio when the blunt-nosed body is at a fixed flight Mach number and angle of attack. Then, the first heat flux of the blunt-nosed body surface is determined based on the temperature and aerodynamic force of the blunt-nosed body surface included in the first flow field characteristic data. The first drag of the blunt-nosed body surface is determined based on the temperature, aerodynamic force, shock wave intensity, shock wave position and shock wave angle of the blunt-nosed body surface included in the first flow field characteristic data.

[0065] Based on the determined first heat flux and first drag, the first preset setting parameter that minimizes the first drag and first heat flux under the preset flight state is determined as the first target preset setting parameter.

[0066] After determining the first heat flux and the first drag, a first correspondence between the blunt-nosed body and the preset parameters of the first target is established based on the first heat flux and the first drag on the surface of the blunt-nosed body.

[0067] That is, the first preset setting parameters that minimize the first resistance and the first heat flow are selected as the preset setting parameters of the blunt body and the first target in the preset flight state (that is, the shock bar size parameters and the reverse jet pressure ratio).

[0068] In the above embodiments, the parameters of the blunt-nosed body are the shock bar size parameters and the reverse jet pressure ratio to obtain the first target preset setting parameters of the blunt-nosed body in a preset flight state. The following embodiments will obtain the second target preset setting parameters of the blunt-nosed body in a preset flight state by adjusting the shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio, and lateral jet direction. The specific implementation methods are as follows:

[0069] Acquire second flow field characteristic data corresponding to a blunt-nosed body under a preset flight state and different second preset setting parameters. The second preset setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio, and lateral jet direction. The second flow field characteristic data includes at least the surface temperature, aerodynamic force, shock wave intensity, shock wave position, and shock wave angle of the blunt-nosed body.

[0070] Based on the second flow field characteristic data, the second heat flow and the second resistance on the blunt body surface are determined under different second preset setting parameters.

[0071] Based on the second heat flow and the second drag on the surface of the blunt-nosed body, the second target preset setting parameters of the blunt-nosed body in the preset flight state are determined.

[0072] By adjusting the pressure ratio and direction of the lateral jets on the windward and leeward sides of a blunt-nosed body at different angles of attack, the size of the recirculation zone and the shock-shock interaction can be controlled. Specifically, at non-zero angles of attack, increasing the lateral jet pressure on the windward side of the blunt-nosed body increases the bow-shaped shock wave angle on the windward side, enlarges the recirculation zone, and weakens the reattached shock wave intensity at the shoulder of the windward side. Simultaneously, decreasing the lateral jet pressure ratio on the leeward side reduces the bow-shaped shock wave angle on the leeward side, decreases the recirculation zone, and reduces the shock wave intensity. In other words, adjusting the lateral jet angle while adjusting the lateral jet pressure ratio, so that the lateral jet is directly facing the shock wave surface, can reduce the heat flux and drag on the surface of the blunt-nosed body.

[0073] In the specific implementation process, the second flow field characteristic data of the blunt-nosed body under the preset flight state and different second preset setting parameters are the second flow field characteristic data of the blunt-nosed body under different shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio and lateral jet direction when the blunt-nosed body is at a fixed flight Mach number and angle of attack. Then, based on the temperature and aerodynamic force of the blunt-nosed body surface included in the second flow field characteristic data, the second heat flux of the blunt-nosed body surface is determined. Based on the temperature, aerodynamic force, shock wave intensity, shock wave position and shock wave angle of the blunt-nosed body surface included in the second flow field characteristic data, the second drag of the blunt-nosed body surface is determined.

[0074] Based on the determined second heat flux and second drag, the second preset setting parameter that minimizes the second drag and second heat flux under the preset flight state is determined as the second target preset setting parameter.

[0075] After determining the second heat flux and the second drag, a second correspondence between the blunt-nosed body and the preset parameters of the second target is constructed based on the second heat flux and the second drag on the surface of the blunt-nosed body.

[0076] That is, the second preset setting parameters with the minimum second resistance and second heat flow are selected as the preset setting parameters of the blunt body and the second target in the preset flight state (that is, shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio and lateral jet direction).

[0077] After determining the first correspondence between the blunt-nosed body in the preset flight state and the preset setting parameters of the first target, and the second correspondence between the blunt-nosed body in the preset flight state and the preset setting parameters of the second target, a target parameter table is constructed based on the first and second correspondences. That is, the constructed target parameter table includes the preset flight state, the preset setting parameters of the first target, the first heat flow, the first drag, the preset setting parameters of the second target, the second heat flow, and the second drag.

[0078] At this point, the specific process of obtaining the target setting parameters corresponding to the target flight status data of the aircraft is as follows:

[0079] First, based on the target flight state data of the aircraft, a target parameter table corresponding to the target flight state data is selected. Then, based on the relationship between the first heat flow and the second heat flow in the target parameter table, as well as the relationship between the first drag and the second drag, the target preset setting parameters corresponding to the minimum heat flow and drag are selected as the target setting parameters for flight.

[0080] Based on the above embodiments, this disclosure also provides a heat reduction and drag reduction device for hypersonic aircraft, such as... Figure 2 As shown, the hypersonic vehicle heat reduction and drag reduction device includes:

[0081] The target flight status data acquisition module 210 is used to acquire the target flight status data of the aircraft, including the flight Mach number and angle of attack.

[0082] The target setting parameter acquisition module 220 is used to acquire target setting parameters corresponding to the target flight state data of the aircraft. The target setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio, and number of lateral jet directions.

[0083] The adjustment module 230 is used to adjust the target setting parameters of the aircraft based on the target flight status data.

[0084] The hypersonic vehicle heat reduction and drag reduction device provided in this application adopts an adaptive combination of shock bar, reverse jet, and lateral jet. Based on different flight Mach numbers and angles of attack of the vehicle, it adaptively adjusts parameters such as shock bar length, reverse jet pressure ratio, lateral jet pressure ratio, and lateral jet direction. On the one hand, it can adjust the position of the bow-shaped shock wave, reducing the ablation of the shock bar end; on the other hand, it can adjust the shock angle, especially by adjusting the shock angles on the windward and leeward sides of the vehicle through the lateral jets, reducing shock-shock interaction and minimizing the shock angle. For example, in a non-zero positive angle of attack state, increasing the lateral jet pressure ratio on the windward side increases the shock angle on the windward side, causing the re-attached shock wave to move away from the vehicle shoulder, reducing shoulder ablation and drag. Conversely, decreasing the lateral jet pressure ratio on the leeward side reduces the shock angle on the leeward side, further reducing drag. The adaptive heat reduction and drag reduction method for hypersonic vehicles provided in this disclosure can not only reduce the heat and drag of the vehicle at zero angle of attack, but also effectively reduce the heat and drag of the vehicle at non-zero angle of attack, thereby improving the aerodynamic performance of the vehicle and greatly increasing its maneuverability.

[0085] In a specific implementation, the hypersonic vehicle heat reduction and drag reduction device further includes: a first flow field characteristic data acquisition module, a first thermal flow drag determination unit, and a first target preset setting parameter determination unit;

[0086] The first flow field characteristic data acquisition module is used to acquire the first flow field characteristic data corresponding to the blunt body under the preset flight state and different first preset setting parameters. The first preset setting parameters include the shock bar size parameter and the reverse jet pressure ratio. The first flow field characteristic data includes at least the temperature, aerodynamic force, shock wave intensity, shock wave position and shock wave angle of the blunt body surface.

[0087] The first thermal flow resistance determination unit is used to determine the first thermal flow and the first resistance of the blunt body surface under different first preset setting parameters based on the first flow field characteristic data.

[0088] The first target preset setting parameter determination unit is used to determine the first target preset setting parameters of the blunt-nosed body in a preset flight state based on the first heat flow and the first drag on the surface of the blunt-nosed body.

[0089] In a specific implementation, the hypersonic vehicle heat reduction and drag reduction device further includes: a first correspondence construction module, used to construct a first correspondence between the blunt body in a preset flight state and the preset parameters of the first target based on the first heat flow and the first drag on the surface of the blunt body.

[0090] In a specific implementation, the hypersonic vehicle heat reduction and drag reduction device further includes: a second flow field characteristic data acquisition module, a second thermal flow resistance determination unit, and a second target preset setting parameter determination unit;

[0091] The second flow field characteristic data acquisition module is used to acquire the second flow field characteristic data corresponding to the blunt body under preset flight state and different second preset setting parameters. The second preset setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio and lateral jet direction. The second flow field characteristic data includes at least the surface temperature, aerodynamic force, shock wave intensity, shock wave position and shock wave angle of the blunt body.

[0092] The second thermal flow resistance determination unit is used to determine the second thermal flow and the second resistance of the blunt body surface under different second preset setting parameters based on the second flow field characteristic data.

[0093] The second target preset setting parameter determination unit is used to determine the second target preset setting parameters of the blunt-nosed body in a preset flight state based on the second heat flow and the second drag on the surface of the blunt-nosed body.

[0094] In a specific implementation, the hypersonic vehicle heat reduction and drag reduction device further includes: a second correspondence construction module, used to construct a second correspondence between the blunt body in a preset flight state and the preset parameters of the second target based on the second heat flow and the second drag on the surface of the blunt body.

[0095] In a specific implementation, the hypersonic vehicle heat reduction and drag reduction device further includes: a parameter table construction module, used to construct a parameter table based on a first correspondence and a second correspondence. The parameter table includes a preset flight state, a first target preset setting parameter, a first heat flux, a first drag, a second target preset setting parameter, a second heat flux, and a second drag.

[0096] In a specific implementation, before acquiring the target setting parameters corresponding to the target flight state data of the aircraft, the following steps are also included:

[0097] Target parameter selection table based on flight Mach number and angle of attack;

[0098] Obtain the target setting parameters corresponding to the target flight status data of the aircraft, including:

[0099] Retrieve the target setting parameters corresponding to the target flight status data from the target parameter table.

[0100] This application also provides a computer device. Please refer to the following for details. Figure 3 , Figure 3 This is a basic structural block diagram of the computer device in this embodiment.

[0101] The computer device includes a memory 410 and a processor 420 that are interconnected via a system bus. It should be noted that only a computer device with components 410-420 is shown in the figure; however, it should be understood that it is not required to implement all the shown components, and more or fewer components may be implemented alternatively. Those skilled in the art will understand that the computer device described herein is a device capable of automatically performing numerical calculations and / or information processing according to pre-set or stored instructions, and its hardware includes, but is not limited to, microprocessors, application-specific integrated circuits (ASICs), field-programmable gate arrays (FPGAs), digital signal processors (DSPs), embedded devices, etc.

[0102] Computer devices can include desktop computers, laptops, handheld computers, and cloud servers. These devices allow for human-computer interaction with users through methods such as keyboards, mice, remote controls, touchpads, or voice-activated devices.

[0103] The memory 410 includes at least one type of readable storage medium, including non-volatile memory or volatile memory, such as flash memory, hard disk, multimedia card, card-type memory (e.g., SD or DX memory), random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM), electrically erasable programmable read-only memory (EEPROM), programmable read-only memory (PROM), magnetic memory, magnetic disk, optical disk, etc. RAM may include static RAM or dynamic RAM. In some embodiments, the memory 410 may be an internal storage unit of a computer device, such as the hard disk or RAM of the computer device. In other embodiments, the memory 410 may also be an external storage device of the computer device, such as a plug-in hard drive, Smart Media Card (SMC), Secure Digital (SD) card, or FlashCard. Of course, the memory 410 may include both internal and external storage units of the computer device. In this embodiment, the memory 410 is typically used to store the operating system and various application software installed on the computer device, such as the program code of the methods described above. Furthermore, the memory 410 may also be used to temporarily store various types of data that have been output or will be output.

[0104] The processor 420 is typically used to perform the overall operation of a computer device. In this embodiment, the memory 410 is used to store program code or instructions, including computer operation instructions, and the processor 420 is used to execute the program code or instructions stored in the memory 410 or to process data, such as program code that runs the methods described above.

[0105] In this article, the bus can be an Industry Standard Architecture (ISA) bus, a Peripheral Component Interconnect (PCI) bus, or an Extended Industry Standard Architecture (EISA) bus, etc. This bus system can be divided into address bus, data bus, control bus, etc. For ease of illustration, only one thick line is used to represent it in the diagram, but this does not mean that there is only one bus or one type of bus.

[0106] Another embodiment of this application also provides a computer-readable medium, which may be a computer-readable signal medium or a computer-readable medium. A processor in a computer reads computer-readable program code stored in the computer-readable medium, enabling the processor to execute the functional actions specified in each step or combination of steps in the above method; and to generate means for implementing the functional actions specified in each block or combination of blocks in the block diagram.

[0107] Computer-readable media include, but are not limited to, electronic, magnetic, optical, electromagnetic, infrared memory or semiconductor systems, devices or apparatuses, or any suitable combination thereof, wherein the memory is used to store program code or instructions, the program code including computer operation instructions, and the processor is used to execute the program code or instructions of the above-described methods stored in the memory.

[0108] The definitions of memory and processor can be found in the description of the foregoing computer device embodiments, and will not be repeated here.

[0109] In the several embodiments provided in this application, it should be understood that the disclosed systems, apparatuses, and methods can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of modules or units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some interfaces; the indirect coupling or communication connection between apparatuses or units may be electrical, mechanical, or other forms.

[0110] In the various embodiments of this application, the functional units or modules can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0111] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it 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 all or part 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.) or processor to execute all or part of the steps of the methods of 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.

[0112] Unless otherwise expressly indicated by the context, the singular form of words used herein and in the appended claims includes the plural form, and vice versa. Thus, when referring to the singular, the plural form of the corresponding term is generally included. Similarly, the terms “comprising” and “including” shall be interpreted as including rather than exclusively. Likewise, the terms “including” and “or” shall be interpreted as including unless such interpretation is expressly prohibited herein. Where the term “example” is used herein, particularly when it follows a set of terms, the “example” is merely exemplary and illustrative and should not be considered exclusive or extensive.

[0113] Further aspects and scope of adaptation become apparent from the description provided herein. It should be understood that various aspects of this application may be implemented individually or in combination with one or more other aspects. It should also be understood that the descriptions and specific embodiments herein are for illustrative purposes only and are not intended to limit the scope of this application.

[0114] Several embodiments of this disclosure have been described in detail above. However, it is obvious that those skilled in the art can make various modifications and variations to the embodiments of this disclosure without departing from the spirit and scope of this disclosure. The scope of protection of this disclosure is defined by the appended claims.

Claims

1. A method for reducing heat and drag in a hypersonic vehicle, characterized in that, include: Collect target flight status data of the aircraft, wherein the target flight status data includes flight Mach number and angle of attack; Obtain target setting parameters corresponding to the target flight state data of the aircraft, wherein the target setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio, and number of lateral jet directions; The target setting parameters of the aircraft are adjusted based on the target flight status data; Prior to collecting the target flight status data of the aircraft, the process also includes: Acquire first flow field characteristic data corresponding to a blunt-nosed body under a preset flight state and different first preset setting parameters, wherein the first preset setting parameters include shock bar size parameters and reverse jet pressure ratio, and the first flow field characteristic data includes at least the surface temperature, aerodynamic force, shock wave intensity, shock wave position and shock wave angle of the blunt-nosed body; Based on the first flow field characteristic data, the first heat flux and the first resistance on the surface of the blunt body are determined under different first preset setting parameters; Based on the first heat flow and the first resistance on the surface of the blunt-nosed body, the first target preset setting parameters of the blunt-nosed body in the preset flight state are determined.

2. The method according to claim 1, characterized in that, The method further includes: Based on the first heat flow and the first resistance on the surface of the blunt body, a first correspondence is established between the blunt body in the preset flight state and the preset setting parameters of the first target.

3. The method according to claim 2, characterized in that, Before collecting the target flight status data of the aircraft, the process also includes: Acquire second flow field characteristic data corresponding to the blunt-nosed body under the preset flight state and different second preset setting parameters, wherein the second preset setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio and lateral jet direction, and the second flow field characteristic data includes at least the surface temperature, aerodynamic force, shock wave intensity, shock wave position and shock wave angle of the blunt-nosed body; Based on the second flow field characteristic data, the second heat flow and the second resistance on the surface of the blunt body are determined under different second preset setting parameters; Based on the second heat flow and the second resistance on the surface of the blunt-nosed body, the second target preset setting parameters of the blunt-nosed body in the preset flight state are determined.

4. The method according to claim 3, characterized in that, The method further includes: Based on the second heat flow and the second resistance on the surface of the blunt body, a second correspondence is established between the blunt body and the preset parameters of the second target under the preset flight state.

5. The method according to claim 4, characterized in that, The method further includes: A parameter table is constructed based on the first correspondence and the second correspondence. The parameter table includes a preset flight state, a first target preset setting parameter, a first heat flow, a first drag, a second target preset setting parameter, a second heat flow, and a second drag.

6. The method according to claim 3, characterized in that, Before acquiring the target setting parameters corresponding to the target flight state data of the aircraft, the method further includes: A target parameter table is selected based on the flight Mach number and the angle of attack number; The acquisition of target setting parameters corresponding to the target flight state data of the aircraft includes: Obtain the target setting parameters corresponding to the target flight status data from the target parameter table.

7. A heat reduction and drag reduction device for hypersonic aircraft, characterized in that, include: The target flight status data acquisition module is used to acquire the target flight status data of the aircraft, wherein the target flight status data includes flight Mach number and angle of attack. The target setting parameter acquisition module is used to acquire target setting parameters corresponding to the target flight state data of the aircraft. The target setting parameters include shock bar size parameters, reverse jet pressure ratio, lateral jet pressure ratio, and number of lateral jet directions. An adjustment module is used to adjust the target setting parameters of the aircraft based on the target flight status data; Prior to collecting the target flight status data of the aircraft, the process also includes: Acquire first flow field characteristic data corresponding to a blunt-nosed body under a preset flight state and different first preset setting parameters, wherein the first preset setting parameters include shock bar size parameters and reverse jet pressure ratio, and the first flow field characteristic data includes at least the surface temperature, aerodynamic force, shock wave intensity, shock wave position and shock wave angle of the blunt-nosed body; Based on the first flow field characteristic data, the first heat flux and the first resistance on the surface of the blunt body are determined under different first preset setting parameters; Based on the first heat flow and the first resistance on the surface of the blunt-nosed body, the first target preset setting parameters of the blunt-nosed body in the preset flight state are determined.

8. A computer device, characterized in that, include: One or more processors; Storage device for storing one or more programs. When the one or more programs are executed by the one or more processors, the one or more processors implement the method as described in any one of claims 1 to 6.

9. A computer-readable storage medium having a computer program stored thereon, characterized in that, When the program is executed by the processor, it implements the method as described in any one of claims 1 to 6.

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