A test system and method for simulating sonic explosion waves based on electric sparks

Abstract

A test system and method for simulating sonic boom waves based on electric sparks belongs to the technical field of ground simulation tests of sonic boom waves. It solves the problem in the prior art that sonic boom models do not simulate the atmospheric turbulence environment. By adjusting the turbulence generation system, a disturbance source is added to the flow field to generate a plane jet, the turbulence intensity is measured using a hot wire measurement system, and an N-type wave signal used to characterize typical sonic boom characteristics is generated with the help of an electric spark sonic boom source system. The sonic boom wave measurement system is used to measure the sonic boom wave signal and store the measurement data. The present invention is a ground test simulation system and method that can complete N-type waves, atmospheric turbulence, and the influence between the two of far-field sonic booms on the ground. It can take into account the influence of atmospheric turbulence on sonic booms, provide a ground simulation platform for the study of the interaction between sonic boom waves and atmospheric turbulence, and improve the prediction accuracy of far-field sonic booms.

Description

Technical Field

[0001] The present invention relates to the technical field of sonic boom wave ground simulation tests, and in particular to a test system and method for simulating sonic boom waves based on electric sparks. Background Art

[0002] Sonic boom, as the core bottleneck technology restricting the development of supersonic civil aircraft, has become a key factor limiting its market competitiveness. Therefore, if we want to control the sonic boom intensity of the next generation of supersonic civil airliners within an acceptable range, we need to make breakthroughs in low sonic boom configuration design technology and sonic boom characteristic suppression technology.

[0003] Existing sonic boom models primarily include traditional physical models and deep learning-based models. Traditional sonic boom models typically rely on physical laws and mathematical equations to simulate the phenomenon. For example, the augmented Burgers equation is used to solve the sonic boom problem, and calculations are performed using methods such as proper orthogonal decomposition, discrete adjoints, and regularized pseudoparabolic equations. Deep learning models, using deep neural networks (DNNs) for sonic boom inverse design, can achieve more accurate results. Specifically, the DNN inverts the near-field waveform and then uses the inverse Abel transform to obtain the aircraft area distribution.

[0004] At the same time, sonic boom models also have many limitations. Currently used models mostly assume a stationary atmosphere, but the real atmospheric environment inevitably contains non-stationary disturbances such as atmospheric turbulence. These disturbances 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.

[0005] Therefore, it is urgent to propose a test system and method based on electric spark simulation of sonic boom waves to solve the problem that the sonic boom model in the existing technology does not simulate the atmospheric turbulence environment. Summary of the Invention

[0006] In view of the above facts, in order to solve the problem that the sonic boom model in the prior art fails to simulate the atmospheric turbulence environment, the present invention further designs a test system and method for simulating sonic boom waves based on electric sparks.

[0007] To achieve the above object, the present invention adopts the following technical solutions:

[0008] Solution 1: A test system based on electric spark sonic boom simulation, including a turbulence generation system, a hot wire measurement system, an electric spark sonic boom source system, and a sonic boom wave measurement system;

[0009] The turbulence generating system includes a jet turbulence disruptor, a fan, and a nozzle;

[0010] The nozzle is mounted on a jet turbulence disruptor, and the left side of the jet turbulence disruptor is connected to a fan via a hose;

[0011] The hot wire measurement system includes a hot wire probe and a hot wire anemometer;

[0012] The hot wire probe is installed on the left side of the hot wire anemometer, and the hot wire anemometer transmits data to the computer. The hot wire probe faces the nozzle and maintains a certain distance;

[0013] The electric spark sonic explosion source system includes an electric spark igniter and a parabolic reflector;

[0014] The parabolic reflector is installed in the electric spark igniter;

[0015] The sonic boom wave measurement system includes an optical fiber acoustic probe array, a signal acquisition system, and a computer;

[0016] 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, and the electric spark igniter faces the optical fiber acoustic probe array and maintains a certain distance.

[0017] Solution 2: A test method based on electric spark simulating sonic boom waves, which is implemented based on the test system based on electric spark simulating sonic boom waves described in Solution 1. The operation process is as follows:

[0018] 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;

[0019] Step 2: Use the hot wire measurement system to measure the turbulence intensity and transmit the data to the computer;

[0020] Step 3: After the turbulence intensity is measured, an N-type wave signal is generated using an electric spark sonic boom source system to characterize typical sonic boom characteristics;

[0021] Step 4: Turn on the turbulence generation system to allow the N-type wave signal generated by the electric spark sonic boom source system to 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.

[0022] Furthermore: the fan is driven by a motor to generate flows with different flow rates, the nozzle slides to adjust the opening width, and the airflow generated by the fan is blown out from the nozzle through the jet turbulence disruptor.

[0023] Furthermore, the hot wire probe transmits the sensed quantity to the hot wire anemometer, and the hot wire anemometer is provided with a compensation circuit.

[0024] Furthermore, the electric spark igniter generates a spherical sonic explosion wave which passes through a parabolic reflector to transform the waveform from a spherical shape into a flat shape.

[0025] The beneficial effects of the present invention are:

[0026] 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.

[0027] 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 predictive test method for the study of the propagation mechanism of sonic boom waves under the influence of atmospheric turbulence.

[0028] 3. The present invention can better understand the behavior of aircraft under complex airflow conditions, optimize their design and operating parameters, and thus improve their stability and safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 It is the system principle diagram of the present invention;

[0030] Figure 2 It is a structural diagram of the turbulence generating system in the present invention;

[0031] Figure 3 It is a structural diagram of the hot wire measurement system of the present invention;

[0032] Figure 4 It is a structural diagram of the electric spark sonic explosion source system of the present invention;

[0033] Figure 5 This is a structural diagram of the sonic boom wave measurement system of the present invention.

[0034] In the figure: 1-jet turbulence disruptor, 2-fan, 3-nozzle, 4-hot wire probe, 5-hot wire anemometer, 6-electric spark 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-electric spark sonic boom source system, 14-sonic boom wave measurement system. DETAILED DESCRIPTION

[0035] In order to enable those skilled in the art to better understand the present invention, the following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts should fall within the scope of protection of this application.

[0036] 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 are not necessarily used to describe a specific order or sequential order. It should be understood that the data used in this way can be interchanged where appropriate, so that the embodiments of the present application described here. In addition, the terms "including" and "having" and any variations thereof are intended to cover non-exclusive inclusions, for example, a process, method, system, product or device that includes a series of steps or units is not necessarily limited to those steps or units clearly listed, but may include other steps or units that are not clearly listed or inherent to these processes, methods, products or devices.

[0037] In this application, terms such as "upper," "lower," "inner," "middle," "outer," "front," and "back" indicate positions or locations based on the positions or locations shown in the accompanying drawings. These terms are primarily intended to better describe this application and its embodiments and are not intended to limit the devices, elements, or components indicated to having a specific orientation, or to being constructed or operated in a specific orientation.

[0038] Furthermore, some of the above terms may be used to express other meanings besides indicating a position or location. For example, the term "on" may also be used to indicate a dependency or connection in certain circumstances. Those skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances.

[0039] Furthermore, the terms "disposed," "connected," and "fixed" should be interpreted broadly. For example, "connected" can mean a fixed connection, a removable connection, or an integral structure; it can be a mechanical connection or an electrical connection; it can be a direct connection, an indirect connection through an intermediary, or an internal communication between two devices, elements, or components. Those skilled in the art will understand the specific meanings of these terms in this application based on the specific circumstances.

[0040] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments in this application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0041] Preferred embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0042] Example 1: Reference Figure 1-Figure 5 Detailed description of this embodiment, a test system based on electric spark simulating sonic boom wave, comprising a turbulence generating system 11, a hot wire measuring system 12, an electric spark sonic boom source system 13, and a sonic boom wave measuring system 14;

[0043] The turbulence generating system 11 includes a jet turbulence disruptor 1, a fan 2, and a nozzle 3;

[0044] 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 through a hose;

[0045] The hot wire measurement system 12 includes a hot wire probe 4 and a hot wire anemometer 5;

[0046] 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. The hot wire probe 4 faces the nozzle 3 and maintains a certain distance to sense the heat exchange between the filter and the fluid.

[0047] The electric spark sonic explosion source system 13 includes an electric spark igniter 6 and a parabolic reflector 7;

[0048] The parabolic reflector 7 is installed in the electric spark igniter 6;

[0049] The sonic boom wave measurement system 14 includes a fiber optic acoustic probe array 8, a signal acquisition system 9, and a computer 10;

[0050] The optical fiber acoustic probe array 8 is connected to the signal acquisition system 9 via a cable, and the signal acquisition system 9 is connected to the computer 10 via a network cable. The electric spark igniter 6 faces the optical fiber acoustic probe array 8 and maintains a certain distance.

[0051] Example 2: A test method based on electric spark simulating sonic boom waves in this embodiment is implemented based on a test system based on electric spark simulating sonic boom waves described in Example 1. The operation process is as follows:

[0052] Step 1: Use the turbulence generating 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 generating system;

[0053] Step 2: Measure the turbulence intensity using the hot wire measurement system 12 and transmit the data to the computer 10;

[0054] Step 3: After the turbulence intensity is measured, an N-type wave signal is generated by the electric spark sonic boom source system 13 to characterize the typical sonic boom characteristics;

[0055] Step 4: Turn on the turbulence generating 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 .

[0056] More specifically: the fan 2 is driven by a motor to generate flows of 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 disruptor 1, and the jet turbulence disruptor 1 generates planar jets of different intensities by comprehensively adjusting the flow rate of the fan 2 and the width of the nozzle 3, simulating different degrees of turbulence intensities.

[0057] More specifically, the hot-wire probe 4 transmits the sensed quantity to the hot-wire anemometer 5 , and the hot-wire anemometer 5 is provided with a compensation circuit, which can process the sensed quantity of the hot-wire probe 4 to obtain the turbulence intensity of the flow field.

[0058] More specifically, the sonic boom wave generated by the spark igniter 6 is a spherical wave, while the sonic boom wave near the ground surface is characterized by a plane wave. Therefore, after the spark igniter 6 generates a spherical sonic boom wave, it passes through the parabolic reflector 7 to convert the waveform from a spherical shape to a plane shape.

[0059] More specifically, the sonic boom wave has a high-frequency characteristic, and a fiber optic acoustic probe is used to sense the sonic boom wave signal.

[0060] More specifically, the computer 10 is used to control the signal acquisition system 9 and store measurement data in real time.

[0061] 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 it. Although the present invention has been described in detail with reference to the aforementioned embodiments, the technical solutions described in the aforementioned embodiments can still be modified, or some or all of the technical features therein can be replaced by equivalents. As long as there is no structural conflict, the various features in the specific implementation methods disclosed in this application can be combined with each other in any way, and the essence of the corresponding technical solutions will not deviate from the scope of the technical solutions of the present invention.

[0062] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods 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 disruptor (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) 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), and the hot wire anemometer (5) transmits data to the computer (10). 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) includes a fiber optic 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.

2. A test method based on electric spark simulating sonic boom waves, which is implemented by the test system based on electric spark simulating sonic boom waves 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: Measure the turbulence intensity using a hot wire measurement system (12) and transmit the data to a computer (10); Step 3: After the turbulence intensity is measured, an N-type wave signal is generated with the help of an electric spark sonic boom source system (13) to characterize the typical sonic boom characteristics; 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. The test method based on electric spark simulation of sonic explosion wave according to claim 2, characterized in that: The fan (2) is driven by a motor to generate flows of different flow rates, and 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 disruptor (1).

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

5. The test method based on electric spark simulation of sonic explosion wave according to claim 2, 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 planar shape.

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