Shock tube apparatus test control system and method

Abstract

The present application relates to the technical field of aerodynamic test, in particular to a shock tube equipment test control system and method, the system comprises: an interactive submodule, the interactive submodule comprises a remote controller for controlling the shock tube system; a detection submodule, the detection submodule comprises a non-contact acquisition unit, a schlieren unit, an optical acquisition unit and a free field unit, the non-contact acquisition unit is used for acquiring dynamic pressure changes of the model surface, the schlieren unit is used for observing flow changes of airflow affected by impact; the optical acquisition unit is used for measuring physical information of the tested model after being impacted by the explosion wave, and the free field unit is used for measuring pressure distribution at different positions of the free field; a control execution submodule, the control execution submodule is signal connected to the interactive submodule and the detection submodule. The present application solves the technical problems that the shock tube wind tunnel test in the prior art cannot realize complex timing logic and accurate synchronous control.

Description

Technical Field

[0001] This invention relates to the field of aerodynamic testing technology, specifically to a shock tube device testing control system and method. Background Technology

[0002] In aerospace, weapons manufacturing, and explosion physics, shock tube wind tunnel testing is a crucial tool for studying and evaluating gas dynamics. A shock tube wind tunnel is a wind tunnel device that uses shock waves to compress experimental gases and then generates hypersonic experimental gas flow through steady expansion. It consists of a long pipe and two closed ends; one end has a gas nozzle, and the other end has a reflector. By generating high-speed airflow at the nozzle, a shock wave is formed and reflected back at the reflector, creating a stable shock field. Shock tube wind tunnels have a relatively simple structure and are easy to operate, allowing for rapid experimental setup and testing. Compared to other experimental equipment, shock tube wind tunnels have lower experimental costs, making them suitable for conducting large-scale experiments. Various gas dynamics and explosion physics experiments can be performed in shock tube wind tunnels, such as studying shock wave propagation, reflection, and refraction; gas compression and expansion; and explosion wave propagation and attenuation, thereby obtaining abundant experimental data. Shock tube wind tunnel testing is widely used in aerospace, weapons design, and industrial safety. For example, in the aerospace field, shock tube wind tunnels can be used to test and study the aerodynamic performance, stability, and dynamic stability characteristics of aircraft; in the field of weapon design, they can be used to study the propagation and attenuation of explosion waves; and in the field of industrial safety, they can be used to study the diffusion of gases and the propagation of explosion waves in explosion accidents.

[0003] Shock tube wind tunnel testing methods typically include two types: static testing and dynamic testing. Static testing is mainly used to measure the aerodynamic characteristics of an object in a static state, such as drag and lift; while dynamic testing is mainly used to simulate the aerodynamic characteristics of an object in motion, such as takeoff, landing, and turning.

[0004] Typically, the shock tube system and the corresponding test and detection unit are two separate parts.

[0005] A conventional shock tube system is an integrated system encompassing the tube body, gas distribution, drive and control, safety and protection systems, and auxiliary equipment, used to generate and study shock wave phenomena. The shock tube body typically consists of a high-pressure section, a low-pressure section, and an experimental section. The gas distribution system comprises components such as a mixing tank, gas cylinders, pressure gauges, a vacuum pump, and piping, used to introduce the required drive gas and reactant mixture into the high and low-pressure sections of the shock tube. The drive and control system includes valves, controllers, and other components used to control the gas injection and emission, as well as the rupture of the membrane mechanism, to generate the desired shock wave. A complete shock tube system usually also includes safety and protection systems, such as pressure relief valves and rupture diaphragms, to ensure the safety of personnel and the stable operation of the equipment during experiments. Other auxiliary equipment may include devices such as vacuum gauges and digital pressure gauges, used for real-time monitoring and recording of various parameters during the experiment.

[0006] The testing and detection unit typically includes a pressure sensor, which is installed in the low-pressure section to collect pressure signals. These signals are then transmitted to a computer for analysis after passing through a charge amplifier and a photomultiplier tube. Alternatively, a grating spectrometer can be used to collect spectral signals, which are also processed and transmitted to the computer.

[0007] Current shock tube wind tunnel tests rely heavily on single sensors, such as wind speed or pressure sensors, for data detection. This single data detection method cannot fully reflect the complex flow characteristics and environmental changes within the shock tube wind tunnel, especially under extreme conditions such as high speed, high pressure, and high temperature, where the detection accuracy and stability of a single sensor will be severely affected.

[0008] Because there is no data interconnection or control loop between the two parts, and the system relies on manual operation and control, shock tube wind tunnel tests typically require manual operation and control by on-site personnel. This is not only inefficient but also susceptible to human error, affecting the reliability and stability of the test results. Furthermore, since wind tunnel tests often require long-term operation, on-site operation presents numerous challenges to personnel safety and equipment maintenance. The inability to achieve complex timing logic and precise synchronous control leads to discontinuities and inconsistencies in data acquisition, further impacting the accuracy and reliability of the test results.

[0009] In summary, existing shock tube wind tunnel tests have shortcomings in data detection, test operation, and synchronous control. Data acquisition during shock tube wind tunnel tests is a complex and delicate process that requires further technological innovation and improvement to enhance the efficiency and accuracy of the tests. Summary of the Invention

[0010] The purpose of this invention is to provide a test control system and method for shock tube equipment, so as to solve the problem that existing shock tube wind tunnel tests cannot achieve complex timing logic and precise synchronous control technology. The specific technical solution is as follows: This invention provides a shock tube device test and control system, comprising: an interaction submodule, which includes a remote control, a touch screen, and indicator lights for controlling the shock tube system; a detection submodule, which includes a non-contact acquisition unit, a schlieren unit, an optical acquisition unit, and a free field unit, wherein the non-contact acquisition unit is used to acquire dynamic pressure changes on the model surface, the schlieren unit is used to observe flow changes of airflow affected by the impact, the optical acquisition unit is used to measure the physical information of the tested model after being impacted by the blast wave, and the free field unit is used to measure the pressure distribution at different locations in the free field; and a control execution submodule, which is signal-connected to the interaction submodule and the detection submodule.

[0011] A further improvement of the shock tube equipment test control system of the present invention is that the control execution submodule includes a host computer, a signal trigger, and a controller. The host computer is used to receive the detection data of the detection submodule. The signal trigger is connected to the host computer and the controller and is used to trigger a control signal for the detection submodule. The controller is connected to a remote controller and is used to control the shock tube system.

[0012] A further improvement of the shock tube equipment test control system of the present invention is that the non-contact acquisition unit includes a pressure-sensitive coating, an excitation light source, an optical filter, and a high-speed camera. The pressure-sensitive coating is used to coat the surface of the model under test, the excitation light source is used to irradiate the pressure-sensitive coating to emit a fluorescence signal, the optical filter is used to convert the fluorescence image into quantitative pressure distribution data, and the high-speed camera is used to photograph the model under test.

[0013] A further improvement of the shock tube equipment test control system of the present invention is that the schlieren unit includes a reflector, a lifting platform, a knife-edge photonic unit and a light source. The knife-edge photonic unit is mounted on the lifting platform, and the light source, the reflector and the knife-edge photonic unit cooperate to form a Z-shaped or coaxial optical path.

[0014] A further improvement of the shock tube equipment test control system of the present invention is that the free field unit includes a pressure sensor and a data acquisition module, the data acquisition module being connected to the pressure sensor.

[0015] A further improvement of the shock tube device test control system of the present invention is that the physical information includes displacement, velocity and acceleration.

[0016] A further improvement of the shock tube equipment test control system of the present invention is that the interactive submodule also includes an alarm.

[0017] The present invention also provides a test control method for shock tube equipment, comprising the following steps: Provide the shock tube equipment test and control system as described above, and perform self-test on the shock tube equipment test and control system. If the self-test fails, process the failed module; if the self-test passes, establish a communication connection between it and the shock tube system. The remote control is activated and a self-test is performed on the shock tube system. If the self-test fails, the failed modules are processed. If the self-test passes, the ready status is fed back to the control execution submodule. The control execution submodule controls the detection submodule to supply power and enables the detection recording function of the free field unit. The remote control sends a start command to control the execution submodule to trigger the recording functions of the non-contact acquisition unit, schlieren unit, and optical acquisition unit. The shock tube system will be started after a first predetermined delay to conduct a shock tube wind tunnel test; After a second predetermined delay, the detection submodule is shut down via the control execution submodule, thus completing the entire testing process.

[0018] The application of the technical solution of the present invention has the following beneficial effects: This invention relates to a shock tube equipment test and control system. Through a detection submodule, it detects various data points; through an interaction submodule and a control execution submodule, it enables remote operation and logic control. Simultaneously, it replaces manual operation by controlling the start and stop of each unit of the detection system via bus / terminals, establishing a data link between the detection and testing system and the shock tube control system under test, enabling data interaction between the two systems. This allows for precise control of the detection system's start and stop status before and after the operation of the system under test (at a predetermined time), achieving complete and accurate test data acquisition. This improves the accuracy of data detection and testing efficiency, solving the problem of existing shock tube wind tunnel tests being unable to achieve complex timing logic and precise synchronous control. By combining multiple detection methods, this application enables the shock tube data detection and control system to acquire more comprehensive and accurate data, reducing errors that may arise from single detection methods and improving data reliability and accuracy. This application achieves remote operation and logic control, making the operation of the shock tube system more convenient and faster. Users do not need to directly operate the shock tube equipment; they can complete the test setup and start-up through a remote interface, greatly shortening test preparation time and improving test efficiency. This application fully integrates the shock tube system with the testing and detection unit, achieving coordinated control and detection of the shock tube. This means that during the experiment, the system can automatically adjust the operating state of the shock tube based on real-time detected data, ensuring the safety and stability of the testing process. Remote control and logic control reduce the possibility of operators directly contacting the high-risk shock tube equipment, lowering operational risks and ensuring personnel safety. The modular design of this application makes it easy to expand with new detection methods and control functions. Furthermore, due to the relative independence between the sub-modules, system maintenance is also more convenient.

[0019] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0020] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a framework diagram of the shock tube equipment test and control system of the present invention; Figure 2 This is a flowchart of the shock tube device testing and control method of the present invention; Figure 3 This is a schematic diagram of the layout of the shock tube equipment test and control system of the present invention.

[0021] Among them, 1. Free field unit; 2. Non-contact acquisition unit; 3. Optical acquisition unit; 4. Schlieren unit; 5. Test section of shock tube. Detailed Implementation

[0022] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0023] In the field of shock tube wind tunnel data monitoring, traditional techniques often rely on single detection methods, such as using only pressure sensors to monitor the flow conditions within the wind tunnel. However, this approach has significant limitations, as a single sensor can only provide limited information and cannot fully reflect the complex flow environment within the wind tunnel. Furthermore, data processing and analysis are often limited to simple data recording and display, lacking in-depth data mining and trend prediction.

[0024] Shock tubes, as devices that generate shock waves using high-speed gas flow, produce high-energy, high-temperature, and high-speed gas flows during experiments. For large equipment, on-site control under such high-speed impact conditions could pose a safety threat to operators. For example, the formation and propagation of the shock wave could produce unforeseen consequences, such as shock wave loads and debris impacts. Remote process control and experimental data acquisition can avoid direct exposure of operators to potentially hazardous environments, thus improving the safety of the experimental process.

[0025] Shock tube experiments typically involve brief but critical combustion or explosion processes, the resulting data and images of which are crucial for subsequent analysis. While high-speed camera systems can capture these high-speed processes, their storage time is limited. Therefore, accurately setting the start time for data acquisition and image acquisition ensures that recording begins when critical events occur, thus capturing complete data and image information. If data acquisition starts too early, data irrelevant to the critical phase of the experiment may be recorded, increasing the complexity and difficulty of data processing. If the start time is too late, critical events may be missed, leading to missing or insufficient data, affecting the accuracy and reliability of experimental results. Therefore, accurately setting the start time ensures that the most critical data and image information is captured within the limited storage time. This helps avoid unnecessary storage waste and optimizes the utilization of storage resources.

[0026] This application proposes a method and system that combines multiple detection methods, supports remote control, and allows for controllable data acquisition. This is achieved by establishing a data link between the shock tube system and the measuring equipment, and by adding corresponding control logic and interactive functions.

[0027] See Figures 1-3As shown, a shock tube device test and control system includes: an interaction submodule, which includes a remote controller for controlling the shock tube system; a detection submodule, which includes a non-contact acquisition unit 2, a schlieren unit 4, an optical acquisition unit 3, and a free field unit 1. The non-contact acquisition unit 2 is used to acquire dynamic pressure changes on the model surface, the schlieren unit 4 is used to observe flow changes of airflow affected by the impact, the optical acquisition unit 3 is used to measure the physical information of the tested model after being impacted by the blast wave, and the free field unit 1 is used to measure the pressure distribution at different locations in the free field; and a control execution submodule, which is signal-connected to the interaction submodule and the detection submodule. (See attached diagram) Figure 1 As shown, in the test section of the shock tube, non-contact acquisition unit 2, non-contact acquisition unit 2, schlieren unit 4 and optical acquisition unit 3 are deployed outside multiple observation windows. At the same time, multiple sensors are deployed inside the test section 5 of the shock tube and connected to the acquisition unit outside the test section of the shock tube via cables. During the experiment, test data can be detected in multiple ways, which is convenient for post-processing analysis and understanding of the shock test process status.

[0028] Specifically, the shock tube system to be tested is connected to the shock tube equipment test and control system of this application. A remote control allows for the manipulation of some components of the shock tube system, and this remote control function improves the safety of on-site operations. The settings of each unit in the detection submodule can comprehensively collect various data such as pressure, deformation, displacement, and velocity during the shock tube test.

[0029] Preferably, the control execution submodule includes a host computer, a signal trigger, and a controller. The host computer receives detection data from the detection submodule. The signal trigger is connected to both the host computer and the controller and is used to trigger control signals for the detection submodule. The controller is connected to a remote controller and is used to control the shock tube system. Specifically, the host computer receives image and sensor data from each detection subsystem via Ethernet, receives operating data from the shock tube system, and interacts with the controller. The signal trigger establishes a connection with the host computer via a serial port, receives operation commands from the host computer, and thus completes the real-time trigger control task for each detection submodule, thereby orderly activating the working state of each detection submodule. The controller establishes a connection with the wireless remote controller, receives remote controller commands, performs necessary logical operations, drives corresponding indicator lights and alarms, etc., and transmits remote controller commands through a data connection with the host computer, and can obtain real-time operating status of the shock tube system.

[0030] Preferably, the non-contact acquisition unit 2 includes a pressure-sensitive coating, an excitation light source, an optical filter, and a high-speed camera. The optical filter includes a bandpass filter, a long-pass filter, or a narrow-band filter. The pressure-sensitive coating is applied to the surface of the test model. The excitation light source is aimed at the test model to illuminate the pressure-sensitive coating and emit a fluorescence signal. The optical filter is used to convert the fluorescence image into quantitative pressure distribution data. A bandpass filter is installed at the light source outlet to limit the excitation light wavelength range. A long-pass filter or a narrow-band filter is installed in front of the high-speed camera lens. The high-speed camera captures images of the test model. By acquiring the fluorescence signal emitted by the pressure-sensitive coating on the surface of the test model excited by the excitation light source and converting the fluorescence image into quantitative pressure distribution data, dynamic pressure changes on the model surface can be captured.

[0031] Furthermore, the schlieren unit 4 includes a mirror, a lifting platform, a knife-edge photonic unit, and a light source. The mirror, as the core optical element, is typically mounted via a support frame, forming a Z-shaped or coaxial optical path with the light source and the knife-edge photonic unit. The lifting platform allows for adjustment in the X and Y directions, and is used to fine-tune the horizontal and vertical positions of optical elements (such as the knife edge and camera). The knife-edge photonic unit is located near the focal point of the mirror. By precisely adjusting the circular light spot formed by cutting the light source (usually cutting it in half), it controls the light intensity distribution entering the camera. The light source is a point source (such as a laser or LED), which is output via fiber optic coupling and forms a parallel beam through a beam expander and collimating lens. A white LED light source is preferred. By utilizing the refraction of light as it passes through a flow field with varying density, and the knife-edge photonic unit partially blocking the light to form bright and dark fringes, and then using a camera to record the changes in light intensity, the flow changes of airflow affected by impact can be observed.

[0032] Preferably, the free field unit 1 includes a pressure sensor and a data acquisition module. The data acquisition module is connected to the pressure sensor to measure the pressure distribution at different locations in the free field.

[0033] Preferably, the physical information includes displacement, velocity, and acceleration.

[0034] Preferably, the interactive submodule also includes a touch screen, indicator lights, and an alarm. These devices are installed on the control box panel to display specific detection data and to display indicator lights and issue alarms if any abnormalities occur.

[0035] like Figure 2As shown, this invention also provides a shock tube device testing and control method. By centralizing the start-up and shutdown control functions of each sub-functional unit of the testing system and establishing a data link between the testing system and the shock tube control system of the test object, data interaction between the two systems can be achieved. This allows for precise control of the start-up and shutdown status of the testing system before and after the operation of the system under test (at a predetermined time), achieving complete and accurate test data acquisition. The method includes the following steps: Provide the shock tube equipment test and control system as described above, and perform self-test on the shock tube equipment test and control system. If the self-test fails, the failed module shall be processed (repaired or replaced); if the self-test passes, establish a communication connection between it and the shock tube system. The remote controller is activated and performs a self-test on the shock tube system. If the self-test fails, the failed module is addressed (repaired or replaced). If the self-test passes, the ready status is fed back to the host computer of the control execution submodule. The host computer of the control execution submodule then controls the detection submodule to supply power and activate the detection and recording function of the free field unit 1. Specifically, the controller receives the remote control signal and remotely issues a start operation command through the remote control, controlling the execution submodule to trigger the recording functions of the non-contact acquisition unit 2, the schlieren unit 4, and the optical acquisition unit 3. The shock tube system will be started after a first predetermined delay to conduct a shock tube wind tunnel test; After a second predetermined delay, the detection submodule is shut down via the control execution submodule (the recording functions of non-contact acquisition unit 2, schlieren unit 4, and optical acquisition unit 3 are disabled), thus completing the entire testing process.

[0036] The first and second predetermined times can be set according to the actual test conditions. In this embodiment, the first and second predetermined times are both 2 seconds. The first predetermined time is generally longer than the time after all modules in the shock tube equipment test control system are started, and the second predetermined time is generally longer than the shock tube wind tunnel test time. The control of the first and second predetermined times can be controlled by software, and the opening operation can be performed by controlling the quick-opening valve.

[0037] Figure 2This is a flowchart of the shock tube equipment test control method of the present invention. The specific process is as follows: First, the shock tube equipment test control system performs a self-test and establishes communication with the shock tube system. Then, it determines whether the remote control is ready to start. If not, it returns to determine whether the remote control is ready to start. If yes, it performs a self-test of the shock tube system and reports the ready status. Then, it detects the power supply of the sub-module, powers it on, and then activates the detection and recording function of the free field unit 1 to determine whether the remote control is started. If not, it returns to determine whether the remote control is started. If yes, it triggers the recording functions of the non-contact acquisition unit 2, the schlieren unit 4, and the optical unit. After a delay (which can be set), it triggers the fast-opening valve of the shock tube system. After a delay (which can be set), it closes the recording functions of each detection sub-module and ends the process.

[0038] This invention relates to a shock tube equipment test and control system. Through a detection submodule, it achieves the detection of various data; through an interaction submodule and a control execution submodule, it achieves remote operation and logic control. By fully integrating the shock tube system with the test and detection unit, it realizes coordinated control of shock wave and detection, improving the accuracy of data detection and experimental efficiency. This solves the problem in existing shock tube wind tunnel tests that cannot achieve complex timing logic and precise synchronous control. By combining multiple detection methods, this application enables the shock tube data detection and control system to acquire more comprehensive and accurate data, reducing errors that may arise from single detection methods and improving data reliability and accuracy. This application realizes remote operation and logic control, making the operation of the shock tube system more convenient and faster. Users do not need to directly operate the shock tube equipment; they can complete the test setup and start-up through a remote interface, greatly shortening test preparation time and improving test efficiency. This application fully integrates the shock tube system with the test and detection unit, realizing coordinated control of shock wave and detection. This means that during the test, the system can automatically adjust the working state of the shock tube based on the real-time detected data, ensuring the safety and stability of the test process. Remote operation and logic control reduce the likelihood of operators having direct contact with high-risk shock tube equipment, thereby lowering operational risks and ensuring personnel safety. The modular design of this application facilitates the expansion of new detection methods and control functions; furthermore, the relative independence between subsystems makes system maintenance more convenient.

[0039] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A shock tube device test and control system, characterized in that, include: An interactive submodule, comprising a remote control for controlling the shock tube system, a touch screen, and indicator lights; The detection submodule includes a non-contact acquisition unit (2), a schlieren unit (4), an optical acquisition unit (3), and a free field unit (1). The non-contact acquisition unit (2) is used to acquire dynamic pressure changes on the model surface, the schlieren unit (4) is used to observe the flow changes of airflow affected by the impact, the optical acquisition unit (3) is used to measure the physical information of the tested model after being impacted by the explosion wave, and the free field unit (1) is used to measure the pressure distribution at different locations in the free field. A control execution submodule, wherein the control execution submodule is signal-connected to the interaction submodule and the detection submodule; The control execution submodule includes a host computer, a signal trigger, and a controller. The host computer is used to receive the detection data from the detection submodule. The signal trigger is connected to the host computer and the controller and is used to trigger control signals to the detection submodule. The controller is connected to a remote controller and is used to control the shock tube system. The detection submodule enables the detection of various data, while the interaction and control execution submodules enable remote operation and logic control. The start-stop control of each unit of the detection system is achieved through a bus / terminal interface, replacing manual operation. By combining the shock tube system with the test and detection unit, coordinated control of shock tube and detection is achieved. The system automatically adjusts the working state of the shock tube based on the real-time detected data.

2. The shock tube equipment test and control system according to claim 1, characterized in that, The non-contact acquisition unit (2) includes a pressure-sensitive coating, an excitation light source, an optical filter, and a high-speed camera. The pressure-sensitive coating is used to coat the surface of the model under test. The excitation light source is used to irradiate the pressure-sensitive coating to emit a fluorescent signal. The optical filter is used to convert the fluorescent image into quantitative pressure distribution data. The high-speed camera is used to photograph the model under test.

3. The shock tube equipment test and control system according to claim 1, characterized in that, The schlieren unit (4) includes a mirror, a lifting platform, a knife-edge photonic unit, and a light source. The knife-edge photonic unit is installed on the lifting platform. The light source, the mirror, and the knife-edge photonic unit cooperate to form a Z-shaped or coaxial optical path.

4. The shock tube equipment test and control system according to claim 1, characterized in that, The free field unit (1) includes a pressure sensor and a data acquisition module, wherein the data acquisition module is connected to the pressure sensor.

5. The shock tube equipment test and control system according to claim 1, characterized in that, The physical information includes displacement, velocity, and acceleration.

6. The shock tube equipment test and control system according to claim 1, characterized in that, The interactive submodule also includes an alarm.

7. A test control method for shock tube equipment, characterized in that, Includes the following steps: The system provides a shock tube device test and control system as described in claim 1, and performs a self-test on the shock tube device test and control system. If the self-test fails, the module that fails is processed; if the self-test passes, a communication connection is established between it and the shock tube system. Start the remote control and perform a self-test on the shock tube system. If the self-test fails, the failed module is processed. If the self-test passes, the ready status is fed back to the control execution submodule. The control execution submodule controls the detection submodule to supply power and enable the detection recording function of the free field unit (1). The remote controller sends a start command to control the execution submodule to trigger the recording functions of the non-contact acquisition unit (2), the schlieren unit (4), and the optical acquisition unit (3); The shock tube system will be started after a first predetermined delay to conduct a shock tube wind tunnel test; After a second predetermined delay, the detection submodule is shut down via the control execution submodule, thus completing the entire testing process.

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