Test system and method based on electric spark simulation acoustic explosion wave

Abstract

The invention discloses a test system and method based on electric spark simulation acoustic detonation waves, and belongs to the technical field of acoustic detonation wave ground simulation tests. The problem that in the prior art, an acoustic explosion model does not simulate the atmospheric turbulence environment is solved. The turbulence generation system is adjusted to add a disturbance source for a flow field to generate plane jet flow, the hot line measurement system is used for measuring turbulence intensity, the electric spark acoustic explosion source system is used for generating N-type wave signals used for representing typical acoustic explosion characteristics, and the acoustic explosion wave measurement system is used for measuring acoustic explosion wave signals and storing measurement data. According to the ground test simulation system and method, the N-type wave of the far-field acoustic detonation, the atmospheric turbulence and the influence between the N-type wave and the atmospheric turbulence can be completed on the ground, the influence of the atmospheric turbulence on the acoustic detonation can be considered, a ground simulation platform is provided for research on the interaction between the acoustic detonation wave and the atmospheric turbulence, and the prediction precision of the far-field acoustic detonation is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of sonic boom ground simulation tests, and specifically to a test system and method for simulating sonic booms based on electric sparks. Background Technique

[0002] As a core bottleneck technology restricting the development of supersonic civil aircraft, sonic boom has become a key factor limiting its market competitiveness. Therefore, if the sonic boom intensity of the next-generation supersonic civil airliner is to be controlled within an acceptable range, breakthroughs need to be made in low sonic boom configuration design technology and sonic boom characteristic suppression technology.

[0003] Existing sonic boom models mainly include traditional physical models and deep learning-based models. Traditional sonic boom models usually rely on physical laws and mathematical equations to simulate sonic boom phenomena. For example, the augmented Burgers equation is used to solve sonic boom problems, and calculations are carried out through methods such as proper orthogonal decomposition, discrete adjoint, and regularized pseudo-parabolic equations; deep learning models can obtain more accurate results through sonic boom inverse design using deep neural networks (DNNs). The specific method is to invert the near-field waveform through a deep neural network and then obtain the aircraft area distribution through Abel inverse transformation.

[0004] At the same time, sonic boom models also have many limitations. Most of the currently adopted models are based on the assumption of a stationary atmosphere, but the real atmospheric environment inevitably contains non-stationary disturbances such as atmospheric turbulence, which often have a great impact on the propagation of sonic boom signals, resulting in a large deviation between the simulation results and the actual situation. Therefore, there is an urgent need to propose a test system and method for simulating sonic booms based on electric sparks to solve the problem that the sonic boom models in the existing technology do not simulate the atmospheric turbulence environment. Summary of the Invention

[0005] In view of the above facts, the present invention designs a test system and method for simulating sonic booms based on electric sparks in order to solve the problem that the sonic boom models in the existing technology do not simulate the atmospheric turbulence environment.

[0006] To achieve the above object, the present invention adopts the following technical solutions: Solution 1: A test system for simulating sonic booms based on electric sparks, including a turbulence generation system, a hot-wire measurement system, an electric spark sonic boom source system, and a sonic boom wave measurement system; The turbulence generation system includes a jet turbulence agitator, a fan, and a nozzle; The nozzle is installed on the jet turbulence agitator, and the left side of the jet turbulence agitator is connected to the fan through a hose; The hot-wire measurement system includes a hot-wire probe and a hot-wire anemometer; The hot-wire probe is installed on the left side of the hot-wire anemometer. The hot-wire anemometer transmits data to a computer. The hot-wire probe faces the nozzle and maintains a certain distance. The electric spark sonic boom source system includes an electric spark igniter and a parabolic reflector. The parabolic reflector is installed inside the electric spark igniter. The sonic boom wave measurement system includes an optical fiber acoustic probe array, a signal acquisition system, and a computer. The optical fiber acoustic probe array is connected to the signal acquisition system through a cable. The signal acquisition system is connected to the computer through a network cable. The electric spark igniter faces the optical fiber acoustic probe array and maintains a certain distance.

[0007] Solution 2: An experimental method based on simulating sonic booms with electric sparks, which is realized relying on the experimental system of simulating sonic booms with electric sparks described in Solution 1. The operation process is as follows: Step 1: Use the turbulence generation system to simulate different degrees of turbulence intensity, and adjust the flow rate of the fan and the width of the nozzle of the turbulence generation system. Step 2: Use the hot-wire measurement system to measure the turbulence intensity and transmit the data to the computer. Step 3: After determining the turbulence intensity, generate an N-wave signal used to characterize typical sonic boom characteristics with the electric spark sonic boom source system. Step 4: Turn on the turbulence generation system to make the N-wave signal generated by the electric spark sonic boom source system pass through the atmospheric turbulence field, and use the sonic boom wave measurement system to measure the sonic boom wave signal and transmit the data to the computer.

[0008] Furthermore: The fan is driven by a motor to generate flows with different flow rates. The nozzle slides to adjust the opening width. The air flow generated by the fan is blown out from the nozzle through the jet turbulence agitator.

[0009] Furthermore: The hot-wire probe transfers the sensed quantity into the hot-wire anemometer, and a compensation circuit is arranged in the hot-wire anemometer.

[0010] Furthermore: After the electric spark igniter generates a spherical sonic boom wave, it passes through the parabolic reflector, and the waveform is transformed from spherical to planar.

[0011] The beneficial effects of the present invention are as follows: 1. The present invention takes into account the influence of atmospheric turbulence on sonic booms, simulates the propagation of sonic booms in the atmospheric turbulence field, and improves the prediction accuracy of far-field sonic booms.

[0012] 2. The present invention provides a ground simulation platform for the study of the interaction between sonic boom waves and atmospheric turbulence, and provides a pre-test experimental method for the study of the propagation mechanism of sonic boom waves under the influence of atmospheric turbulence.

[0013] 3. The present invention can better understand the behavior of the aircraft under complex airflow conditions, optimize its design and operation parameters, thereby improving its stability and safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is the system schematic diagram of the present invention; Figure 2 is the structural diagram of the turbulence generation system in the present invention; Figure 3 is the structural diagram of the hot-wire measurement system in the present invention; Figure 4 is the structural diagram of the spark discharge sonic boom source system in the present invention; Figure 5 is the structural diagram of the sonic boom wave measurement system in the present invention.

[0015] In the figure: 1 - jet turbulence agitator, 2 - fan, 3 - nozzle, 4 - hot-wire probe, 5 - hot-wire anemometer, 6 - spark discharge igniter, 7 - parabolic reflector, 8 - fiber optic acoustic probe array, 9 - signal acquisition system, 10 - computer, 11 - turbulence generation system, 12 - hot-wire measurement system, 13 - spark discharge sonic boom source system, 14 - sonic boom wave measurement system. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0016] In order to enable those skilled in the art to better understand the solution of the present application, the technical solutions in the embodiments of the present application will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present application.

[0017] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and do not necessarily need to describe a specific order or sequence. It should be understood that such data can be interchanged under appropriate circumstances so as to describe the embodiments of the present application here. In addition, the terms "comprising" and "having" and any variations thereof are intended to cover non-exclusive inclusion. For example, a process, method, system, product or device comprising a series of steps or units does not necessarily have to be limited to those steps or units clearly listed, but may include other steps or units not clearly listed or inherent to these processes, methods, products or devices.

[0018] In this application, the orientation or positional relationship indicated by terms such as "upper", "lower", "inner", "middle", "outer", "front", "rear", etc. is based on the orientation or positional relationship shown in the drawings. These terms are mainly used to better describe this application and its embodiments, and are not used to limit that the indicated device, element or component must have a specific orientation, or be constructed and operated in a specific orientation.

[0019] Moreover, in addition to being able to represent the orientation or positional relationship, some of the above terms may also be used to represent other meanings. For example, the term "upper" may also be used to represent a certain attachment relationship or connection relationship in some cases. For those of ordinary skill in the art, the specific meanings of these terms in this application can be understood according to specific circumstances.

[0020] In addition, the terms "arrangement", "connection", "fixation" should be understood in a broad sense. For example, "connection" can be a fixed connection, a detachable connection, or an integral structure; it can be a mechanical connection or an electrical connection; it can be directly connected, or indirectly connected through an intermediate medium, or there can be internal communication between two devices, elements or components. For those of ordinary skill in the art, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0021] It should be noted that, without conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The following will refer to the drawings and combine with embodiments to detail this application.

[0022] The preferred embodiments of the present invention will be elaborated in detail below according to the drawings.

[0023] Embodiment 1: Refer to Figures 1-5 This embodiment will be described in detail. A test system based on an electric spark-simulated sonic boom wave includes a turbulence generation system 11, a hot-wire measurement system 12, an electric spark sonic boom source system 13, and a sonic boom wave measurement system 14; The turbulence generation system 11 includes a jet turbulence disruptor 1, a fan 2, and a nozzle 3; The nozzle 3 is installed on the jet turbulence disruptor 1, and the left side of the jet turbulence disruptor 1 is connected to the fan 2 through a hose; The hot-wire measurement system 12 includes a hot-wire probe 4 and a hot-wire anemometer 5; The hot-wire probe 4 is installed on the left side of the hot-wire anemometer 5. The hot-wire anemometer 5 transmits data to a computer 10. The hot-wire probe 4 is facing the nozzle 3 and maintains a certain distance, and is used to sense the heat exchange between the filter hot wire and the fluid; The electric spark sonic boom source system 13 includes an electric spark igniter 6 and a parabolic reflector 7; The parabolic reflector 7 is installed inside the electric spark igniter 6; The sonic boom wave measurement system 14 includes an optical fiber acoustic probe array 8, a signal acquisition system 9, and a computer 10; The optical fiber acoustic probe array 8 is connected to the signal acquisition system 9 through a cable, and the signal acquisition system 9 is connected to the computer 10 through a network cable. The electric spark igniter 6 faces the optical fiber acoustic probe array 8 and maintains a certain distance.

[0024] Embodiment 2: A test method based on electric spark simulation of sonic boom waves according to this embodiment is realized relying on the test system based on electric spark simulation of sonic boom waves described in Embodiment 1. The operation process is as follows: Step 1: Use the turbulence generation system 11 to simulate different degrees of turbulence intensity, and adjust the flow rate of the fan 2 and the width of the nozzle 3 of the turbulence generation system. Step 2: Use the hot-wire measurement system 12 to measure the turbulence intensity and transmit the data to the computer 10. Step 3: After the turbulence intensity is determined, generate an N-type wave signal used to characterize typical sonic boom characteristics with the electric spark sonic boom source system 13. Step 4: Turn on the turbulence generation system 11 to make the N-type wave signal generated by the electric spark sonic boom source system 13 pass through the atmospheric turbulence field, and use the sonic boom wave measurement system 14 to measure the sonic boom wave signal and transmit the data to the computer 10.

[0025] More specifically: The fan 2 is driven by a motor to generate flows with different flow rates. The nozzle 3 slides to adjust the opening width. The airflow generated by the fan 2 is blown out from the nozzle 3 through the jet turbulence agitator 1. By comprehensively adjusting the flow rate of the fan 2 and the width of the nozzle 3, the jet turbulence agitator 1 generates plane jets with different intensities to simulate different degrees of turbulence intensity.

[0026] More specifically: The hot-wire probe 4 transfers the sensed quantity to the hot-wire anemometer 5. A compensation circuit is provided in the hot-wire anemometer 5, which can process the sensed quantity of the hot-wire probe 4 to obtain the turbulence intensity of the flow field.

[0027] More specifically: The sonic boom wave generated by the electric spark igniter 6 is a spherical wave, while the characteristics of the sonic boom wave near the ground surface are plane waves. Therefore, after the electric spark igniter 6 generates a spherical sonic boom wave, it passes through the parabolic mirror 7 to convert the waveform from spherical to plane.

[0028] More specifically: The sonic boom wave has high-frequency characteristics, and an optical fiber acoustic probe is used to sense the sonic boom wave signal.

[0029] More specifically: The computer 10 is used to control the signal acquisition system 9 and store the measurement data in real time.

[0030] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, it is still possible to modify the technical solutions described in the foregoing embodiments, or to equivalently replace some or all of the technical features thereof; as long as there is no structural conflict, the various features in the specific embodiments disclosed in this application can be combined with each other in any way, and it will not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the present invention.

[0031] In addition, it should be understood that although this specification is described according to embodiments, not every embodiment only contains an independent technical solution. This narrative way of the specification is only for clarity. Those skilled in the art should regard the specification as a whole, and the technical solutions in each embodiment can also be appropriately combined to form other embodiments that can be understood by those skilled in the art.

Claims

1. A test system based on electric spark simulation of sonic explosion waves, characterized in that: It includes a turbulence generation system (11), a hot wire measurement system (12), an electric spark sonic explosion source system (13), and a sonic explosion wave measurement system (14); The turbulence generating system (11) comprises a jet turbulence disturber (1), a fan (2), and a nozzle (3); The nozzle (3) is mounted on the jet turbulence disruptor (1), and the left side of the jet turbulence disruptor (1) is connected to the fan (2) via a hose; The hot wire measurement system (12) comprises a hot wire probe (4) and a hot wire anemometer (5); The hot wire probe (4) is installed on the left side of the hot wire anemometer (5), the hot wire anemometer (5) transmits data to the computer (10), and the hot wire probe (4) faces the nozzle (3) and maintains a certain distance; The electric spark sonic explosion source system (13) comprises an electric spark igniter (6) and a parabolic reflector (7); The parabolic reflector (7) is installed in the electric spark igniter (6); The sonic boom wave measurement system (14) comprises an optical fiber acoustic probe array (8), a signal acquisition system (9), and a computer (10); The optical fiber acoustic probe array (8) is connected to the signal acquisition system (9) via a cable, the signal acquisition system (9) is connected to the computer (10) via a network cable, and the electric spark igniter (6) faces the optical fiber acoustic probe array (8) and maintains a certain distance therefrom.

2. A test method based on electric spark simulating sonic explosion wave, which is implemented by relying on the test system based on electric spark simulating sonic explosion wave according to claim 1, characterized in that: The operation process is: Step 1: using a turbulence generating system (11) to simulate different degrees of turbulence intensity, and adjusting the flow rate of the fan (2) and the width of the nozzle (3) of the turbulence generating system; Step 2: Using a hot wire measurement system (12) to measure the turbulence intensity, and transmitting the data to a computer (10); Step 3: After the turbulence intensity is measured, an N-type wave signal for characterizing typical sonic boom characteristics is generated by means of an electric spark sonic boom source system (13); Step 4: Turn on the turbulence generation system (11) to allow the N-type wave signal generated by the electric spark sonic boom source system (13) to pass through the atmospheric turbulence field, and use the sonic boom wave measurement system (14) to measure the sonic boom wave signal and transmit the data to the computer (10).

3. A test method based on electric spark simulation of sonic explosion waves according to claim 2, characterized in that: The fan (2) is driven by a motor to generate flows of different flow rates, the nozzle (3) slides to adjust the opening width, and the airflow generated by the fan (2) is blown out from the nozzle (3) through the jet turbulence disruptor (1).

4. The test method based on electric spark simulation of sonic explosion wave according to claim 2 is characterized in that: The hot wire probe (4) transmits the sensed quantity to the hot wire anemometer (5), and a compensation circuit is provided in the hot wire anemometer (5).

5. The test method based on electric spark simulation of sonic explosion wave according to claim 2 is characterized in that: The electric spark igniter (6) generates a spherical sonic explosion wave which then passes through a parabolic reflector (7) to transform the waveform from a spherical shape into a flat shape.

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