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

Abstract

The invention discloses a method for obtaining a dynamic shock wave angle, a storage medium and electronic equipment, and the method comprises the steps: obtaining the gas through-flow relaxation time based on a rotating inclined plane when the rotating inclined plane is at an inclined plane angle; wherein the inclined plane angle is an included angle between the rotating inclined plane and the reference direction; according to the gas through-flow relaxation time and the inclined plane rotation angular velocity of the rotation inclined plane, determining an effective inclined plane angle of the rotation inclined plane corresponding to the inclined plane angle where the rotation inclined plane is located in a steady-state flow field; and according to supersonic incoming flow parameters, calculating an oblique shock wave angle when the rotating inclined plane is at the effective inclined plane angle in the steady-state flow field, and taking the oblique shock wave angle as a dynamic shock wave angle when the rotating inclined plane is at the inclined plane angle. According to the technical scheme provided by the invention, the dynamic shock wave angle can be quickly and accurately calculated, so that the implementation cost of performance evaluation and safety evaluation of the device where the rotating inclined plane is located can be remarkably reduced.

Description

Technical Field

[0001] The present disclosure relates to the technical field of fluid mechanics, and in particular, 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, and a dynamic shock wave refers to a shock wave phenomenon in a compressible fluid, where the shock wave characteristics change continuously with 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 with 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 cost. 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 the rotating inclined plane is at an inclined plane angle, obtaining the gas flow relaxation time based on the rotating inclined plane; where 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 wave 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 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, where the storage medium stores a computer program, and the computer program is used to implement the above method.

[0008] According to a 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 obtaining 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 the 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 by using the effective inclined surface angle, so that the oblique shock wave angle obtained by 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 level, 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 realize 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. Together with the embodiments of the present disclosure, they are used to explain 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; Figure 2 It is a flowchart of an embodiment of the method for obtaining the dynamic shock wave angle of the present disclosure; Figure 3Schematic diagram of the positional relationship between the rotating inclined plane and the dynamic shock wave surface of the present disclosure; Figure 4 Schematic diagram of the change of the angular velocity of the inclined plane rotation of the rotating inclined plane of the present disclosure over time; Figure 5 Schematic structural diagram of an embodiment of a device for obtaining the dynamic shock wave angle of the present disclosure; Figure 6 Structural diagram of an electronic device provided by an exemplary embodiment of the present disclosure. Detailed implementation manners

[0013] Hereinafter, exemplary embodiments according to 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 embodiments of the present disclosure. It should be understood that the present disclosure is not limited by the exemplary embodiments described herein.

[0014] It should be noted that: Unless otherwise specifically stated, the relative arrangements, numerical expressions, and numerical values of the components and steps set forth in these embodiments do not limit the scope of the present disclosure.

[0015] Those skilled in the art can understand that terms such as "first" and "second" in the embodiments of the present disclosure are only used to distinguish different steps, devices, or modules, etc., and neither represent any specific technical meaning nor indicate an inevitable logical order between them.

[0016] 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.

[0017] It should also be understood that for any component, data, or structure mentioned in the embodiments of the present disclosure, without clear limitation or contrary indication in the context, it is generally understood as one or more.

[0018] 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.

[0019] It should also be understood that the present disclosure emphasizes the differences between the various embodiments. Their similarities or similarities can be referred to each other. For the sake of brevity, they will not be described one by one.

[0020] At the same time, it should be understood that for the sake of description, the dimensions of the various parts shown in the drawings are not drawn according to the actual proportional relationship.

[0021] The following description of at least one exemplary embodiment is merely illustrative and is in no way a limitation on the disclosure, its application, or its use.

[0022] Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, such technologies, methods, and devices should be considered as part of the specification.

[0023] 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.

[0024] 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, minicomputer systems, mainframe computer systems, and distributed cloud computing technology environments including any of the above systems, and so on.

[0025] 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 can 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.

[0026] 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 not being able to obtain it in real time. By analyzing 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.).

[0027] By further analyzing 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 varies sinusoidally with time), the obtained dynamic shock wave surfaces are as follows Figure 1 shown.

[0028] 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 shown in Figure 1 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 shown in Figure 1 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.

[0029] 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 plane 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 plane 100 is at an angle α of 8° with the oncoming flow direction. In addition, when the rotating inclined plane 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 plane 100 is at an angle α of 8° with the oncoming flow direction. From this, it can be known that when the rotating inclined plane 100 is at the same inclined plane angle (such as 8°), compared with the steady-state shock wave, the dynamic shock wave has a hysteresis characteristic.

[0030] If the inclined plane angle of the rotating inclined plane in the calculation principle of the oblique shock wave angle based on the steady state is adjusted / corrected by using the hysteresis characteristic of the dynamic shock wave, and the calculation is carried out based on the adjusted / corrected effective inclined plane angle by using the calculation principle of the oblique shock wave angle based on the steady state, then the calculation result can be used as the dynamic shock wave angle of the rotating inclined plane, so that the dynamic shock wave angle of the rotating inclined plane can be calculated conveniently and in real time without the need for simulation. This is of great significance for the performance evaluation and safety evaluation of the device where the rotating inclined plane is located.

[0031] 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 inlet design scenario 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 inlet, 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 of the shock wave intensity usually leads to the change of the aerodynamic performance of the inlet. By evaluating the change of the aerodynamic performance of the inlet, it is helpful for the structural design such as the selection of the inlet configuration. From this, it can be known that the technical solution of the present disclosure is beneficial to providing scientific data support for the design of the inlet.

[0032] 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 will combine Figure 3 and Figure 4 , and Figure 2 will explain each step in

[0033] S200. When the rotating inclined plane is at an inclined plane angle, obtain the gas flow relaxation time based on the rotating inclined plane.

[0034] 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.

[0035] 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.

[0036] 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).

[0037] 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 path, 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.

[0038] In one example, the present disclosure can utilize the air flow velocity in front of the oblique shock wave, and the process of obtaining the air flow velocity behind the oblique shock wave can be as follows: 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.

[0039] The present disclosure can utilize the calculation principle of the oblique shock wave angle based on the steady state, and calculate based on the inclined plane angle and the supersonic oncoming Mach number to 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): Formula (1) 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 oncoming flow direction in ∞ ), β is the oblique shock wave angle based on the steady-state flow field, M

[0040] is the supersonic oncoming Mach number, and k is the specific heat ratio of the gas. The supersonic oncoming Mach number can be obtained by measurement. For example, relevant physical quantities related to the oncoming Mach number are measured by relevant measuring devices, and the oncoming Mach number is calculated using the measurement results. The present disclosure does not limit the specific manner of obtaining the supersonic oncoming Mach number. Formula (2) 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 air flow velocity in front of the oblique shock wave, V 2 and V R are both the air flow velocities behind the oblique shock wave.

[0041] In one example, after the present disclosure obtains the air flow velocity V R behind the oblique shock wave, the ratio of the inclined plane length of the rotating inclined plane and the air flow velocity V R behind the oblique shock wave can be calculated, and this ratio is used as the gas flow-through relaxation time. Specifically, the gas flow-through relaxation time can be calculated using the following formula (3): Δt = R / V R Formula (3) In the above formula (3), R is the inclined plane length of the rotating inclined plane, V R is the airflow velocity after the oblique shock calculated using the above formula (2), and Δt is the gas flow relaxation time.

[0042] S201. Determine 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 according to the gas flow relaxation time and the inclined plane rotation angular velocity of the rotating inclined plane.

[0043] Due to the hysteresis characteristic of the dynamic shock wave, there is a certain correlation between the inclined plane angle of the rotating inclined plane and the effective inclined plane 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 inclined plane rotation angular velocity of the rotating inclined plane. Specifically, the present disclosure can 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. That is, the present disclosure can calculate and obtain the effective inclined plane angle using the following formula (4): α' = α – ωΔt Formula (4) In the above formula (4), α' is the effective inclined plane angle, α is the inclined plane angle of the rotating inclined plane, ω is the inclined plane rotation angular velocity of the rotating inclined plane, and Δt is the gas flow relaxation time.

[0044] The inclined plane rotation angular velocity ω of the rotating inclined plane in the above formula (4) can be the inclined plane rotation angular velocity of the rotating inclined plane at the current moment. Usually, the inclined plane rotation angular velocity of the rotating inclined plane often conforms to a certain law. For example, the inclined plane rotation angular velocity of the rotating inclined plane changes sinusoidally with time. Another example is that the inclined plane 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 inclined plane rotation angular velocity of the rotating inclined plane. For example, find the corresponding inclined plane rotation angular velocity in this law using the current moment, and use the inclined plane rotation angular velocity obtained from this search as the inclined plane rotation angular velocity of the rotating inclined plane at this moment (such as the current moment).

[0045] An example of the inclined plane rotation angular velocity of the rotating inclined plane changing sinusoidally with time and the inclined plane rotation angular velocity of the rotating inclined plane maintaining a constant speed and changing in the reverse direction with time is as Figure 4 shown.

[0046] Figure 4In it, the abscissa represents time (unit: millisecond, ms), the ordinate represents the angular velocity of the rotating inclined plane (unit: degree / second), and the curve 400 represents that the angular velocity of the rotating inclined plane (i.e., ω1) varies sinusoidally with time. That is, at the 0th 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 at 0.125 ms, the angular velocity of the rotating inclined plane reaches the maximum value of 1.3×10 4 degrees / s. From 0.125 ms to 0.25 ms, the angular velocity of the rotating inclined plane gradually decreases, and at 0.25 ms, the angular velocity of the rotating inclined plane returns to 0. 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 rotating inclined plane based on the clockwise downward direction (such as Figure 3 the ω of the downward arrow in), and after 0.25 ms, it changes to the angular velocity of the rotating inclined plane based on the counterclockwise upward direction (such as Figure 3 the ω of the upward arrow in). From 0.25 ms to 0.375 ms, the angular velocity of the rotating inclined plane gradually increases in the current direction, and at 0.375 ms, the angular velocity of the rotating inclined plane reaches the maximum value of 1.3×10 4 degrees / s in the current direction (i.e., Figure 4 -1.3×10 4 degrees / s in). From 0.375 ms to 0.5 ms, the angular velocity of the rotating inclined plane gradually decreases in the current direction, and at 0.5 ms, the angular velocity of the rotating inclined plane returns to 0.

[0047] Figure 4 The ω1 in can be expressed in the form of the following formula (5): Formula (5) In the above formula (5), τ 0 = 0.5 ms, t is time, that is, a certain moment from 0 ms to 0.5 ms.

[0048] Figure 4The reverse change broken line 401 therein 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 3 , 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 at 0.25 ms, it changes to the angular velocity of the inclined plane rotation based on the clockwise downward direction (such as

[0049] Figure 4 the ω of the downward arrow in ). From the start at 0 ms to 0.5 ms, the magnitude of the angular velocity of the inclined plane rotation of the rotating inclined plane has not changed, always being 8000 degrees / s. In the above formula (6), τ 0 = 0.5 ms, t is the time, that is, a certain moment from 0 ms to 0.5 ms.

[0050] In an 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 4 , then at any moment from 0 ms to 0.5 ms, the angular velocity of the inclined plane rotation of the rotating inclined plane at the corresponding moment can be obtained by using curve 400. And if the angular velocity of the inclined plane rotation of the rotating inclined plane changes according to the

[0051] broken line 401 in ∞ , then at any moment from 0 ms to 0.5 ms, the angular velocity of the inclined plane rotation of the rotating inclined plane at the corresponding moment can be obtained by using broken line 401.

[0052] 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 makes up for this hysteresis characteristic. Therefore, in the steady shock wave environment, the present disclosure can use this effective inclined plane angle to calculate the oblique shock wave angle, 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 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 such as 8 degrees in Figure 3 such as the included angle β between the dynamic shock wave surface 3 and the horizontal oncoming flow in

[0053] The present disclosure conducts 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 Mach number M ∞ = 2.5, the detected air flow velocity V 1 before the oblique shock wave is 563 m / s, the inclined plane angle α of the rotating inclined plane is 8°, and the range of variation of the inclined plane angle α is 7° to 9°. And the dynamic shock wave angle is 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 after the oblique shock wave is 528 m / s, the gas flow relaxation time Δt = 62.2 μs, and the inclined plane rotation angular velocities during the calculation process are obtained by using the curve 400 (i.e., ω1) and the broken line 401 (i.e., ω2) shown in Figure 4 respectively.

[0054] The results of the CFD simulation and the results obtained by the present disclosure are shown in Table 1.

[0055] Table 1

[0056] 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 better accuracy.

[0057] Exemplary device Figure 5 FIG. is a schematic structural diagram of an embodiment of a device for obtaining a dynamic shock wave angle according to 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.

[0058] The relaxation time acquisition module 500 is configured to obtain the gas flow relaxation time based on the rotating slope when the rotating slope is at a slope angle; the slope angle is the included angle between the rotating slope and the reference direction.

[0059] In one example, the relaxation time acquisition module 500 may include: a first unit 501 and a second unit 502. The first unit 501 is configured to obtain 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 use the calculation principle of the oblique shock wave angle based on the steady state to calculate based on the slope angle and the supersonic incoming 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 configured 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.

[0060] The effective inclined plane angle acquisition 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 at which the rotating inclined plane is located according to the gas flow relaxation time obtained by the relaxation time acquisition module 500 and the inclined plane rotation angular velocity of the rotating inclined plane. For example, the effective inclined plane angle acquisition 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: In the first way, when the inclined plane rotation angular velocity of the rotating inclined plane varies sinusoidally with time, the effective inclined plane angle acquisition 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.

[0061] In the second way, when the inclined plane rotation angular velocity of the rotating inclined plane varies in the reverse direction with time, the effective inclined plane angle acquisition 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.

[0062] The dynamic shock wave angle acquisition module 520 is configured to calculate the oblique shock wave 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 use the oblique shock wave angle as the dynamic shock wave angle when the rotating inclined plane is at the inclined plane angle. For example, the dynamic shock wave angle acquisition module 520 may perform calculations 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.

[0063] Exemplary electronic device The following refers to Figure 6 to describe the electronic device according to an embodiment of the present disclosure. Figure 6 The block diagram of the electronic device according to an embodiment of the present disclosure is shown. As Figure 6 shown, the electronic device 61 includes one or more processors 611 and a memory 612.

[0064] The processor 611 may be a central processing unit (CPU) or other form of processing unit with data processing capabilities and / or instruction execution capabilities, and may control other components in the electronic device 61 to perform desired functions.

[0065] 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 method for obtaining the dynamic shock angle and / or other desired functions of the various embodiments of the present disclosure described above.

[0066] 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.

[0067] 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.

[0068] Exemplary computer program products and computer-readable storage media In addition to the above methods and devices, the 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 method for obtaining the dynamic shock angle according to various embodiments of the present disclosure described in the "Exemplary Method" section above of this specification.

[0069] 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.

[0070] 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 "Exemplary Method" section above of this specification.

[0071] 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, for example, include 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 listing) 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 disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the above.

[0072] 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 implement using the above specific details.

[0073] Each embodiment in this specification is described in a progressive manner. 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, they are described relatively simply, and for the relevant parts, reference may be made to the partial description of the method embodiments.

[0074] 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 word "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.

[0075] The methods and apparatuses of the present disclosure may be implemented in many ways. For example, the methods and apparatuses of the present disclosure may be implemented by software, hardware, firmware, or any combination of software, hardware, and firmware. The above order of steps for the methods is for illustration only. The steps of the methods 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 may also be implemented as a program recorded in a recording medium, and these programs include machine-readable instructions for implementing the methods according to the present disclosure. Thus, the present disclosure also covers a recording medium storing a program for executing the methods according to the present disclosure.

[0076] 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.

[0077] The above description of the disclosed aspects is provided to enable any person skilled in the art to make or use the present disclosure. Various modifications etc. to these aspects will be readily apparent 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 is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

[0078] The above description has been presented 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, alterations, additions, and sub-combinations thereof.

Claims

1. A method for obtaining a dynamic shock wave angle, characterized in that: include: When the rotating inclined plane is at an inclined plane angle, obtaining a gas flow relaxation time based on the rotating inclined plane; wherein the inclined plane angle is an angle between the rotating inclined plane and a reference direction; Determining, according to the gas flow relaxation time and the inclined plane rotation angular velocity of the rotating inclined plane, an effective inclined plane angle of the rotating inclined plane in a steady-state flow field corresponding to the inclined plane angle at which the rotating inclined plane is located; According to the supersonic incoming flow parameters, the oblique shock wave angle when the rotating inclined plane is at the effective inclined plane angle in the steady-state flow field is calculated, and the oblique shock wave angle is used as the dynamic shock wave angle when the rotating inclined plane is at the inclined plane angle.

2. The method according to claim 1, characterized in that The step of obtaining the gas flow relaxation time based on the rotating inclined plane when the rotating inclined plane is at an inclined plane angle comprises: acquiring the airflow velocity after the oblique shock wave when the rotating inclined plane is at the inclined plane angle; The gas flow relaxation time is obtained by calculating the air flow velocity after the oblique shock wave. 。 3. The method according to claim 2, characterized in that The obtaining of the airflow velocity after the oblique shock wave when the rotating inclined plane is at the inclined plane angle comprises: determining an oblique shock wave angle formed by a rotating inclined plane at the inclined plane angle in a steady-state flow field; The airflow velocity behind the oblique shock wave is obtained by performing calculation based on the angle of the oblique shock wave formed by the rotating inclined plane in the steady-state flow field and the airflow velocity before the oblique shock wave.

4. The method according to claim 3, characterized in that The step of determining the angle of the oblique shock wave formed by the rotating inclined plane at the inclined plane angle in the steady-state flow field comprises: The oblique shock wave angle calculation principle based on steady state is utilized, and the calculation is performed based on the inclined plane angle and the supersonic incoming flow Mach number to obtain the oblique 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, characterized in that: The calculating based on the airflow velocity after the oblique shock wave to obtain the gas flow relaxation time includes: Calculate the ratio of the inclined plane length of the rotating inclined plane to the airflow velocity after the oblique shock wave, and use the ratio as the gas flow relaxation time 。 6. The method according to any one of claims 1 to 5, characterized in that: Determining the effective slope angle of the rotating slope in the steady-state flow field corresponding to the slope angle of the rotating slope according to the gas flow relaxation time and the slope rotation angular velocity of the rotating slope comprises: The difference between the slope angle and the product of the gas flow relaxation time and the slope rotation angular velocity when the rotating slope is at the slope angle is taken as the effective slope angle of the rotating slope in the steady-state flow field.

7. The method according to claim 6, characterized in that The inclined plane rotation angular velocity when the rotating inclined plane is at the inclined plane angle includes: In the case where the inclined plane rotation angular velocity of the rotating inclined plane changes sinusoidally with time, the angular velocity corresponding to the moment when the rotating inclined plane is at the inclined plane angle on the sinusoidal variation curve is taken as the inclined plane rotation angular velocity when the rotating inclined plane is at the inclined plane angle; or When the angular velocity of the rotating inclined plane changes inversely with time, the angular velocity corresponding to the reverse change curve when the rotating inclined plane is at the inclined plane angle is taken as the angular velocity of the rotating inclined plane when the rotating inclined plane is at the inclined plane angle.

8. The method according to any one of claims 1 to 5, characterized in that: The step of calculating the oblique shock wave angle of the rotating inclined plane when the rotating inclined plane is at the effective inclined plane angle in the steady-state flow field according to the supersonic incoming flow parameters comprises: The oblique shock wave angle calculation principle based on steady state is utilized, and the calculation is performed based on the effective inclined plane angle and the supersonic incoming 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 state flow field.

9. A computer-readable storage medium storing a computer program, wherein the computer program is used to execute the method according to any one of claims 1 to 8.

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

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