A method for judging droplet impact on a hypersonic wall surface in a high-humidity environment

Abstract

The application discloses a kind of methods for judging droplet impact on hypersonic wall in high water vapor environment, and relates to the technical field of hypersonic speed, comprising, obtaining the initial physical parameters of droplet and the leading edge flow field parameters of hypersonic vehicle;Based on the initial physical parameters of droplet and the flow field parameters behind shock wave, the breaking displacement of droplet before breaking and vaporizing can be calculated;Based on the leading edge flow field parameters of the vehicle, the maximum geometric distance of droplet from passing through the shock wave to the wall of the vehicle is calculated;Impact criterion formula is constructed, the breaking displacement is compared with the maximum geometric distance, and the impact determination signal of droplet is output according to the comparison result.The application realizes the accurate determination of droplet impact or not, adapts to the sea-skimming flight condition of hypersonic vehicle, and can also determine the impact risk boundary to guide the flight height planning, and overall realizes the efficient and accurate judgment of droplet impact on hypersonic wall in high water vapor environment, to ensure the flight safety of the vehicle.

Description

Technical Field

[0001] This invention relates to the field of hypersonic technology, and in particular to a method for determining the impact of droplets on a hypersonic wall in a high-water-vapor environment. Background Technology

[0002] With the rapid development of hypersonic flight technology, the aerodynamic and thermodynamic characteristics of aircraft in complex weather environments have received increasing attention. Especially in low-altitude, high-humidity environments, the interaction between atmospheric droplets and high-temperature walls becomes a key factor affecting the effectiveness of aircraft thermal protection systems. Traditional research is mostly based on the assumption of a continuous medium, using the Eulerian-Lagrange method to track droplet trajectories or estimating the evaporation rate of droplets in high-temperature airflows using empirical formulas. These methods have formed relatively mature application systems under subsonic or hyposonic conditions, enabling preliminary predictions of heat and mass transfer processes in droplets. However, when the flight Mach number increases significantly, shock wave structures, boundary layer transitions, and droplet dynamics exhibit strong nonlinear coupling characteristics, and traditional methods face theoretical limitations when dealing with multiphase flow interactions under extreme non-equilibrium conditions.

[0003] Existing technologies for predicting droplet behavior in hypersonic strong shock fields are primarily limited by their ability to dynamically characterize the relationship between droplet breakup and wall geometric constraints. Specifically, existing models typically treat droplet breakup criteria and wall distance as independent parameters, lacking quantitative correlation analysis of their critical relationship. Because a mechanism for comparing the effective displacement of the droplet with its remaining flight distance after the shock wave has not been established, it is difficult to accurately determine whether the droplet has completed a phase transition or breakup process before reaching the wall. This technical bottleneck makes it impossible to distinguish in thermal protection designs whether the energy release mode of the droplet within the boundary layer is altered by vaporization endothermic changes in fluid properties or by generating localized hot spots through liquid impact. Summary of the Invention

[0004] In view of the aforementioned existing problems, the present invention is proposed.

[0005] Therefore, this invention provides a method for determining whether a droplet impacts a hypersonic wall in a high-moisture environment. This solves the problem in existing technologies that, due to the lack of a quantitative comparison mechanism between the breakup displacement and the geometric distance to the wall, it is impossible to accurately determine whether a droplet has impacted the wall when predicting droplet behavior.

[0006] To solve the above-mentioned technical problems, the present invention provides the following technical solution: In a first aspect, the present invention provides a method for determining the impact of droplets on a hypersonic wall in a high water vapor environment, which includes acquiring the leading edge flow field parameters of the hypersonic vehicle and the initial physical parameters of the droplets. Based on the initial physical parameters of the droplet and the flow field parameters after the shock wave, the breakup displacement that the droplet can move before breaking up and vaporizing is calculated. Based on the flow field parameters at the leading edge of the aircraft, the maximum geometric distance from the droplet to the aircraft wall after passing through the shock wave is calculated. An impact criterion formula is constructed, the breakup displacement is compared with the maximum geometric distance, and a droplet impact determination signal is output based on the comparison result.

[0007] As a preferred embodiment of the method for determining droplet impact on a hypersonic wall in a high-water-vapor environment described in this invention, the acquisition of the leading-edge flow field parameters of the hypersonic vehicle and the initial physical parameters of the droplet specifically includes: Obtain the Mach number of the incoming stream gas density before shock wave Droplet density Droplet radius The initial height of the droplet above the horizontal plane And the angle θ between the wedge-shaped wall and the horizontal plane; Based on the incoming Mach number Calculate the shock angle of the oblique shock wave by considering the angle θ between the wedge-shaped wall and the horizontal plane. β, and calculate the gas density after the shock wave based on gas dynamics. .

[0008] Furthermore, the core parameters of the leading-edge flow field of the hypersonic vehicle and the initial physical parameters of the droplet were accurately collected. Specific parameters collected included the incoming Mach number, the gas density before the shock wave, the droplet density, the droplet radius, the initial height of the droplet above the horizontal plane, and the angle between the wedge wall and the horizontal plane. After the parameter collection was completed, based on gas dynamics theory, the shock wave angle corresponding to the oblique shock wave was calculated using oblique shock wave theory based on the known incoming Mach number and the angle between the wedge wall and the horizontal plane. Then, the gas density after the shock wave was solved using standard gas dynamics relations, providing basic flow field data support for subsequent droplet motion and impact judgment.

[0009] As a preferred embodiment of the method for determining the impact of droplets on a hypersonic wall in a high-water-vapor environment described in this invention, the calculation of the breakup displacement that the droplet can move before breaking up and vaporizing specifically includes: constructing a droplet aerodynamic force model based on droplet density, post-shock gas density, and droplet radius; combining the coupling relationship between droplet surface evaporation rate and aerodynamic breakup in a high-water-vapor environment, solving the droplet's motion path from the moment it passes through the oblique shock wave to the moment it completely breaks up or completely vaporizes, and setting this motion path as the breakup displacement.

[0010] Furthermore, based on the principle of airflow drag force, a differential equation of droplet motion adapted to the hypersonic flow field is first constructed, and a dimensionless time parameter characterizing the complete breakup state of the droplet is introduced. Then, the constructed differential equation of droplet motion is numerically solved to extract the displacement distance in the final relative velocity direction when the droplet reaches the complete breakup state. The calculation verifies that this breakup displacement is determined only by the initial radius of the droplet, the droplet density, and the flow field density after the shock wave, and is not affected by the change in the initial relative velocity of the droplet.

[0011] As a preferred embodiment of the method for determining droplet impact on a hypersonic wall in a high-water-vapor environment described in this invention, the step of calculating the maximum geometric distance from the droplet to the spacecraft wall after passing through the shock wave based on the flow field parameters at the leading edge of the spacecraft specifically includes: establishing a two-dimensional geometric position mapping relationship based on the initial height of the droplet, the shock wave angle, and the angle between the wedge-shaped wall and the horizontal plane; and using a geometric projection algorithm to solve for the shortest straight-line distance from the point where the droplet passes through the oblique shock wave to the wedge-shaped wall, and defining this shortest straight-line distance as the maximum geometric distance.

[0012] Furthermore, the maximum geometric distance that the droplet can reach the spacecraft wall after passing through the shock wave is calculated. Using the initial height of the droplet, the shock wave angle, and the wall angle as the core calculation variables, and combined with the geometric relationship of the hypersonic wedge flow field, the limit distance that the droplet can reach the wall in the relative velocity direction is derived.

[0013] As a preferred embodiment of the method for determining droplet impact on a hypersonic vehicle wall in a high-water-vapor environment described in this invention, the step of constructing the impact criterion formula and outputting a droplet impact determination signal based on the comparison results specifically includes: setting the impact criterion: if the breakup displacement is greater than or equal to the maximum geometric distance, it is determined that the droplet can impact the hypersonic vehicle wall, and an effective impact determination signal is output; if the breakup displacement is less than the maximum geometric distance, it is determined that the droplet has broken up or vaporized before reaching the wall, and an invalid impact determination signal is output.

[0014] Furthermore, a quantitative criterion is constructed to accurately determine whether a droplet impacts a wall. First, the criterion function is defined as the difference between the droplet breakup displacement and the maximum geometric distance, and then the impact criterion formula is established. The judgment criteria are divided according to the judgment results. When Δ≥0, it means that the droplet breaking displacement is greater than or equal to the maximum geometric distance that can be reached to the wall, and the droplet can be judged to hit the wall of the aircraft. When Δ<0, it means that the droplet has already broken before moving to the wall, and the droplet cannot hit the wall.

[0015] As a preferred embodiment of the method for determining droplet impact on a hypersonic wall in a high-water-vapor environment according to the present invention, the step of outputting a droplet impact determination signal based on the comparison result specifically includes: Real-time acquisition of Weber numbers for droplets of different radii; When the criterion formula Δ≥0 holds, an impact signal is output, and the droplet breakup state is determined by combining the Weber number. When the criterion formula Δ<0 is true, a no-collision signal is output, indicating that the droplet has been completely broken up and vaporized before reaching the wall.

[0016] Furthermore, to complete the output of the droplet impact determination signal, firstly, the Weber number corresponding to droplets of different radii in the hypersonic flow field is monitored and acquired in real time; if the criterion formula Δ≥0 holds, the droplet impact signal is immediately output, and the breakup mode and degree of droplet impact on the wall are further determined by combining the Weber number; if the criterion formula Δ<0 holds, the droplet does not impact the wall signal is output, clearly determining that the droplet has been completely broken up and vaporized before reaching the spacecraft wall and will not have an impact effect on the wall.

[0017] As a preferred embodiment of the method for judging the impact of droplets on a hypersonic wall in a high water vapor environment described in this invention, the method is applied to the sea-skimming flight condition of a hypersonic vehicle. The hypersonic vehicle operates under sea-skimming conditions with an incoming Mach number greater than 5, and the water vapor content in the air surrounding the flight environment increases significantly, with a large number of suspended droplets in the airflow.

[0018] Furthermore, the aforementioned droplet impact assessment method is specifically applied to the sea-skimming flight condition of hypersonic vehicles. Under this condition, the incoming Mach number of the vehicle is greater than 5, indicating a typical hypersonic flight state. Due to the characteristics of the sea-skimming environment, the water vapor content in the air is significantly increased, resulting in a large number of tiny droplets formed by the evaporation of seawater suspended in the airflow. This high-water-vapor, high-droplet-concentration environment easily leads to droplet impact on the wall. This method can be adapted to this condition to quickly assess the risk of droplet impact. As a preferred embodiment of the method for determining droplet impact on a hypersonic wall in a high-water-vapor environment according to the present invention, the method further includes determining the droplet impact risk boundary: Based on the criterion formula, the maximum critical height at which droplets of different radii can impact the wall is calculated under a given working condition. A mapping table between droplet radius and maximum critical altitude was established to guide the safe flight altitude planning of aircraft in high water vapor environments.

[0019] Furthermore, based on the established impact criterion formula, under fixed flight conditions and flow field parameters, the maximum critical height at which droplets of different radii can achieve wall impact is calculated. Through batch calculations and data fitting, a mapping table between droplet radius and corresponding maximum critical height is established. This table can directly provide data for the flight altitude planning of hypersonic vehicles in high water vapor environments, guide the vehicle to avoid droplet impact risks, and ensure flight safety.

[0020] In a second aspect, the present invention provides a computer device, including a memory and a processor, wherein the memory stores a computer program, wherein: when the computer program is executed by the processor, it implements any step of the method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in the first aspect of the present invention.

[0021] Thirdly, the present invention provides a computer-readable storage medium having a computer program stored thereon, wherein: when the computer program is executed by a processor, it implements any step of the method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in the first aspect of the present invention.

[0022] The beneficial effects of this invention are as follows: by acquiring the leading-edge flow field parameters of the hypersonic vehicle and the initial physical parameters of the droplet, it provides basic data support for subsequent judgment; by calculating the droplet breakup displacement, it accurately captures the droplet's motion capability before breakup and clarifies its range of motion; by calculating the maximum geometric distance from the droplet to the wall, it determines the limit threshold for the droplet to reach the wall; by constructing an impact criterion formula and outputting a judgment signal, it achieves accurate judgment of whether the droplet will impact, adapts to the sea-skimming flight conditions of hypersonic vehicles, and can also determine the impact risk boundary to guide flight altitude planning. Overall, it achieves efficient and accurate judgment of droplet impact on hypersonic walls in high water vapor environments, ensuring the flight safety of the vehicle. Attached Figure Description

[0023] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the following description of the embodiments will be briefly introduced. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0024] Figure 1 This is a schematic diagram of a droplet passing through a shock wave and impacting a wedge-shaped wall.

[0025] Figure 2 This is a schematic diagram of a method for determining the impact of droplets on a hypersonic wall in a high-water-vapor environment.

[0026] Figure 3 This is a schematic diagram of the motion of droplets impacting a 30° wedge-shaped wall from a uniform liquid mist flow. Detailed Implementation

[0027] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0028] Many specific details are set forth in the following description in order to provide a full understanding of the invention. However, the invention may also be practiced in other ways different from those described herein, and those skilled in the art can make similar extensions without departing from the spirit of the invention. Therefore, the invention is not limited to the specific embodiments disclosed below.

[0029] Secondly, the term "one embodiment" or "embodiment" as used herein refers to a specific feature, structure, or characteristic that may be included in at least one implementation of the present invention. The phrase "in one embodiment" appearing in different places in this specification does not necessarily refer to the same embodiment, nor is it a single or selective embodiment that is mutually exclusive with other embodiments.

[0030] Reference Figures 1-3 This embodiment of the invention provides a method for determining the impact of droplets on a hypersonic wall in a high-water-vapor environment, comprising the following steps: Example 1 This example focuses on the sea-skimming flight condition of a hypersonic vehicle, employing the aforementioned judgment method to determine droplet impact on the wall. First, the flow field parameters at the vehicle's leading edge and the initial physical parameters of the droplet under this condition are obtained, yielding the corresponding incoming Mach number, gas density before the shock wave, droplet density, droplet radius, initial droplet height, and wedge-shaped wall angle. The shock wave angle and the gas density after the shock wave are then calculated. Subsequently, a differential equation of droplet motion is established based on the airflow drag force, and dimensionless time is introduced to solve for the droplet breakup displacement, which is determined solely by the droplet's own parameters and the flow field density after the shock wave. Finally, the maximum geometric distance from the droplet to the wall is calculated by combining the initial droplet height, shock wave angle, and wall angle, constructing a difference-based impact criterion formula. The system collects Weber numbers corresponding to different droplet radii in real time, calculates the impact conditions based on criteria, outputs an impact signal, and determines the fragmentation state of the droplet when it impacts the wall based on the Weber number. At the same time, it calculates the maximum critical height of droplets with different radii under this condition based on the criteria, and establishes a mapping table between radius and critical height to provide data support for the planning of sea-skimming flight altitude of the aircraft.

[0031] Example 2 This example is applied to the scenario of droplet impact prediction on the leading edge wall of a hypersonic vehicle in a high-water-vapor environment. First, the flow field parameters and initial physical parameters of the droplet under the target operating condition are collected. The shock wave angle and the gas density after the shock wave are solved using gas dynamics relationships. Next, the droplet's breakup displacement before disintegration and vaporization is calculated. A dimensionless time for complete droplet breakup is introduced during the solution process to clarify that this displacement is unaffected by the droplet's initial relative velocity. Then, the maximum geometric distance from the droplet to the wall after passing through the shock wave is calculated using geometric relationships. A criterion formula is constructed to compare the breakup displacement with the maximum geometric distance. If the calculated criterion result does not reach the impact threshold, a non-impact signal is output, indicating that the droplet has completely broken up and vaporized before reaching the wall. Simultaneously, the droplet impact risk boundary under this operating condition is determined based on the criterion formula, establishing a correspondence between the droplet radius and the maximum critical height, which can be directly used to guide the formulation of safe flight strategies for vehicles in high-water-vapor environments.

[0032] For a droplet in an airflow, its velocity change is affected by the drag force of the airflow, specifically expressed as follows: (1) in, The relative velocity between the droplet and the high-speed incoming flow after the shock wave is denoted as . The time it takes for the incoming flow of droplets to interact with the liquid. For droplet density, Where is the droplet radius, It represents the drag coefficient under the influence of airflow drag force.

[0033] Separate variables on both sides and Integrals, recording The final relative velocity at time is Given an initial relative velocity of 0, we can obtain:

[0034] (2) Speed ​​at time 0 Substituting, we can obtain the integral constant. . Based on extensive simulations and physical experiments of droplet-shock interactions, the time required for complete droplet breakup can be estimated. For completely broken dimensionless time , In (2) Replace with achievable (3) By applying the chain rule to the differential transformation of equation (1), we can obtain the relative velocity. Relative displacement distance Ordinary differential relations Eliminate both sides achievable

[0035] Separate variables

[0036] Integrating both sides yields the final displacement distance when the droplet breaks apart. relative velocity with initial Final relative velocity satisfy:

[0037] Organized (4) Combined with equation (3), substitute one of them. achievable (5) Thus, the displacement distance in the direction of the final relative velocity during droplet breakup was established. Equation (5) shows the relationship between the initial droplet and the surrounding flow field conditions. It can be seen from the equation that the displacement in the relative velocity direction when the droplet finally breaks up is only related to the initial radius, initial density and surrounding flow field density of the droplet, and is not related to the initial relative velocity of the droplet.

[0038] For high The maximum relative distance between an incoming liquid droplet and the airflow after passing through a shock wave. satisfy:

[0039] in The angle between the wedge-shaped wall and the horizontal plane, The shock angle of the oblique shock wave can be obtained from... With incoming flow Sure.

[0040] The condition for a droplet to collide with a wall before breaking apart is: That is, the criterion formula is

[0041] When the criterion formula When the value is greater than or equal to zero, the droplet can collide with the wall under given operating conditions; otherwise, it cannot collide with the wall.

[0042] In practical use, Based on the coefficients determined experimentally, they were respectively taken as... Compared to version 6.0.

[0043] against wedge-shaped wall, incoming Mach number Droplet density The gas density before the shock wave is The gas density after the shock wave At this time, the shock angle When the droplet radius is The distance from the horizontal height is When, substitute into the criterion formula to calculate At this point, the droplet can collide with the wall. All other conditions remain the same, with a height of... The droplets are substituted into the criterion formula to calculate. The droplet cannot hit the wall.

[0044] Based on this formula, the radius can also be determined under the above working conditions. The maximum height that a droplet can hit a wall is approximately The table below shows the Weber number and the maximum height that droplets of different radii can reach when impacting a wall: Table 1. Weber numbers and maximum impact heights of droplets with different radii. ; This embodiment also provides a computer device applicable to the method for determining the impact of droplets on a hypersonic wall in a high-water-vapor environment, comprising: a memory and a processor; the memory is used to store computer-executable instructions, and the processor is used to execute the computer-executable instructions to implement the method for determining the impact of droplets on a hypersonic wall in a high-water-vapor environment as proposed in the above embodiment.

[0045] The computer device can be a terminal, comprising a processor, memory, communication interface, display screen, and input devices connected via a system bus. The processor provides computing and control capabilities. The memory includes non-volatile storage media and internal memory. The non-volatile storage media stores the operating system and computer programs. The internal memory provides an environment for the operation of the operating system and computer programs stored in the non-volatile storage media. The communication interface is used for wired or wireless communication with external terminals; wireless communication can be achieved through Wi-Fi, carrier networks, NFC (Near Field Communication), or other technologies. The display screen can be an LCD screen or an e-ink screen. The input devices can be a touch layer covering the display screen, buttons, a trackball, or a touchpad on the computer device's casing, or an external keyboard, touchpad, or mouse.

[0046] This embodiment also provides a storage medium storing a computer program. When executed by a processor, the program implements the method for determining droplet impact on a hypersonic wall in a high-water-vapor environment, as proposed in the above embodiments. The storage medium can be implemented by any type of volatile or non-volatile storage device or a combination thereof, such as Static Random Access Memory (SRAM), Electrically Erasable Programmable Read-Only Memory (EEPROM), Erasable Programmable Read-Only Memory (EPROM), Programmable Red-Only Memory (PROM), Read-Only Memory (ROM), magnetic storage, flash memory, magnetic disk, or optical disk.

[0047] In summary, this invention provides fundamental data support for subsequent judgments by acquiring the leading-edge flow field parameters of a hypersonic vehicle and the initial physical parameters of the droplet; it accurately captures the droplet's motion capability before breakup by calculating the droplet's breakup displacement, thus clarifying its range of motion; it determines the limit threshold for the droplet to reach the wall by calculating the maximum geometric distance from the droplet to the wall; and it achieves accurate judgment of whether a droplet will collide by constructing an impact criterion formula and outputting a judgment signal. This invention is suitable for the sea-skimming flight conditions of hypersonic vehicles and can also determine the impact risk boundary to guide flight altitude planning. Overall, it achieves efficient and accurate judgment of droplet impact on hypersonic walls in high-water-vapor environments, ensuring the flight safety of the vehicle.

[0048] It should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit it. Although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications or equivalent substitutions can be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all such modifications or substitutions should be covered within the scope of the claims of the present invention.

Claims

1. A method for determining the impact of droplets on a hypersonic wall in a high-water-vapor environment, characterized in that: include, Acquire the leading-edge flow field parameters and initial physical parameters of the droplets of the hypersonic vehicle; Based on the initial physical parameters of the droplet and the flow field parameters after the shock wave, the breakup displacement that the droplet can move before breaking up and vaporizing is calculated. Based on the flow field parameters at the leading edge of the aircraft, the maximum geometric distance from the droplet to the aircraft wall after passing through the shock wave is calculated. An impact criterion formula is constructed, the breakup displacement is compared with the maximum geometric distance, and a droplet impact determination signal is output based on the comparison result.

2. The method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in claim 1, characterized in that: The acquisition of the leading-edge flow field parameters and initial physical parameters of the droplets of the hypersonic vehicle specifically includes: Obtain the Mach number of the incoming stream gas density before shock wave Droplet density droplet radius The initial height of the droplet above the horizontal plane And the angle θ between the wedge-shaped wall and the horizontal plane; Based on the incoming Mach number Calculate the shock angle of the oblique shock wave by considering the angle θ between the wedge-shaped wall and the horizontal plane. β, and calculate the gas density after the shock wave based on gas dynamics. .

3. The method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in claim 2, characterized in that: The calculation of the droplet's breakage displacement before it breaks up and vaporizes specifically includes: constructing a droplet aerodynamic force model based on droplet density, post-shock gas density, and droplet radius; combining the coupling relationship between droplet surface evaporation rate and aerodynamic breakage in a high-water-vapor environment, solving the droplet's motion path from the moment it passes through the oblique shock wave to the moment it completely breaks up or vaporizes, and setting this motion path as the breakage displacement.

4. The method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in claim 3, characterized in that: The calculation of the maximum geometric distance from the droplet to the spacecraft wall after passing through the shock wave based on the flow field parameters at the leading edge of the spacecraft specifically includes: establishing a two-dimensional geometric position mapping relationship based on the initial height of the droplet, the shock wave angle, and the angle between the wedge wall and the horizontal plane; using a geometric projection algorithm to solve for the shortest straight-line distance from the point where the droplet passes through the oblique shock wave to the wedge wall, and defining the shortest straight-line distance as the maximum geometric distance.

5. The method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in claim 4, characterized in that: The construction of the impact criterion formula and the output of the droplet impact judgment signal based on the comparison results specifically include: setting the impact criterion: if the breakup displacement is greater than or equal to the maximum geometric distance, it is determined that the droplet can impact the wall of the hypersonic vehicle, and an impact judgment valid signal is output; if the breakup displacement is less than the maximum geometric distance, it is determined that the droplet has broken up or vaporized before reaching the wall, and an impact judgment invalid signal is output.

6. The method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in claim 5, characterized in that: The output of the droplet impact determination signal based on the comparison results specifically includes: Real-time acquisition of Weber numbers for droplets of different radii; When the criterion formula Δ≥0 holds, an impact signal is output, and the breakup state of the droplet is determined by combining the Weber number. When the criterion formula Δ<0 is true, a no-collision signal is output, indicating that the droplet has been completely broken up and vaporized before reaching the wall.

7. The method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in claim 6, characterized in that: The method is applied to the sea-skimming flight conditions of hypersonic vehicles. The hypersonic vehicle operates under sea-skimming conditions with an incoming Mach number greater than 5, and the water vapor content in the air surrounding the flight environment increases significantly, with a large number of suspended droplets in the airflow.

8. The method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in claim 6, characterized in that... The method also includes determining the droplet impact risk boundary: Based on the criterion formula, the maximum critical height at which droplets of different radii can impact the wall is calculated under a given working condition. A mapping table between droplet radius and maximum critical altitude was established to guide the safe flight altitude planning of aircraft in high water vapor environments.

9. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that: When the processor executes the computer program, it implements the steps of the method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in any one of claims 1 to 8.

10. A computer-readable storage medium having a computer program stored thereon, characterized in that: When the computer program is executed by the processor, it implements the steps of the method for determining droplet impact on a hypersonic wall in a high-water-vapor environment as described in any one of claims 1 to 8.

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