Method, storage medium, and electronic device for obtaining a dynamic shock wave angle

Abstract

Methods, storage media, and electronic devices for obtaining dynamic shock angles are disclosed. The methods include: when the rotating inclined plane is at an inclined plane angle, obtaining the gas flow relaxation time based on the rotating inclined plane; wherein the inclined plane angle is the angle between the rotating inclined plane and the reference direction; determining the effective inclined plane angle of the rotating inclined plane in the steady-state flow field corresponding to the inclined plane angle at which the rotating inclined plane is located according to the gas flow relaxation time and the inclined plane rotation angular velocity of the rotating inclined plane; calculating the oblique shock angle of the rotating inclined plane in the steady-state flow field when the rotating inclined plane is at the effective inclined plane angle according to the supersonic oncoming flow parameters, and taking the oblique shock angle as the dynamic shock angle when the rotating inclined plane is at the inclined plane angle. The technical solution provided by the present disclosure is conducive to realizing the rapid and accurate calculation of the dynamic shock angle, thereby significantly reducing the implementation cost of the performance evaluation and safety evaluation of the device where the rotating inclined plane is located.

Description

Technical Field

[0001] The present disclosure relates to the technical field of fluid mechanics, and particularly to a method, a storage medium, and an electronic device for obtaining a dynamic shock wave angle. Background Art

[0002] When an object (such as an aircraft or a missile, etc., an aircraft) moves at supersonic speed in a gas, a shock wave will be generated. A dynamic shock wave refers to a shock wave phenomenon in a compressible fluid where the shock wave characteristics change continuously over time due to various dynamic factors. Here, the shock wave characteristics include the dynamic shock wave angle, etc. The dynamic shock wave angle refers to the angle between the shock wave surface and the oncoming flow direction, and the magnitude of the dynamic shock wave angle will change dynamically over time.

[0003] The dynamic shock wave has a very important impact on the performance and stable operation of the aircraft and its power plant, etc. The dynamic shock wave angle is of great significance for studying the propagation of the dynamic shock wave, the interaction between the shock wave and the object, and the variation law of the flow field, etc. For example, when evaluating the performance and safety of an aircraft and its power plant, the dynamic shock wave angle is often required.

[0004] Currently, usually, experiments or numerical simulations are used to obtain the dynamic shock wave angle. However, the experimental or numerical simulation methods often require a long time and high costs. How to quickly obtain the dynamic shock wave angle is a technical problem worthy of attention. Summary of the Invention

[0005] To solve the above technical problems, the present disclosure is proposed. Embodiments of the present disclosure provide a method, a storage medium, and an electronic device for obtaining a dynamic shock wave angle.

[0006] According to a first aspect of an embodiment of the present disclosure, a method for obtaining a dynamic shock wave angle is provided, including: when a rotating inclined plane is at an inclined plane angle, obtaining the gas flow relaxation time based on the rotating inclined plane; wherein, the inclined plane angle is the angle between the rotating inclined plane and a reference direction; determining the effective inclined plane angle of the rotating inclined plane in a steady-state flow field corresponding to the inclined plane angle of the rotating inclined plane according to the gas flow relaxation time and the inclined plane rotation angular velocity of the rotating inclined plane; calculating the oblique shock wave angle when the rotating inclined plane is at the effective inclined plane angle in the steady-state flow field according to the supersonic oncoming flow parameters, and taking the oblique shock wave angle as the dynamic shock wave angle when the rotating inclined plane is at the inclined plane angle.

[0007] According to a second aspect of an embodiment of the present disclosure, a computer-readable storage medium is provided, and the storage medium stores a computer program, and the computer program is used to implement the above method.

[0008] According to the third aspect of the embodiments of the present disclosure, an electronic device is provided, including: a processor; a memory for storing executable instructions executable by the processor; the processor is configured to read the executable instructions from the memory and execute the instructions to implement the above method.

[0009] Based on a method, a storage medium, and an electronic device for obtaining a dynamic shock wave angle provided by the above embodiments of the present disclosure, by acquiring the gas flow relaxation time, the effective inclined surface angle of the rotating inclined surface in the steady-state flow field corresponding to the inclined surface angle of the rotating inclined surface can be obtained by using the gas flow relaxation time and the angular velocity of the inclined surface rotation of the rotating inclined surface. Since this effective inclined surface angle can reflect the hysteresis situation of the dynamic shock wave, when obtaining the oblique shock wave angle using the steady-state technology, the effective inclined surface angle can be used to replace the inclined surface angle of the rotating inclined surface, that is, the inclined surface angle of the rotating inclined surface can be corrected using the effective inclined surface angle, so that the oblique shock wave angle obtained using the steady-state technology can be used as the dynamic shock wave angle when the rotating inclined surface is at the inclined surface angle; since obtaining the oblique shock wave angle using the steady-state technology is a mature technology, and the effective inclined surface angle obtained by the present disclosure using the gas flow relaxation time and the angular velocity of the inclined surface rotation can accurately reflect the hysteresis situation of the dynamic shock wave, therefore, the finally obtained dynamic shock wave angle of the present disclosure has good accuracy. After simulation verification, the gap between the dynamic shock wave angle obtained by the present disclosure and the simulation result does not exceed 0.2%. It can be seen from this that the technical solution provided by the present disclosure can achieve real-time and accurate calculation of the dynamic shock wave angle, which is beneficial to significantly improving the efficiency of performance evaluation and safety evaluation of the device where the rotating inclined surface is located, and is beneficial to significantly reducing the implementation cost of performance evaluation and safety evaluation of the device where the rotating inclined surface is located.

[0010] The technical solution of the present disclosure will be further described in detail below with reference to the drawings and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] By describing the embodiments of the present disclosure in more detail in conjunction with the drawings, the above and other objects, features, and advantages of the present disclosure will become more obvious. The drawings are used to provide a further understanding of the embodiments of the present disclosure, and constitute a part of the specification, and are used to explain the present disclosure together with the embodiments of the present disclosure, and do not constitute a limitation to the present disclosure. In the drawings, the same reference numerals generally represent the same components or steps.

[0012] Figure 1 It is a schematic diagram of the positional relationship among the dynamic shock wave surface, the steady-state shock wave surface, and the rotating inclined surface of the present disclosure;

[0013] Figure 2 It is a flowchart of an embodiment of the method for obtaining the dynamic shock wave angle of the present disclosure;

[0014] Figure 3 Schematic diagram of the positional relationship between the rotating inclined plane and the dynamic shock wave surface of the present disclosure;

[0015] Figure 4 Schematic diagram of the variation of the angular velocity of the inclined plane rotation of the rotating inclined plane of the present disclosure with time;

[0016] Figure 5 Schematic structural diagram of an embodiment of an apparatus for obtaining the dynamic shock wave angle of the present disclosure;

[0017] Figure 6 It is a structural diagram of an electronic device provided by an exemplary embodiment of the present disclosure. Specific embodiments

[0018] Hereinafter, exemplary embodiments of the present disclosure will be described in detail with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present disclosure, rather than all of the embodiments of the present disclosure. It should be understood that the present disclosure is not limited by the exemplary embodiments described herein.

[0019] It should be noted that: Unless otherwise specifically stated, the relative arrangements of components and steps, numerical expressions and values set forth in these embodiments do not limit the scope of the present disclosure.

[0020] Those skilled in the art can understand that terms such as "first", "second", etc. in the embodiments of the present disclosure are only used to distinguish different steps, devices or modules, etc., and do not represent any specific technical meaning nor indicate an inevitable logical order between them.

[0021] It should also be understood that in the embodiments of the present disclosure, "a plurality" may refer to two or more, and "at least one" may refer to one, two or more.

[0022] It should also be understood that for any component, data or structure mentioned in the embodiments of the present disclosure, unless otherwise clearly defined or given a contrary indication in the context, it is generally understood to be one or more.

[0023] In addition, the term "and / or" in the present disclosure is only a description of the association relationship of associated objects, indicating that there can be three relationships. For example, A and / or B can represent: A exists alone, A and B exist simultaneously, and B exists alone. In addition, the character " / " in the present disclosure generally represents an "or" relationship between the associated objects before and after.

[0024] It should also be understood that the present disclosure emphasizes the differences between the various embodiments, and the same or similar parts thereof can be referred to each other. For the sake of brevity, they will not be repeated one by one.

[0025] Meanwhile, it should be understood that, for the sake of description convenience, the sizes of the various parts shown in the drawings are not drawn in actual proportional relationship.

[0026] The following description of at least one exemplary embodiment is in fact merely illustrative and in no way limits the present disclosure, its application or use.

[0027] Techniques, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, the techniques, methods, and devices should be regarded as part of the specification.

[0028] It should be noted that like reference numerals and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.

[0029] Embodiments of the present disclosure can be applied to electronic devices such as terminal devices, computer systems, servers, etc., which can operate with many other general or special computing system environments or configurations. Examples of well-known terminal devices, computing systems, environments, and / or configurations suitable for use with electronic devices such as terminal devices, computer systems, or servers include, but are not limited to: personal computer systems, server computer systems, thin clients, thick clients, handheld or laptop devices, microprocessor-based systems, set-top boxes, programmable consumer electronics, network personal computers, small computer systems, large computer systems, and distributed cloud computing technology environments including any of the above systems, etc.

[0030] Electronic devices such as terminal devices, computer systems, servers, etc. can be described in the general context of computer system-executable instructions (such as program modules) executed by a computer system. Generally, program modules may include routines, programs, object programs, components, logic, data structures, etc., which perform specific tasks or implement specific abstract data types. The computer system / server can be implemented in a distributed cloud computing environment. In a distributed cloud computing environment, tasks can be executed by remote processing devices linked through a communication network. In a distributed cloud computing environment, program modules can be located on local or remote computing system storage media including storage devices.

[0031] In the process of implementing the present disclosure, the inventors found that currently, by using the simulation method of CFD (Computational Fluid Dynamics), the dynamic shock wave angle can be captured relatively accurately. However, the method of obtaining the dynamic shock wave angle by using the CFD simulation method not only has the problem of high cost, but also has the problem of inability to obtain it in real time. Through the analysis of the CFD simulation results, it can be seen that there are significant differences between the dynamic shock wave and the steady-state shock wave. Therefore, if the calculation principle of the oblique shock wave angle based on the steady state is directly used to calculate the dynamic shock wave angle, the calculation result will have a large deviation from the simulation result, which will have a great impact on the subsequent applications of the dynamic shock wave angle (such as the performance evaluation and safety evaluation of corresponding devices, etc.).

[0032] Through further analysis of the CFD simulation results, it can be seen that the dynamic shock wave has a certain hysteresis characteristic compared with the steady-state shock wave. For example, in a CFD simulation, when the rotating inclined plane rotates counterclockwise to 8° and clockwise to 8° based on a predetermined motion law (such as the angular velocity of the inclined plane rotation varying sinusoidally with time), the dynamic shock wave surfaces obtained respectively are as Figure 1 shown.

[0033] Figure 1 In the figure, both the x coordinate and the y coordinate are spatial position coordinates, and the units of the x coordinate and the y coordinate are both millimeters. The (0, 0) coordinate point in the xy coordinate system is the fixed point of the rotating inclined plane 100, and the rotating inclined plane 100 can rotate counterclockwise upward and clockwise downward around this fixed point. When the rotating inclined plane 100 rotates counterclockwise upward based on a predetermined motion law and rotates to an angle α of 8° with the oncoming flow direction (such as the horizontal oncoming flow direction), the dynamic shock wave surface formed by the rotating inclined plane 100 is as Figure 1 shown by the first dynamic shock wave surface 110 in the figure. When the rotating inclined plane 100 rotates clockwise downward based on a predetermined motion law and rotates to an angle α of 8° with the oncoming flow direction (such as the horizontal oncoming flow direction), the dynamic shock wave surface formed by the rotating inclined plane 100 is as Figure 1 shown by the second dynamic shock wave surface 120 in the figure. Using this simulation, the steady-state shock wave surface when the rotating inclined plane 100 is at an angle α of 8° with the oncoming flow direction (such as the horizontal oncoming flow direction) can also be obtained, that is Figure 1 the steady-state shock wave surface 130 in the figure.

[0034] By comparing the first dynamic shock wave surface 110, the second dynamic shock wave surface 120, and the steady-state shock wave surface 130, it can be seen that when the rotating inclined surface 100 rotates counterclockwise upward to an angle α of 8° with the oncoming flow direction, the dynamic shock wave angle of the formed first dynamic shock wave surface 110 is the smallest, and it is smaller than the steady-state shock wave angle of the steady-state shock wave surface 130 formed when the rotating inclined surface 100 is at an angle α of 8° with the oncoming flow direction. In addition, when the rotating inclined surface 100 rotates clockwise downward to an angle α of 8° with the oncoming flow direction, the dynamic shock wave angle of the formed second dynamic shock wave surface 120 is the largest, and it is larger than the steady-state shock wave angle of the steady-state shock wave surface 130 formed when the rotating inclined surface 100 is at an angle α of 8° with the oncoming flow direction. It can be seen from this that when the rotating inclined surface 100 is at the same inclined surface angle (such as 8°), compared with the steady-state shock wave, the dynamic shock wave has a hysteresis characteristic.

[0035] If the hysteresis characteristic of the dynamic shock wave is used to adjust / correct the inclined surface angle of the rotating inclined surface in the calculation principle of the inclined shock wave angle based on the steady state, and the calculation principle based on the steady state of the inclined shock wave angle is used to calculate based on the adjusted / corrected effective inclined surface angle, then the calculation result can be used as the dynamic shock wave angle of the rotating inclined surface, so that the dynamic shock wave angle of the rotating inclined surface can be calculated conveniently and in real time without the need for simulation. This is of great significance for the performance evaluation and safety assessment of the device where the rotating inclined surface is located.

[0036] The technical solution for obtaining the dynamic shock wave angle of the present disclosure can be applied to a variety of application scenarios. For example, it can be applied to the intake duct design scenarios of flying objects such as supersonic aircraft or missiles. Specifically, assuming that the angle of attack of flying objects such as supersonic aircraft or missiles changes in various ways, the technical solution of the present disclosure can be used to calculate the dynamic shock wave angle for the intake duct, so as to obtain a series of dynamic shock wave angles. By calculating the shock wave intensity for each dynamic shock wave angle respectively, the shock wave intensity corresponding to each different dynamic shock wave angle can be obtained, and the change in the shock wave intensity usually leads to a change in the aerodynamic performance of the intake duct. By evaluating the change in the aerodynamic performance of the intake duct, it helps in the structural design such as the selection of the intake duct configuration. It can be seen from this that the technical solution of the present disclosure is beneficial to providing scientific data support for the design of the intake duct.

[0037] Figure 2 It is a flowchart of an embodiment of the method for obtaining the dynamic shock wave angle of the present disclosure. As Figure 2 shown, the method mainly includes: S200, S201, and S202. The following combines Figure 3 and Figure 4 , and Figure 2 will separately describe each step in

[0038] S200. When the rotating inclined plane is at an inclined plane angle, obtain the gas flow relaxation time based on the rotating inclined plane.

[0039] The rotating inclined plane in the present disclosure can be an inclined plane based on a rotating compression inclined plane model. When the rotating inclined plane rotates, it will not only cause the inclined plane angle to change, but also change the flow direction and velocity of the air flow, thereby generating a shock wave, such as an oblique shock wave, on the rotating inclined plane. Here, the oblique shock wave refers to a shock wave whose shock wave surface forms a certain angle (non-perpendicular angle) with the oncoming flow direction. In addition, some dynamic factors will cause a dynamic shock wave to be generated on the rotating inclined plane. For example, changes in the motion state (such as acceleration, deceleration, or turning, etc.) of a supersonic aircraft during flight will cause the shock wave to change dynamically, thereby forming a dynamic shock wave.

[0040] The inclined plane angle in the present disclosure refers to the included angle between the rotating inclined plane and the oncoming flow direction. The oncoming flow direction can be the horizontal oncoming flow direction, that is, the inclined plane angle can be the included angle between the rotating inclined plane and the horizontal oncoming flow direction. For example, Figure 1 the inclined plane angle α in is the included angle between the rotating inclined plane 100 and the horizontal oncoming flow direction. For another example, Figure 3 the inclined plane angle α in is the included angle between the rotating inclined plane 2 and the horizontal oncoming flow direction. In addition, Figure 3 the rotating inclined plane 2 in is connected to the fixed flat plate 1, and the horizontal oncoming flow direction is the same as the direction of the fixed flat plate 1.

[0041] The rotating inclined plane in the present disclosure being at an inclined plane angle can refer to the included angle between the rotating inclined plane and the reference direction at the current moment during the rotation of the rotating inclined plane, that is, the rotating inclined plane being at an inclined plane angle can be the inclined plane angle of the rotating inclined plane at a certain moment (such as the current moment).

[0042] The gas flow relaxation time based on the rotating inclined plane in the present disclosure refers to the time required for the gas to transition from a non-equilibrium state to an equilibrium state when flowing through the system (such as a channel, etc.) where the rotating inclined plane is located. Since time is usually related to velocity, and the time required to transition from a non-equilibrium state to an equilibrium state is often related to the air flow velocity after the oblique shock wave, therefore, the present disclosure can use the air flow velocity after the oblique shock wave to obtain the gas flow relaxation time based on the rotating inclined plane. Specifically, the air flow velocity after the oblique shock wave when the rotating inclined plane is at the above-mentioned inclined plane angle can be obtained first (for example, by measuring the air flow velocity before the oblique shock wave and calculating the air flow velocity after the oblique shock wave using the air flow velocity before the oblique shock wave). Then, since time is related not only to velocity but also to the length of the flow, the air flow velocity after the oblique shock wave can be calculated using the physical shape parameters of the rotating inclined plane, thereby obtaining the gas flow relaxation time. The air flow velocity after the oblique shock wave here refers to the changed flow velocity of the gas after passing through the oblique shock wave, and the air flow velocity before the oblique shock wave refers to the flow velocity of the gas before encountering the oblique shock wave.

[0043] In one example, the present disclosure can utilize the airflow velocity in front of the oblique shock wave, and the process of obtaining the airflow velocity behind the oblique shock wave can be as follows:

[0044] First, determine the oblique shock wave angle formed by the rotating inclined plane at the above-mentioned inclined plane angle in the steady-state flow field.

[0045] The present disclosure can calculate based on the oblique shock wave angle calculation principle in the steady state, calculate based on the inclined plane angle and the supersonic incoming flow Mach number, and obtain the oblique shock wave angle formed by the rotating inclined plane at the inclined plane angle in the steady-state flow field, that is, the oblique shock wave angle based on the steady-state flow field. Specifically, the present disclosure can calculate and obtain the oblique shock wave angle formed by the rotating inclined plane at the inclined plane angle in the steady-state flow field by using the following formula (1):

[0046] Formula (1)

[0047] In the above formula (1), α is the inclined plane angle of the rotating inclined plane (such as Figure 1 and Figure 3 the included angle α between the rotating inclined plane and the horizontal incoming flow direction), β is the oblique shock wave angle based on the steady-state flow field, M ∞ is the supersonic incoming flow Mach number, and k is the specific heat ratio of the gas. The supersonic incoming flow Mach number can be obtained by measurement. For example, relevant physical quantities related to the incoming flow Mach number are measured by relevant measuring devices, and the incoming flow Mach number is calculated using the measurement results. The present disclosure does not limit the specific method for obtaining the supersonic incoming flow Mach number.

[0048] Secondly, calculate based on the oblique shock wave angle formed by the rotating inclined plane in the steady-state flow field and the airflow velocity in front of the oblique shock wave, so as to obtain the airflow velocity behind the oblique shock wave. Specifically, the present disclosure can calculate and obtain the airflow velocity behind the oblique shock wave by using the following formula (2):

[0049] Formula (2)

[0050] In the above formula (2), α is the inclined plane angle of the rotating inclined plane, β is the oblique shock wave angle based on the steady-state flow field, V 1 is the airflow velocity in front of the oblique shock wave, V 2 and V R are both the airflow velocities behind the oblique shock wave.

[0051] In one example, after the present disclosure obtains the airflow velocity behind the oblique shock wave V R , it can calculate the inclined plane length of the rotating inclined plane and the airflow velocity behind the oblique shock wave V RThe ratio is calculated and used as the gas flow relaxation time. Specifically, the gas flow relaxation time can be obtained by using the following formula (3):

[0052] Δ t = R / V R Formula (3)

[0053] In the above formula (3), R is the slope length of the rotating inclined plane, V R is the airflow velocity after the oblique shock calculated by using the above formula (2), and Δt is the gas flow relaxation time.

[0054] S201. Determine the effective slope angle of the rotating inclined plane in the steady-state flow field corresponding to the slope angle of the rotating inclined plane according to the gas flow relaxation time and the slope rotation angular velocity of the rotating inclined plane.

[0055] Due to the hysteresis characteristic of the dynamic shock, there is a certain correlation between the slope angle of the rotating inclined plane and the effective slope angle of the rotating inclined plane in the steady-state flow field. This correlation is usually determined by the gas flow relaxation time and the slope rotation angular velocity of the rotating inclined plane. Specifically, the present disclosure can use the difference between the slope angle and the product of the gas flow relaxation time and the slope rotation angular velocity of the rotating inclined plane when the rotating inclined plane is at the slope angle as the effective slope angle of the rotating inclined plane in the steady-state flow field, that is, the present disclosure can calculate the effective slope angle by using the following formula (4):

[0056] α' = α – ωΔt Formula (4)

[0057] In the above formula (4), α' is the effective slope angle, α is the slope angle of the rotating inclined plane, ω is the slope rotation angular velocity of the rotating inclined plane, and Δt is the gas flow relaxation time.

[0058] The slope rotation angular velocity ω of the rotating inclined plane in the above formula (4) can be the slope rotation angular velocity of the rotating inclined plane at the current moment. Usually, the slope rotation angular velocity of the rotating inclined plane often conforms to a certain law. For example, the slope rotation angular velocity of the rotating inclined plane changes sinusoidally with time. For another example, the slope rotation angular velocity of the rotating inclined plane changes in the reverse direction with time while maintaining a constant speed. The present disclosure can combine a certain moment (such as the current moment, etc.) with this law to obtain the slope rotation angular velocity of the rotating inclined plane. For example, the corresponding slope rotation angular velocity is found in this law by using the current moment, and the slope rotation angular velocity obtained from this search is used as the slope rotation angular velocity of the rotating inclined plane at this moment (such as the current moment).

[0059] An example where the angular velocity of the rotating inclined plane varies sinusoidally with time and where the angular velocity of the rotating inclined plane remains uniform and varies in the reverse direction with time is as follows Figure 4 as shown.

[0060] Figure 4 In [figure], the abscissa represents time (in milliseconds ms), the ordinate represents the angular velocity of the rotating inclined plane (in degrees / second), and the curve 400 represents the angular velocity of the rotating inclined plane (i.e., ω1) varying sinusoidally with time. That is, at 0 ms, the angular velocity of the rotating inclined plane is 0. From 0 ms to 0.125 ms, the angular velocity of the rotating inclined plane gradually increases and reaches a maximum value of 1.3×10 4 degrees / s at 0.125 ms. From 0.125 ms to 0.25 ms, the angular velocity of the rotating inclined plane gradually decreases and returns to 0 at 0.25 ms. From 0.25 ms to 0.5 ms, the direction of the angular velocity of the rotating inclined plane changes. For example, before 0.25 ms, it is the angular velocity of the inclined plane rotating in the clockwise downward direction (such as Figure 3 the ω of the downward arrow in [figure]), and after 0.25 ms, it changes to the angular velocity of the inclined plane rotating in the counterclockwise upward direction (such as Figure 3 the ω of the upward arrow in [figure]). From 0.25 ms to 0.375 ms, the angular velocity of the rotating inclined plane gradually increases in the current direction and reaches a maximum value of 1.3×10 4 degrees / s in the current direction at 0.375 ms (i.e., Figure 4 -1.3×10 4 degrees / s in [figure]), and from 0.375 ms to 0.5 ms, the angular velocity of the rotating inclined plane gradually decreases in the current direction and returns to 0 at 0.5 ms.

[0061] Figure 4 The ω1 in [figure] can be expressed in the form of the following formula (5):

[0062] Formula (5)

[0063] In the above formula (5), τ0 = 0.5 ms, t is the time, that is, a certain moment between 0 ms and 0.5 ms.

[0064] Figure 4The reverse change broken line 401 in [Figure Name] indicates that the angular velocity of the inclined plane rotation of the rotating inclined plane (i.e., ω2) will change in the reverse direction with time while maintaining a constant speed. That is, from the start at 0 ms to 0.25 ms, the angular velocity of the inclined plane rotation of the rotating inclined plane does not change either in direction or in magnitude, always in the same direction and with a magnitude of 8000 degrees / s. At 0.25 ms, the angular velocity of the inclined plane rotation of the rotating inclined plane changes in direction. From 0.25 ms to 0.5 ms, the angular velocity of the inclined plane rotation of the rotating inclined plane does not change either in direction or in magnitude, always in the same direction and with a magnitude of 8000 degrees / s. That is to say, before 0.25 ms, it is the angular velocity of the inclined plane rotation based on the counterclockwise upward direction (such as Figure 3 the ω of the upward arrow in [Figure Name]. Note: When ω is positive, it corresponds to counterclockwise rotation, and when ω is negative, it corresponds to clockwise rotation), and after 0.25 ms and including 0.25 ms, it changes to the angular velocity of the inclined plane rotation based on the clockwise downward direction (such as Figure 3 the ω of the downward arrow in [Figure Name]). From 0 ms to 0.5 ms, the magnitude of the angular velocity of the inclined plane rotation of the rotating inclined plane does not change, always being 8000 degrees / s.

[0065] Figure 4 The ω2 in [Figure Name] can be expressed in the form of the following formula (6):

[0066] Formula (6)

[0067] In the above formula (6), τ0 = 0.5 ms, t is the time, that is, a certain moment between 0 ms and 0.5 ms.

[0068] In one example, if the angular velocity of the inclined plane rotation of the rotating inclined plane changes according to the Figure 4 curve 400 in [Figure Name], then at any moment between 0 ms and 0.5 ms, the angular velocity of the inclined plane rotation of the rotating inclined plane at the corresponding moment can be obtained using curve 400. And if the angular velocity of the inclined plane rotation of the rotating inclined plane changes according to the Figure 4 broken line 401 in [Figure Name], then at any moment between 0 ms and 0.5 ms, the angular velocity of the inclined plane rotation of the rotating inclined plane at the corresponding moment can be obtained using broken line 401.

[0069] S202. According to the supersonic oncoming flow parameter M ∞ , calculate the oblique shock wave angle of the rotating inclined plane in the steady flow field at the above effective inclined plane angle, and use this oblique shock wave angle as the dynamic shock wave angle of the rotating inclined plane at this inclined plane angle.

[0070] Compared with the steady shock wave, due to the certain hysteresis characteristics of the dynamic shock wave, and the present disclosure obtains the effective inclined plane angle of the rotating inclined plane in the steady flow field, and this effective inclined plane angle effectively compensates for this hysteresis characteristic. Therefore, the present disclosure can calculate the oblique shock wave angle by using this effective inclined plane angle in the steady shock wave environment, and the calculated oblique shock wave angle can be considered as the dynamic shock wave angle when the rotating inclined plane is at the corresponding inclined plane angle. That is to say, the present disclosure can calculate based on the principle of calculating the oblique shock wave angle based on the steady state, based on the effective inclined plane angle and the supersonic oncoming flow Mach number, so as to obtain the oblique shock wave angle formed by the rotating inclined plane at the effective inclined plane angle in the steady flow field, that is, to obtain the dynamic shock wave angle when the rotating inclined plane is at the corresponding inclined plane angle. The present disclosure can substitute the supersonic oncoming flow parameters into the above formula (1), and use the effective inclined plane angle α' as α in the above formula (1), so as to calculate β. In order to distinguish it from the previously calculated β, the β obtained in this calculation can be considered as β´, and this β´ is the finally obtained dynamic shock wave angle when the rotating inclined plane is at the inclined plane angle (such as Figure 1 and Figure 3 in 8 degrees) (such as Figure 3 the included angle β between the dynamic shock wave surface 3 and the horizontal oncoming flow in).

[0071] The present disclosure carried out CFD simulation for the Figure 1 and Figure 3 shown rotating inclined plane. In this simulation, the inclined plane length R of the rotating inclined plane is 32.8 mm, the detected supersonic oncoming flow Mach number M ∞ = 2.5, the detected air flow velocity before the oblique shock wave V 1 = 563 m / s, the inclined plane angle α of the rotating inclined plane is 8°, and the range of change of the inclined plane angle α is 7° to 9°. And the dynamic shock wave angle was calculated by using the calculation method of the present disclosure. During the calculation process, the inclined plane angle α of the rotating inclined plane is 8°, and the calculated air flow velocity V R = 528 m / s, the gas flow relaxation time Δt = 62.2 μs, and the inclined plane rotation angular velocities during the calculation process were obtained by using the curve 400 (i.e., ω1) and the broken line 401 (i.e., ω2) shown in Figure 4 .

[0072] The results of the CFD simulation and the results obtained by the present disclosure are shown in Table 1.

[0073] Table 1

[0074]

[0075] Comparing the simulation results of CFD in Table 1 with the results obtained in this disclosure, it can be seen that the two are highly consistent. If the simulation results of CFD are used as the standard results, the error of the results obtained in this disclosure does not exceed 0.2%, showing good accuracy.

[0076] Exemplary device

[0077] Figure 5 It is a schematic structural diagram of an embodiment of a device for obtaining the dynamic shock wave angle in this disclosure. The device of this embodiment can be used to implement the corresponding method embodiment of this disclosure. As Figure 5 shown, the device includes: a relaxation time acquisition module 500, an effective slope angle acquisition module 510, and a dynamic shock wave angle acquisition module 520. Each module will be described separately below.

[0078] The relaxation time acquisition module 500 is used to acquire the gas flow relaxation time based on the rotating slope when the rotating slope is at a slope angle; the slope angle herein is the included angle between the rotating slope and the reference direction.

[0079] In an example, the relaxation time acquisition module 500 may include: a first unit 501 and a second unit 502. The first unit 501 is used to acquire the airflow velocity behind the oblique shock wave when the rotating slope is at the slope angle. For example, the first unit 501 may first determine the oblique shock wave angle formed by the rotating slope at the slope angle in the steady-state flow field, and then calculate based on the oblique shock wave angle formed by the rotating slope in the steady-state flow field and the airflow velocity before the oblique shock wave to obtain the airflow velocity behind the oblique shock wave. The first unit 501 may calculate based on the calculation principle of the oblique shock wave angle in the steady state, based on the slope angle and the supersonic oncoming Mach number, so as to obtain the oblique shock wave angle formed by the rotating slope at the slope angle in the steady-state flow field. The second unit 502 is used to calculate based on the airflow velocity behind the oblique shock wave obtained by the first unit 501 to obtain the gas flow relaxation time. For example, the second unit 502 may calculate the ratio of the slope length of the rotating slope to the airflow velocity behind the oblique shock wave, and use the ratio as the gas flow relaxation time.

[0080] The effective inclined plane angle obtaining module 510 is configured to determine the effective inclined plane angle of the rotating inclined plane in a steady-state flow field corresponding to the inclined plane angle of the rotating inclined plane according to the gas flow relaxation time obtained by the relaxation time obtaining module 500 and the inclined plane rotation angular velocity of the rotating inclined plane. For example, the effective inclined plane angle obtaining module 510 may use the difference between the inclined plane angle and the product of the gas flow relaxation time and the inclined plane rotation angular velocity when the rotating inclined plane is at the inclined plane angle as the effective inclined plane angle of the rotating inclined plane in the steady-state flow field. The inclined plane rotation angular velocity when the rotating inclined plane is at the inclined plane angle can be obtained in the following two ways:

[0081] Method 1: When the inclined plane rotation angular velocity of the rotating inclined plane varies sinusoidally with time, the effective inclined plane angle obtaining module 510 may use the angular velocity corresponding to the moment when the rotating inclined plane is at the inclined plane angle on the sine variation curve as the inclined plane rotation angular velocity when the rotating inclined plane is at the inclined plane angle.

[0082] Method 2: When the inclined plane rotation angular velocity of the rotating inclined plane varies in the reverse direction with time, the effective inclined plane angle obtaining module 510 may use the angular velocity corresponding to the moment when the rotating inclined plane is at the inclined plane angle on the reverse variation broken line as the inclined plane rotation angular velocity when the rotating inclined plane is at the inclined plane angle.

[0083] The dynamic shock wave angle obtaining module 520 is configured to calculate the oblique shock wave angle of the rotating inclined plane when it is at the effective inclined plane angle in the steady-state flow field according to the supersonic oncoming flow parameters, and use the oblique shock wave angle as the dynamic shock wave angle of the rotating inclined plane when it is at the inclined plane angle. For example, the dynamic shock wave angle obtaining module 520 may calculate based on the effective inclined plane angle and the supersonic oncoming flow Mach number using the calculation principle of the oblique shock wave angle based on the steady state, so as to obtain the oblique shock wave angle formed by the rotating inclined plane at the effective inclined plane angle in the steady-state flow field.

[0084] Exemplary electronic device

[0085] Reference is made below Figure 6 to describe the electronic device according to an embodiment of the present disclosure. Figure 6 FIG. shows a block diagram of an electronic device according to an embodiment of the present disclosure. As Figure 6 shown, the electronic device 61 includes one or more processors 611 and a memory 612.

[0086] The processor 611 may be a central processing unit (CPU) or other form of processing unit having data processing capabilities and / or instruction execution capabilities, and may control other components in the electronic device 61 to perform desired functions.

[0087] The memory 612 may include one or more computer program products, and the computer program products may include various forms of computer-readable storage media, such as volatile memory and / or non-volatile memory. The volatile memory, for example, may include random access memory (RAM) and / or cache memory, etc. The non-volatile memory, for example, may include read-only memory (ROM), hard disk, and flash memory, etc. One or more computer program instructions may be stored on the computer-readable storage media, and the processor 611 may run the program instructions to implement the methods for obtaining the dynamic shock angle in various embodiments of the present disclosure as described above and / or other desired functions.

[0088] In one example, the electronic device 61 may further include an input device 613 and an output device 614, etc., and these components are interconnected through a bus system and / or other forms of connection mechanisms (not shown). In addition, the input device 613 may include, for example, a keyboard, a mouse, etc. The output device 614 may output various information to the outside. The output device 614 may include, for example, a display, a speaker, a printer, and a communication network and its connected remote output devices, etc.

[0089] Of course, for simplicity, Figure 6 only some of the components related to the present disclosure in the electronic device 61 are shown, and components such as buses, input / output interfaces, etc. are omitted. In addition, according to specific application scenarios, the electronic device 61 may further include any other appropriate components.

[0090] Exemplary computer program products and computer-readable storage media

[0091] In addition to the above methods and devices, embodiments of the present disclosure may also be computer program products, which include computer program instructions that, when run by a processor, cause the processor to execute the steps in the methods for obtaining the dynamic shock angle according to various embodiments of the present disclosure described in the "Exemplary Methods" section above of this specification.

[0092] The computer program products may be written in any combination of one or more programming languages to write program codes for performing the operations of the embodiments of the present disclosure. The programming languages include object-oriented programming languages, such as Java, C++, etc., and also include conventional procedural programming languages, such as the "C" language or similar programming languages. The program codes may be executed entirely on the user computing device, partially on the user device, executed as an independent software package, partially on the user computing device and partially on a remote computing device, or entirely on a remote computing device or server.

[0093] In addition, an embodiment of the present disclosure may also be a computer-readable storage medium having computer program instructions stored thereon, and when the computer program instructions are run by a processor, the processor is caused to execute the steps in the method for obtaining a dynamic shock angle according to various embodiments of the present disclosure described in the above "Exemplary Method" section of this specification.

[0094] The computer-readable storage medium may adopt any combination of one or more readable media. The readable media may be a readable signal medium or a readable storage medium. The readable storage medium may include, for example, but is not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the above. More specific examples (non-exhaustive list) of the readable storage medium may include: an electrical connection having one or more wires, a portable disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above.

[0095] The basic principles of the present disclosure have been described above in conjunction with specific embodiments. However, it should be noted that the advantages, benefits, effects, etc. mentioned in the present disclosure are only examples and not limitations, and it cannot be considered that these advantages, benefits, and effects, etc. are essential for each embodiment of the present disclosure. In addition, the above-disclosed specific details are only for the purposes of illustration and facilitating understanding, rather than limitations, and the above details do not limit the present disclosure to necessarily adopt the above specific details for implementation.

[0096] Each embodiment in this specification is described in a progressive manner, and the key point of each embodiment is to illustrate the differences from other embodiments. For the same or similar parts among the embodiments, reference may be made to each other. For system embodiments, since they basically correspond to method embodiments, the description is relatively simple, and reference may be made to the partial description of the method embodiments for relevant parts.

[0097] The block diagrams of the devices, apparatuses, equipment, and systems involved in the present disclosure are only illustrative examples and do not intend to require or imply that they must be connected, arranged, and configured in the manner shown in the block diagrams. As those skilled in the art will recognize, these devices, apparatuses, equipment, and systems can be connected, arranged, and configured in any manner. Words such as "including", "comprising", "having", etc. are open-ended words, meaning "including but not limited to", and can be used interchangeably with each other. The words "or" and "and" used herein refer to the word "and / or" and can be used interchangeably with each other, unless the context clearly indicates otherwise. The word "such as" used herein refers to the phrase "such as but not limited to" and can be used interchangeably with each other.

[0098] The methods and apparatuses of the present disclosure can be implemented in many ways. For example, the methods and apparatuses of the present disclosure can be implemented by software, hardware, firmware, or any combination of software, hardware, and firmware. The above order of the steps for the method is for illustration only, and the steps of the method of the present disclosure are not limited to the specific order described above, unless otherwise specifically stated. In addition, in some embodiments, the present disclosure can also be implemented as a program recorded in a recording medium, and these programs include machine-readable instructions for implementing the method according to the present disclosure. Therefore, the present disclosure also covers a recording medium storing a program for executing the method according to the present disclosure.

[0099] It should also be noted that in the apparatuses, devices, and methods of the present disclosure, each component or each step can be decomposed and / or recombined. These decompositions and / or recombinations should be regarded as equivalent solutions of the present disclosure.

[0100] The above description of the disclosed aspects is provided so that any person skilled in the art can make or use the present disclosure. Various modifications to these aspects are very obvious to those skilled in the art, and the general principles defined herein can be applied to other aspects without departing from the scope of the present disclosure. Therefore, the present disclosure is not intended to be limited to the aspects shown herein, but to the broadest scope consistent with the principles and novel features disclosed herein.

[0101] The above description has been given for purposes of illustration and description. In addition, this description is not intended to limit the embodiments of the present disclosure to the forms disclosed herein. Although multiple example aspects and embodiments have been discussed above, those skilled in the art will recognize certain variations, modifications, changes, additions, and sub-combinations thereof.

Claims

1. A method for obtaining a dynamic shock wave angle, characterized in that, Including: When the rotating inclined plane is at an inclined plane angle, obtaining the gas flow relaxation time based on the rotating inclined plane; wherein, the inclined plane angle is the included angle between the rotating inclined plane and the reference direction; the gas flow relaxation time based on the rotating inclined plane refers to the time required for the gas to transition from a non-equilibrium state to an equilibrium state when flowing through the system where the rotating inclined plane is located; According to the gas flow relaxation time and the angular velocity of the inclined plane rotation of the rotating inclined plane, determining the effective inclined plane angle of the rotating inclined plane in the steady-state flow field corresponding to the inclined plane angle of the rotating inclined plane; wherein, the effective inclined plane angle is used to reflect the hysteresis situation of the dynamic shock wave, and the effective inclined plane angle is obtained by adjusting / correcting the inclined plane angle of the rotating inclined plane in the inclined shock wave angle calculation principle based on the steady state by using the hysteresis characteristics of the dynamic shock wave; According to the supersonic oncoming flow parameters, calculating the inclined shock wave angle when the rotating inclined plane is at the effective inclined plane angle in the steady-state flow field, and taking the inclined shock wave angle as the dynamic shock wave angle when the rotating inclined plane is at the inclined plane angle.

2. The method according to claim 1, wherein The step of, when the rotating inclined plane is at an inclined plane angle, obtaining the gas flow relaxation time based on the rotating inclined plane includes: Obtaining the gas flow velocity behind the inclined shock wave when the rotating inclined plane is at the inclined plane angle; Based on the airflow velocity behind the oblique shock wave, calculations are performed to obtain the gas flow relaxation time 。 3. The method according to claim 2, wherein The step of obtaining the gas flow velocity behind the inclined shock wave when the rotating inclined plane is at the inclined plane angle includes: Determining the inclined shock wave angle formed by the rotating inclined plane at the inclined plane angle in the steady-state flow field; Calculating based on the inclined shock wave angle formed by the rotating inclined plane in the steady-state flow field and the gas flow velocity in front of the inclined shock wave to obtain the gas flow velocity behind the inclined shock wave.

4. The method according to claim 3, characterized in that, The step of determining the inclined shock wave angle formed by the rotating inclined plane at the inclined plane angle in the steady-state flow field includes: Using the inclined shock wave angle calculation principle based on the steady state, calculating based on the inclined plane angle and the supersonic oncoming flow Mach number to obtain the inclined shock wave angle formed by the rotating inclined plane at the inclined plane angle in the steady-state flow field.

5. The method according to claim 2, wherein The step of calculating based on the gas flow velocity behind the inclined shock wave to obtain the gas flow relaxation time includes: Calculate the ratio of the slope length of the rotating inclined plane to the airflow velocity after the oblique shock wave, and use this ratio as the gas flow relaxation time 。 6. The method according to any one of claims 1 to 5, characterized in that The step of, according to the gas flow relaxation time and the angular velocity of the inclined plane rotation of the rotating inclined plane, determining the effective inclined plane angle of the rotating inclined plane in the steady-state flow field corresponding to the inclined plane angle of the rotating inclined plane includes: Taking the difference between the inclined plane angle and the product of the gas flow relaxation time and the angular velocity of the inclined plane rotation when the rotating inclined plane is at the inclined plane angle as the effective inclined plane angle of the rotating inclined plane in the steady-state flow field.

7. The method according to claim 6, characterized in that The angular velocity of the inclined plane rotation when the rotating inclined plane is at the inclined plane angle includes: When the angular velocity of the inclined plane rotation of the rotating inclined plane varies sinusoidally with time, the angular velocity corresponding to the moment when the rotating inclined plane is at the inclined plane angle on the sine variation curve is taken as the angular velocity of the inclined plane rotation when the rotating inclined plane is at the inclined plane angle; or When the angular velocity of the rotating inclined plane changes in the reverse direction with time, the angular velocity corresponding to the moment when the rotating inclined plane is at the inclined plane angle on the reverse change broken line is taken as the angular velocity of the rotating inclined plane when it is at the inclined plane angle.

8. The method according to any one of claims 1 to 5, characterized in that, Calculating the oblique shock wave angle when the rotating inclined plane is at the effective inclined plane angle in the steady flow field according to the supersonic oncoming flow parameters includes: Using the calculation principle of the oblique shock wave angle based on the steady state, calculating based on the effective inclined plane angle and the supersonic oncoming flow Mach number to obtain the oblique shock wave angle formed by the rotating inclined plane at the effective inclined plane angle in the steady flow field.

9. A computer-readable storage medium storing a computer program for executing the method according to any one of claims 1-8 above.

10. An electronic device, comprising: a processor; a memory for storing executable instructions executable by the processor; The processor is configured to read the executable instructions from the memory and execute the instructions to implement the method according to any one of claims 1-8 above.

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