CN117760681B - Combined type acoustic explosion test device and method suitable for large supersonic wind tunnel - Google Patents
Combined type acoustic explosion test device and method suitable for large supersonic wind tunnel Download PDFInfo
- Publication number
- CN117760681B CN117760681B CN202410194980.7A CN202410194980A CN117760681B CN 117760681 B CN117760681 B CN 117760681B CN 202410194980 A CN202410194980 A CN 202410194980A CN 117760681 B CN117760681 B CN 117760681B
- Authority
- CN
- China
- Prior art keywords
- model
- measuring device
- test
- wind tunnel
- point
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 186
- 238000004880 explosion Methods 0.000 title claims abstract description 83
- 238000000034 method Methods 0.000 title claims abstract description 34
- 238000010998 test method Methods 0.000 claims abstract description 25
- 238000005259 measurement Methods 0.000 claims description 48
- 230000033001 locomotion Effects 0.000 claims description 47
- 230000007246 mechanism Effects 0.000 claims description 26
- FGUUSXIOTUKUDN-IBGZPJMESA-N C1(=CC=CC=C1)N1C2=C(NC([C@H](C1)NC=1OC(=NN=1)C1=CC=CC=C1)=O)C=CC=C2 Chemical compound C1(=CC=CC=C1)N1C2=C(NC([C@H](C1)NC=1OC(=NN=1)C1=CC=CC=C1)=O)C=CC=C2 FGUUSXIOTUKUDN-IBGZPJMESA-N 0.000 claims description 3
- GNFTZDOKVXKIBK-UHFFFAOYSA-N 3-(2-methoxyethoxy)benzohydrazide Chemical compound COCCOC1=CC=CC(C(=O)NN)=C1 GNFTZDOKVXKIBK-UHFFFAOYSA-N 0.000 claims description 2
- 230000009286 beneficial effect Effects 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 8
- 239000000523 sample Substances 0.000 description 7
- 238000004458 analytical method Methods 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 238000007405 data analysis Methods 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 3
- 238000005457 optimization Methods 0.000 description 3
- 238000012805 post-processing Methods 0.000 description 3
- 238000004088 simulation Methods 0.000 description 3
- 238000011010 flushing procedure Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000012552 review Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a combined acoustic explosion test device and method suitable for a large supersonic wind tunnel. The test device comprises a wind tunnel, and further comprises a parallel measuring device, a single-point measuring device and a sonic boom test model device which are positioned in the wind tunnel. The test method comprises the following test modes in different forms: performing an acoustic explosion test according to a model moving method by using a single-point measuring device alone; performing an acoustic explosion test by using a single-point measuring device independently according to a device moving method; carrying out acoustic explosion test by using a parallel measuring device independently; carrying out an acoustic explosion test by taking a parallel measuring device as a main and single-point measuring device as an auxiliary; and simultaneously, carrying out an acoustic explosion test by using the single-point measuring device and the parallel measuring device. The invention has the beneficial effects that: the single-point measuring device and the parallel measuring device are compatible, the most suitable device can be selected to carry out the test according to the test requirement, the two sets of devices can work independently to obtain more test data, and a mode of 'one is mainly used and the other is mainly used' can be adopted.
Description
Technical Field
The invention belongs to the technical field of wind tunnel acoustic explosion tests, and particularly relates to a combined acoustic explosion test device and method suitable for a large supersonic wind tunnel.
Background
When the airflow environment in the wind tunnel is supersonic, the model appearance can generate a series of wave systems, the wave systems often correspond to pressure changes, and the acoustic explosion test is mainly used for acquiring the variation of the pressure distribution influenced by the model wave system in a given space compared with the pressure distribution when the space is not influenced by the model wave system. It can be seen that the acoustic explosion test measurement data mainly comprises two parts, namely, a spatial pressure distribution affected by the model wave system and a pressure distribution of the same space not affected by the model wave system.
At present, the acoustic explosion test method mainly comprises two methods, namely a model moving method and a measuring device moving method. The model moving method is that the measuring device keeps a fixed position in the test, acoustic explosion test data measurement is achieved by changing the space position of the model, as shown in fig. 1, when the model is at a position 1, the measuring device obtains pressure distribution data affected by the model wave system, when the model is at a position 2, a model wave system affected area shown by a dotted line is already located at the downstream of the measuring device, and at the moment, the measuring device obtains pressure distribution data not affected by the model wave system. The moving method of the measuring device means that the model keeps a fixed position in the test, the acoustic explosion test data measurement is realized by changing the space position of the measuring device, as shown in fig. 2, the model keeps the fixed position unchanged, when the measuring device is at a position 1, pressure distribution data which is not influenced by the model wave system is obtained, and when the measuring device is at a position 2, pressure distribution data which is influenced by the model wave system is obtained.
Based on different test methods, the current acoustic explosion test measuring device mainly comprises the following two types, namely a single-point measuring device and a parallel measuring device. The appearance of the single-point measuring device is similar to that of a probe, and the single-point measuring device is mainly characterized in that pressure distribution data of one model position point can be obtained only at each time point. In order to obtain the complete model acoustic explosion signal, the model moving method is adopted to enable all wave systems of the model to sweep through the single-point measuring device in sequence, or the measuring device moving method is adopted to enable the measuring device to sweep through the complete model wave system influence area in sequence. Taking a measuring probe as a single-point measuring device as an example, fig. 3 shows a schematic diagram of a model moving method, wherein the measuring probe keeps a fixed position, the model moves from a front position to a rear position along an X direction, during which the model wave system influence is scanned across the probe in sequence, and corresponding pressure data is acquired by the probe. FIG. 4 shows a schematic diagram of a single point measuring device movement method, the model is kept at a fixed position, the measuring probe moves along the X direction to pass through the acoustic explosion signal influence area of the model, and corresponding pressure data are acquired by single point measuring equipment. The single-point measuring device has the advantages of small size, streamline appearance, small influence on the environment of a wind tunnel flow field, no need of post-processing of obtained data, higher reliability, low test efficiency, long time required for obtaining pressure distribution of a complete model only by obtaining data of one model position point at each time point, and time saving, wherein the single-point measuring device is often divided into two parts, one part is a model wave system influence measuring device which is mainly positioned in a model wave system influence area, pressure data influenced by the model wave system is mainly obtained, the other part is a reference measuring device which is usually arranged outside the model wave system influence area, and the non-interference wind tunnel incoming flow pressure data is mainly obtained.
The parallel measuring device is integrally strip-shaped, and is mainly characterized in that the device is provided with a series of pressure measuring points along the X direction, so that the pressure distribution data of the whole model can be obtained at the same time point. The parallel measuring device is large in size and can only be fixedly arranged on the wind tunnel wallboard, and the test can only adopt a model moving method, as shown in fig. 5, the distance between the model and the parallel measuring device in the Y direction is adjusted before the test, so that the distance meets the planned test working condition; after the wind tunnel is started and the flow field is established, the model is controlled to move for a certain distance in a stepped mode along the X direction of the wind tunnel, model influence areas corresponding to the steps are all located in a measuring interval of the parallel measuring device, such as a model position 1 and a model position 2, after the steps are completed, the model is controlled to move to a position, away from the parallel measuring device, of the model wave system influence area, such as a model position 3, of the model along the X direction, at the moment, data collected by the parallel measuring device can be regarded as interference-free data, and then the wind tunnel is shut down. And processing the acquired data to obtain a corresponding acoustic explosion test result.
At present, the parallel measuring device has high test efficiency and can acquire reliable test data by matching with a corresponding data processing method to become a main measuring device for a sound explosion test, but the problem is that the parallel measuring device is installed in a wind tunnel and has a size far larger than that of a single-point measuring device, so that the parallel measuring device can be generally used in a large supersonic wind tunnel, meanwhile, the large size inevitably affects the air flow distribution in the wind tunnel, the influence and the wave system generated by a model interfere with each other, the reliability and the accuracy of the test data acquired by the parallel measuring device are affected, that is, the quality of the sound explosion test data acquired by the parallel measuring device is greatly affected by the appearance of the device, and the smaller the appearance of the parallel measuring device affects the air flow distribution of the wind tunnel, the better the data quality is. However, because of the differences in the structural forms of different wind tunnels and the differences in the installation positions of the parallel measuring devices in the wind tunnels, the parallel measuring devices among different wind tunnels are difficult to be used commonly, and the theoretically optimized parallel measuring devices designed through numerical simulation are directly adopted, on one hand, the numerical simulation is difficult to truly simulate the structural details of the wind tunnels, on the other hand, the deformation of the parallel measuring devices caused by the airflow pulsation and the like of the wind tunnels is difficult to be simulated, the effect of the theoretically optimized parallel measuring devices in the actual test is uncertain, and the situation that whether the device structure is influenced, the model state is caused or the wind tunnel test working condition is caused is difficult to be judged when the test data obtained based on the device are in doubt. Although the single-point measuring device has lower test efficiency, the single-point measuring device has small size and streamline shape, has little influence on the air flow distribution of the wind tunnel, has higher reliability of the obtained test data and better universality of the wind tunnel, so the single-point measuring device has more application in acoustic explosion tests which rely on the focus of a small wind tunnel for research.
Disclosure of Invention
The invention aims at: the invention provides a combined type acoustic explosion test device and method suitable for a large supersonic wind tunnel, which solve the problems that measurement data are very sensitive to external conditions, especially flow field changes, and the existing acoustic explosion test device and method can provide very limited auxiliary analysis means, so that the measurement data are difficult to analyze.
The aim of the invention is achieved by the following technical scheme:
The combined type acoustic explosion test device comprises a wind tunnel, and comprises a parallel measuring device, a single-point measuring device and an acoustic explosion test model device which are arranged in the wind tunnel, wherein the parallel measuring device is fixedly arranged on a wind tunnel wall plate of a test area, the single-point measuring device is arranged on the inner side of the wind tunnel wall plate of the test area and at least has X-direction and Y-direction movement capability, the acoustic explosion test model device is arranged in the middle of the test area, and the acoustic explosion test model device at least has X-direction, Y-direction and pitching-direction movement capability.
Further, the single-point measuring device comprises single-point measuring equipment, a single-point supporting device, a single-point motion control mechanism and reference measuring equipment, wherein the single-point supporting device is arranged between the single-point measuring equipment and the single-point motion control mechanism, the single-point motion control mechanism is fixedly arranged on the wind tunnel wallboard of the test area, the single-point motion control mechanism at least has the capability of controlling the X-direction and Y-direction motion of the single-point measuring equipment, and the reference measuring equipment is fixedly arranged on the wind tunnel wallboard which is not influenced by the model wave system.
Further, the acoustic explosion test model device comprises an acoustic explosion test model, a model supporting device and a model motion control mechanism, wherein the model supporting device is arranged between the acoustic explosion test model and the model motion control mechanism, and the model motion control mechanism at least has the capability of controlling the acoustic explosion test model to move in the X direction, the Y direction and the pitching direction.
Furthermore, the parallel measuring device and the single-point measuring device are symmetrically arranged.
A combined acoustic explosion test method suitable for a large supersonic wind tunnel adopts the test device, and comprises the following test modes in different forms:
mode 1, carrying out an acoustic explosion test according to a model moving method by using a single-point measuring device alone;
Mode 2, carrying out an acoustic explosion test by using a single-point measuring device independently according to a device moving method;
Mode 3, carrying out acoustic explosion test by using the parallel measuring device alone;
mode 4, carrying out an acoustic explosion test by taking the parallel measuring device as a main and single-point measuring device as an auxiliary;
And 5, carrying out an acoustic explosion test by using the single-point measuring device and the parallel measuring device.
Further, in the above-described embodiment 1, the test method is as follows:
step a, according to the planned test working condition, the distance between the model and the single-point measuring device in the Y direction is adjusted;
b, installing a reference measuring device of the single-point measuring device at a fixed position of a wind tunnel wall plate, wherein the position is ensured not to be influenced by a model and a wall wave system;
Step c, starting the wind tunnel and establishing an ultrasonic flow field;
Step d, the single-point measuring equipment of the single-point measuring device keeps a fixed position, the model moves along the X direction for a distance, during which the model wave system influence is scanned across the single-point measuring equipment in sequence, and corresponding pressure data are acquired by the single-point measuring equipment; meanwhile, the interference-free incoming flow pressure data are acquired by a reference measuring device;
and e, closing the wind tunnel.
Further, in the above-described mode 2, the test method is as follows:
step a, according to the planned test working condition, the distance between the model and the single-point measuring device in the Y direction is adjusted;
b, installing a reference measuring device of the single-point measuring device at a fixed position of a wind tunnel wall plate, wherein the position is ensured not to be influenced by a model and a wall wave system;
Step c, starting the wind tunnel and establishing an ultrasonic flow field;
step d, the model keeps a fixed position, single-point measuring equipment of the single-point measuring device moves along the X direction to pass through an acoustic explosion signal influence area of the model, and corresponding pressure data are acquired by the single-point measuring equipment; meanwhile, the interference-free incoming flow pressure data are acquired by a reference measuring device;
and e, closing the wind tunnel.
Further, in the above-described mode 3, the test method is as follows:
step a, adjusting the distance between the model and the parallel measuring device in the Y direction according to the planned test working condition;
Step b, starting the wind tunnel and establishing an ultrasonic flow field;
Step c, controlling the model to move in a step mode along the X direction of the wind tunnel, wherein model influence areas corresponding to steps are all in a measurement interval of the parallel measurement device, and pressure data corresponding to the influence of the model influence areas are acquired by the parallel measurement device;
step d, controlling the model to move along the X direction until a model wave system influence area is far away from the position of the parallel measuring device, wherein the data acquired by the parallel measuring device can be regarded as interference-free data;
and e, closing the wind tunnel.
Further, in the above-described mode 4, the test method is as follows:
step a, adjusting the distance between the model and the parallel measuring device in the Y direction according to the planned test working condition;
b, installing a reference measuring device of the single-point measuring device at a fixed position of a wind tunnel wall plate, wherein the position is ensured not to be influenced by a model and a wall wave system;
Step c, starting the wind tunnel and establishing an ultrasonic flow field;
Step d, controlling the model to move in a step mode along the X direction of the wind tunnel, wherein model influence areas corresponding to steps are all in a measurement interval of the parallel measurement device, and pressure data corresponding to the influence of the model influence areas are acquired by the parallel measurement device;
Step e, in the step d, simultaneously, single-point measuring equipment of the single-point measuring device moves at intervals between steps which are the same as those of the model, corresponding pressure data are collected, and meanwhile, interference-free incoming flow pressure data are collected by referring to the measuring device;
f, after the step d is finished, controlling the model to move along the X direction until the model wave system influence area is far away from the position of the parallel measuring device, wherein the data collected by the parallel measuring device can be regarded as interference-free data;
step g, in the step f, the single-point measuring equipment synchronously moves according to the model, and acquires corresponding pressure data, and meanwhile, the reference measuring device acquires interference-free incoming flow pressure data;
and h, closing the wind tunnel.
Further, in the above-described mode 5, the test method is as follows:
Step a, according to the planned test working condition, the distance between the model and the parallel measuring device in the Y direction is adjusted, and at the moment, the distance between the single-point measuring equipment of the single-point measuring device and the model in the Y direction is also determined;
b, installing a reference measuring device of the single-point measuring device at a fixed position of a wind tunnel wall plate, wherein the position is ensured not to be influenced by a model and a wall wave system;
Step c, adjusting the position of the single-point measuring equipment in the axial direction, keeping the single-point measuring equipment still during the test, and ensuring that the complete pressure distribution data of the wave system influence area can be obtained when the model moves along the X direction;
step d, starting the wind tunnel and establishing an ultrasonic flow field;
Step e, controlling the model to move in a step mode along the X direction of the wind tunnel, wherein model influence areas corresponding to steps are all in a measurement interval of the parallel measurement device, and pressure data corresponding to the influence of the model influence areas are acquired by the parallel measurement device; simultaneously, the non-interference incoming flow pressure data are acquired by single-point measuring equipment and a reference measuring device;
F, after the step e is finished, controlling the model to move along the X direction until the model wave system influence area is far away from the position of the parallel measuring device, wherein the data collected by the parallel measuring device can be regarded as interference-free data;
And g, closing the wind tunnel.
The invention has the beneficial effects that:
1. Aiming at the problems that test data obtained based on a parallel measuring device are influenced by various factors such as wind tunnel incoming flow conditions, spatial flow field distribution, the structural form and the external dimension of the device, and the like, the influence of the device on the test data is difficult to strip out, and further the optimal design of the device is supported, a single-point measuring device with small flow field interference and high test data reliability is introduced into the device, and a corresponding test method is designed, so that more reliable incoming flow condition change and spatial flow field distribution data are obtained, the test data analysis of the parallel measuring device is assisted, the influence of the device on the test data is stripped out, and the problems that the current technology only can obtain the parallel measuring device suitable for the current wind tunnel through repeated iterative optimization of a large number of test attempts and simulation calculation are avoided.
2. The single-point measuring device and the parallel measuring device are compatible in the same wind tunnel, the most suitable device can be selected to carry out the test according to the test requirement, the problem of wind tunnel correlation possibly existing in the test carried out in different wind tunnels is avoided, the two sets of devices can respectively and independently work to obtain more test data, a mode of 'one being the main one and the other being the auxiliary one' can be adopted, the auxiliary analysis data of the influence of parameter change on the test data is added while the required test data is obtained, and the better analysis of the test data rule is facilitated.
The foregoing inventive subject matter and various further alternatives thereof may be freely combined to form a plurality of alternatives, all of which are employable and claimed herein; and the invention can be freely combined between the (non-conflicting choices) choices and between the choices and other choices. Various combinations will be apparent to those skilled in the art from a review of the present disclosure, and are not intended to be exhaustive or all of the present disclosure.
Drawings
FIG. 1 is a schematic diagram of a prior art model shifting method test.
FIG. 2 is a schematic diagram of a prior art measurement device movement method test.
FIG. 3 is a schematic diagram of a single point measurement device model movement method test.
FIG. 4 is a schematic illustration of a single point measurement device movement method test.
FIG. 5 is a schematic diagram of a parallel measurement device model movement method test.
Fig. 6 is a schematic structural view of the present invention.
Fig. 7 is a schematic diagram of the reference measurement device pressure measurement results.
FIG. 8 is a schematic diagram of the results of sonic boom test for a single point measurement device and a parallel measurement device.
In the figure: 1 is a parallel measuring device; 2 is single-point measuring equipment; 3 is a single-point supporting device; 4 is a single-point motion control mechanism; 5 is a reference measurement device; 6 is a sound explosion test model; 7 is a model supporting device; 8 is a model motion control mechanism.
Detailed Description
The following non-limiting examples illustrate the invention.
Example 1
Referring to fig. 6, a combined acoustic explosion testing device suitable for a large supersonic wind tunnel is described by taking the arrangement of devices along the longitudinal distribution of the wind tunnel as an example, and the devices can be transversely arranged along the horizontal plane according to the specific conditions of the wind tunnel. The test device comprises a wind tunnel, and comprises a parallel measuring device 1, a single-point measuring device and an acoustic explosion test model device which are positioned in the wind tunnel.
The parallel measuring device 1 is fixedly arranged on a wind tunnel wallboard of the test area. The single-point measuring device is positioned on the inner side of the wind tunnel wall plate of the test area and at least has X-direction and Y-direction movement capability. The acoustic explosion test model device is positioned in the middle of the test area and at least has the motion capacities of X direction, Y direction and pitching direction.
The preferred parallel measuring device 1 is arranged symmetrically to the single point measuring device. The single point measuring device comprises a single point measuring apparatus 2 (i.e. model wave system influencing measuring apparatus), a single point support 3, a single point motion control mechanism 4 and a reference measuring apparatus 5. A single-point supporting device 3 is arranged between the single-point measuring equipment 2 and the single-point motion control mechanism 4 and is used for realizing the connection between the single-point measuring equipment and the single-point motion control mechanism. The single-point motion control mechanism 4 is fixedly arranged on a wind tunnel wallboard of a test area, and according to a coordinate system shown in the drawing, the single-point motion control mechanism 4 at least has the capability of controlling the X-direction and Y-direction motions of single-point measuring equipment, and the reference measuring equipment 5 is fixedly arranged on the wind tunnel wallboard which is not influenced by a model wave system.
The acoustic explosion test model device comprises an acoustic explosion test model 6, a model supporting device 7 and a model motion control mechanism 8. And a model supporting device 7 is arranged between the acoustic explosion test model 6 and the model motion control mechanism 8 and is used for realizing the connection of the two parts. The model motion control mechanism 8 has at least the capability of controlling the motion of the acoustic explosion test model in the X direction, the Y direction and the pitch direction. The acoustic explosion test model device is a device of the wind tunnel, or is a special device for acoustic explosion test, and is a device which is necessary for carrying out acoustic explosion test.
Example 2
Referring to fig. 6, a combined acoustic explosion test method suitable for a large supersonic wind tunnel adopts the test device of embodiment 1, and includes the following test modes in different forms.
Mode 1, a single point measuring device is used alone to perform an acoustic explosion test according to a model moving method.
Mode 2, the acoustic explosion test is carried out according to the device movement method by using a single-point measuring device alone.
And 3, carrying out an acoustic explosion test by using the parallel measuring device alone.
And 4, carrying out an acoustic explosion test by taking the parallel measuring device as a main and single-point measuring device as an auxiliary.
And 5, carrying out an acoustic explosion test by using the single-point measuring device and the parallel measuring device.
In mode 1, the test method is as follows.
And a, adjusting the distance between the model and the single-point measuring device in the Y direction (the height direction is also the vertical airflow direction) according to the planned test working condition.
And b, installing a reference measuring device of the single-point measuring device at a fixed position of the wind tunnel wall plate, wherein the position is ensured to be free from the influence of the model and the wall wave system.
And c, starting the wind tunnel and establishing a supersonic flow field.
Step d, the single-point measuring equipment of the single-point measuring device keeps a fixed position, the model moves along the X direction (axial direction, also air flow direction) for a distance, during which the model wave system influence is scanned across the single-point measuring equipment in sequence, and corresponding pressure data is acquired by the single-point measuring equipment; at the same time, the undisturbed incoming flow pressure data is acquired by the reference measuring device.
And e, closing the wind tunnel.
In mode 2, the test method is as follows.
And a, adjusting the distance between the model and the single-point measuring device in the Y direction according to the planned test working condition.
And b, installing a reference measuring device of the single-point measuring device at a fixed position of the wind tunnel wall plate, wherein the position is ensured to be free from the influence of the model and the wall wave system.
And c, starting the wind tunnel and establishing a supersonic flow field.
Step d, the model keeps a fixed position, single-point measuring equipment of the single-point measuring device moves along the X direction to pass through an acoustic explosion signal influence area of the model, and corresponding pressure data are acquired by the single-point measuring equipment; at the same time, the undisturbed incoming flow pressure data is acquired by the reference measuring device.
And e, closing the wind tunnel.
In mode 3, the test method is as follows.
And a, adjusting the distance between the model and the parallel measuring device in the Y direction according to the planned test working condition.
And b, starting the wind tunnel and establishing a supersonic flow field.
And c, controlling the model to move in a step mode along the wind tunnel X direction, wherein model influence areas corresponding to steps are all in a measurement interval of the parallel measurement device, and pressure data corresponding to the influence of the model influence areas are acquired by the parallel measurement device.
And d, controlling the model to move along the X direction until the model wave system influence area is far away from the position of the parallel measuring device, wherein the data acquired by the parallel measuring device can be regarded as interference-free data.
And e, closing the wind tunnel.
The first three test devices and methods are different from the prior art, only the required test device can be selected, and the acoustic explosion measuring device which does not participate in the test can be removed. It is also possible to choose to keep all the devices, but it should be noted that the test area selection of the model and the measurement device should avoid the wave system influence area of the rest of the measurement devices so as not to affect the accuracy of the test data. The single-point measuring device and the parallel measuring device can be respectively arranged at the same position to carry out the acoustic explosion test, at the moment, the model wave system influence areas keep the same to the greatest extent, and at the moment, the influence of the device difference on test data can be better reflected based on the test results obtained by different measuring devices.
In mode 4, the test method is as follows.
And a, adjusting the distance between the model and the parallel measuring device in the Y direction according to the planned test working condition.
And b, installing a reference measuring device of the single-point measuring device at a fixed position of the wind tunnel wall plate, wherein the position is ensured to be free from the influence of the model and the wall wave system.
And c, starting the wind tunnel and establishing a supersonic flow field.
And d, controlling the model to move in a step mode along the wind tunnel X direction, wherein model influence areas corresponding to steps are all in a measurement interval of the parallel measurement device, and pressure data corresponding to the influence of the model influence areas are acquired by the parallel measurement device.
And e, in the step d, simultaneously, single-point measuring equipment of the single-point measuring device moves at the same step interval as the model, corresponding pressure data are collected, and meanwhile, interference-free incoming flow pressure data are collected by referring to the measuring device.
And f, after the step d is finished, controlling the model to move along the X direction until the model wave system influence area is far away from the position of the parallel measuring device, wherein the data collected by the parallel measuring device can be regarded as interference-free data.
And g, in the step f, simultaneously, the single-point measuring equipment synchronously moves with the model, and acquires corresponding pressure data, and simultaneously, the reference measuring device acquires interference-free incoming flow pressure data.
And h, closing the wind tunnel.
The method is adopted to carry out the test, and the acoustic explosion test data are obtained mainly by the parallel measuring device, so that on one hand, the change of the incoming flow pressure can be monitored in real time by the reference measuring device, and a data basis is provided for confirming the influence of the incoming flow condition change on the test data; on the other hand, the single-point measuring equipment and the model keep synchronous motion, which is equivalent to the influence of the wave system of the same position of the model obtained by the single-point measuring equipment all the time, and is beneficial to analyzing the influence of different space flow field distribution on test data. Reliable data support is provided for test data analysis based on parallel measurement devices.
In mode 5, the test method is as follows.
And a step a, adjusting the distance between the model and the parallel measuring device in the Y direction according to the planned test working condition, wherein the distance between the single-point measuring device of the single-point measuring device and the model in the Y direction is also determined.
And b, installing a reference measuring device of the single-point measuring device at a fixed position of the wind tunnel wall plate, wherein the position is ensured to be free from the influence of the model and the wall wave system.
And c, adjusting the position of the single-point measuring equipment in the axial direction, keeping the single-point measuring equipment still during the test, and ensuring that the complete pressure distribution data of the wave system influence area can be obtained when the model moves along the X direction.
And d, starting the wind tunnel and establishing a supersonic flow field.
Step e, controlling the model to move in a step mode along the X direction of the wind tunnel, wherein model influence areas corresponding to steps are all in a measurement interval of the parallel measurement device, and pressure data corresponding to the influence of the model influence areas are acquired by the parallel measurement device; and simultaneously, the non-interference incoming flow pressure data is acquired by single-point measuring equipment and a reference measuring device.
And f, after the step e is finished, controlling the model to move along the X direction until the model wave system influence area is far away from the position of the parallel measuring device, wherein the data collected by the parallel measuring device can be regarded as interference-free data.
And g, closing the wind tunnel.
For the model with an up-down symmetrical structure, if the distances between the model and the single-point measuring device and the parallel measuring device in the Y direction are consistent, the obtained test data can be directly compared and analyzed, and if the distances are inconsistent, the two groups of data can be normalized to the same height through data post-processing and then are compared and analyzed. For an asymmetric model, a test can be carried out in a mode of forward and backward loading of the model, and consistency of test data obtained under the same conditions of two sets of devices is compared, so that reliability of the test data of the parallel measuring device is better evaluated.
The invention provides a combined acoustic explosion test device and method, which fully exert the respective advantages of a single-point measuring device and a parallel measuring device, solve the problems existing in the independent use of the respective devices and ensure the reliability of acoustic explosion test data of a large-scale temporary-flushing supersonic wind tunnel. On the one hand, the single-point measuring device has little interference to a flow field, the reliability of test data is high, the test efficiency is low, and the single-point measuring device is not suitable for being used as a main measuring device in a large temporary flushing wind tunnel with large air consumption, but is only used for acquiring key test data and is further suitable for being used as an auxiliary analysis and verification means of parallel measuring device data. In addition, the parallel measuring device has high test efficiency, is very suitable for large-scale wind tunnels, but has great influence on test data due to the appearance and the size, has strong correlation between the structural form and the wind tunnel structure and the running mode, and needs as many means and data as possible to assist in data analysis, thereby supporting optimization and improvement of the parallel measuring device and finally becoming a high-reliability acoustic explosion test measuring device suitable for the current wind tunnels.
Although the two sets of devices are used in a simple combined mode, in order to avoid mutual interference of wave systems among the devices and meet the requirements of respective measuring ranges, the connection form of single-point measuring equipment and a motion control mechanism in the single-point measuring device serving as an auxiliary analysis means, the streamline aerodynamic shape of the whole set of device and the like are required to be specially designed, and meanwhile, the installation positions of the two sets of measuring devices are also required to be comprehensively considered according to a model motion range.
In the aspect of control, in the past, only model movement or device movement is needed in the single test period based on the acoustic explosion test of the single-point measuring device, and only model movement is needed in the acoustic explosion test based on the parallel measuring device.
The first three methods are essentially identical to conventional test methods in terms of test methods. According to the fourth test method, data acquired by the reference measurement equipment are used as an incoming flow condition stability monitoring result, data acquired by the single-point measurement equipment when the same model wave system influence region is different in space flow field are used as a space flow field distribution influence monitoring result, the influence of the device on the test data can be better stripped from the test data based on the parallel measurement device, and the shape optimization of the device is better supported. The fifth test method increases the data acquired by the reference measurement equipment as the stability monitoring result of the incoming flow condition, realizes that a single test acquires two groups of acoustic explosion test data based on two sets of acoustic explosion test data, can mutually verify and analyze the data after post-treatment, assists in improving the parallel measurement device, increases the available test data volume of the single test, and improves the test efficiency to a certain extent.
The method provided by the invention is applied to a sonic boom test in a supersonic wind tunnel, and is installed in a sonic boom test device in a large supersonic wind tunnel, wherein the upper wall plate is provided with a single-point measuring device (comprising single-point measuring equipment and reference measuring equipment) with a probe configuration, the lower wall plate is provided with a parallel measuring device with a pressure measuring rail configuration, and the middle part is a model installed on a model motion control mechanism. Fig. 7 shows the results of the incoming flow pressure obtained by the reference measuring device during the test, and it can be seen that the incoming flow pressure changes by about 0.1% in comparison with the mean value of not more than 40Pa during the test, and the incoming flow pressure has better stability. FIG. 8 shows the results of model acoustic explosion signals obtained by post-processing test data obtained by the single-point measuring device and the parallel measuring device, and it can be seen that the test result curves of the two sets of devices are consistent in rule as a whole.
The foregoing basic embodiments of the invention, as well as other embodiments of the invention, can be freely combined to form numerous embodiments, all of which are contemplated and claimed. In the scheme of the invention, each selection example can be arbitrarily combined with any other basic example and selection example.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention.
Claims (6)
1. The utility model provides a combination formula sound burst test device suitable for large-scale supersonic wind tunnel, includes wind tunnel, its characterized in that: the device comprises a parallel measuring device (1), a single-point measuring device and a sonic boom test model device which are positioned in a wind tunnel, wherein the parallel measuring device (1) is fixedly arranged on a wind tunnel wall plate of a test area, the single-point measuring device is positioned on the inner side of the wind tunnel wall plate of the test area, the single-point measuring device at least has the motion capacities of X direction and Y direction, the sonic boom test model device is positioned in the middle of the test area, and the sonic boom test model device at least has the motion capacities of X direction, Y direction and pitching direction;
The single-point measuring device comprises single-point measuring equipment (2), a single-point supporting device (3), a single-point motion control mechanism (4) and reference measuring equipment (5), wherein the single-point supporting device (3) is arranged between the single-point measuring equipment (2) and the single-point motion control mechanism (4), the single-point motion control mechanism (4) is fixedly arranged on a wind tunnel wallboard of a test area, the single-point motion control mechanism (4) at least has the capability of controlling the X-direction and Y-direction motions of the single-point measuring equipment (2), and the reference measuring equipment (5) is fixedly arranged on the wind tunnel wallboard which is not influenced by a model wave system;
the test device comprises the following test modes in different forms:
mode 1, carrying out an acoustic explosion test according to a model moving method by using a single-point measuring device alone;
Mode 2, carrying out an acoustic explosion test by using a single-point measuring device independently according to a device moving method;
Mode 3, carrying out acoustic explosion test by using the parallel measuring device alone;
mode 4, carrying out an acoustic explosion test by taking the parallel measuring device as a main and single-point measuring device as an auxiliary;
Mode 5, carrying out an acoustic explosion test by using the single-point measuring device and the parallel measuring device at the same time;
in the embodiment 4, the test method is as follows:
step a, adjusting the distance between the model and the parallel measuring device in the Y direction according to the planned test working condition;
B, the reference measuring equipment of the single-point measuring device is arranged at a fixed position of the wind tunnel wall plate, and the position is ensured not to be influenced by the model and the wall wave system;
Step c, starting the wind tunnel and establishing an ultrasonic flow field;
Step d, controlling the model to move in a step mode along the X direction of the wind tunnel, wherein model influence areas corresponding to steps are all in a measurement interval of the parallel measurement device, and pressure data corresponding to the influence of the model influence areas are acquired by the parallel measurement device;
Step e, in the step d, simultaneously, single-point measuring equipment of the single-point measuring device moves at the same step interval as the model, corresponding pressure data are collected, and meanwhile, interference-free incoming flow pressure data are collected by reference to the measuring equipment;
f, after the step d is finished, controlling the model to move along the X direction until the model wave system influence area is far away from the position of the parallel measuring device, wherein the data collected by the parallel measuring device can be regarded as interference-free data;
step g, in the step f, the single-point measuring equipment synchronously moves according to the model, and acquires corresponding pressure data, and meanwhile, the reference measuring equipment acquires interference-free incoming flow pressure data;
Step h, closing the wind tunnel;
in the embodiment 5, the test method is as follows:
Step a, according to the planned test working condition, the distance between the model and the parallel measuring device in the Y direction is adjusted, and at the moment, the distance between the single-point measuring equipment of the single-point measuring device and the model in the Y direction is also determined;
B, the reference measuring equipment of the single-point measuring device is arranged at a fixed position of the wind tunnel wall plate, and the position is ensured not to be influenced by the model and the wall wave system;
Step c, adjusting the position of the single-point measuring equipment in the axial direction, keeping the single-point measuring equipment still during the test, and ensuring that the complete pressure distribution data of the wave system influence area can be obtained when the model moves along the X direction;
step d, starting the wind tunnel and establishing an ultrasonic flow field;
step e, controlling the model to move in a step mode along the X direction of the wind tunnel, wherein model influence areas corresponding to steps are all in a measurement interval of the parallel measurement device, and pressure data corresponding to the influence of the model influence areas are acquired by the parallel measurement device; simultaneously, the non-interference incoming flow pressure data is acquired by single-point measuring equipment and reference measuring equipment;
F, after the step e is finished, controlling the model to move along the X direction until the model wave system influence area is far away from the position of the parallel measuring device, wherein the data collected by the parallel measuring device can be regarded as interference-free data;
And g, closing the wind tunnel.
2. The combined acoustic explosion testing device suitable for a large supersonic wind tunnel according to claim 1, wherein: the acoustic explosion test model device comprises an acoustic explosion test model (6), a model supporting device (7) and a model motion control mechanism (8), wherein the model supporting device (7) is arranged between the acoustic explosion test model (6) and the model motion control mechanism (8), and the model motion control mechanism (8) at least has the capability of controlling the acoustic explosion test model (6) to move in the X direction, the Y direction and the pitching direction.
3. The combined acoustic explosion testing device suitable for a large supersonic wind tunnel according to claim 1, wherein: the parallel measuring device (1) and the single-point measuring device are symmetrically arranged.
4. The combined acoustic explosion testing device suitable for a large supersonic wind tunnel according to claim 1, wherein: in the above-described mode 1, the test method is as follows:
step a, according to the planned test working condition, the distance between the model and the single-point measuring device in the Y direction is adjusted;
B, the reference measuring equipment of the single-point measuring device is arranged at a fixed position of the wind tunnel wall plate, and the position is ensured not to be influenced by the model and the wall wave system;
Step c, starting the wind tunnel and establishing an ultrasonic flow field;
step d, the single-point measuring equipment of the single-point measuring device keeps a fixed position, the model moves along the X direction for a distance, during which the model wave system influence is scanned across the single-point measuring equipment in sequence, and corresponding pressure data are acquired by the single-point measuring equipment; meanwhile, the interference-free incoming flow pressure data are acquired by reference measuring equipment;
and e, closing the wind tunnel.
5. The combined acoustic explosion testing device suitable for a large supersonic wind tunnel according to claim 1, wherein: in the above-described mode 2, the test method is as follows:
step a, according to the planned test working condition, the distance between the model and the single-point measuring device in the Y direction is adjusted;
B, the reference measuring equipment of the single-point measuring device is arranged at a fixed position of the wind tunnel wall plate, and the position is ensured not to be influenced by the model and the wall wave system;
Step c, starting the wind tunnel and establishing an ultrasonic flow field;
Step d, the model keeps a fixed position, single-point measuring equipment of the single-point measuring device moves along the X direction to pass through an acoustic explosion signal influence area of the model, and corresponding pressure data are acquired by the single-point measuring equipment; meanwhile, the interference-free incoming flow pressure data are acquired by reference measuring equipment;
and e, closing the wind tunnel.
6. The combined acoustic explosion testing device suitable for a large supersonic wind tunnel according to claim 1, wherein: in the above-described mode 3, the test method is as follows:
step a, adjusting the distance between the model and the parallel measuring device in the Y direction according to the planned test working condition;
Step b, starting the wind tunnel and establishing an ultrasonic flow field;
Step c, controlling the model to move in a step mode along the X direction of the wind tunnel, wherein model influence areas corresponding to steps are all in a measurement interval of the parallel measurement device, and pressure data corresponding to the influence of the model influence areas are acquired by the parallel measurement device;
step d, controlling the model to move along the X direction until a model wave system influence area is far away from the position of the parallel measuring device, wherein the data acquired by the parallel measuring device can be regarded as interference-free data;
and e, closing the wind tunnel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410194980.7A CN117760681B (en) | 2024-02-22 | 2024-02-22 | Combined type acoustic explosion test device and method suitable for large supersonic wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410194980.7A CN117760681B (en) | 2024-02-22 | 2024-02-22 | Combined type acoustic explosion test device and method suitable for large supersonic wind tunnel |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117760681A CN117760681A (en) | 2024-03-26 |
| CN117760681B true CN117760681B (en) | 2024-05-31 |
Family
ID=90314783
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202410194980.7A Active CN117760681B (en) | 2024-02-22 | 2024-02-22 | Combined type acoustic explosion test device and method suitable for large supersonic wind tunnel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117760681B (en) |
Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7302839B1 (en) * | 2006-06-22 | 2007-12-04 | Cessna Aircraft Company | Method and system for gathering pressure signature data using a scaled model in a wind tunnel |
| CN107074345A (en) * | 2014-08-14 | 2017-08-18 | 湾流航空航天公司 | System and method for controlling the pressure field around airborne vehicle in-flight |
| CN208818458U (en) * | 2018-11-15 | 2019-05-03 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of space near field sonic boom feature high precision measuring device |
| KR102009845B1 (en) * | 2018-03-08 | 2019-08-12 | 국방과학연구소 | Wind-tunnel test device for flow through type vehicle and wind-tunnel test method using thereof |
| RU2697569C1 (en) * | 2018-11-29 | 2019-08-15 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Device for investigating near field of model pressure in a wind tunnel |
| CN110132528A (en) * | 2019-06-27 | 2019-08-16 | 中国空气动力研究与发展中心高速空气动力研究所 | A temporary supersonic wind tunnel sonic boom measurement test device and measurement method |
| CN209841336U (en) * | 2019-06-27 | 2019-12-24 | 中国空气动力研究与发展中心高速空气动力研究所 | A test device for measuring and testing the sonic boom in a temporary supersonic wind tunnel |
| CN110686858A (en) * | 2019-11-07 | 2020-01-14 | 中国空气动力研究与发展中心 | Sound explosion measurement wind tunnel test data processing method |
| CN111103117A (en) * | 2020-03-18 | 2020-05-05 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Low-speed wind tunnel integration direction dynamic pressure combination probe measuring device |
| CN210487222U (en) * | 2019-10-28 | 2020-05-08 | 中国航空工业集团公司沈阳空气动力研究所 | Jet flow model sonic explosion characteristic wind tunnel test device |
| CN210603820U (en) * | 2019-11-01 | 2020-05-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Continuous pressure distribution measuring device in air inlet channel for hypersonic wind tunnel |
| CN218646558U (en) * | 2022-12-20 | 2023-03-17 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Wind tunnel dynamic pressure measuring device |
| CN116952523A (en) * | 2023-09-12 | 2023-10-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Near-field acoustic explosion signal optical measurement method based on velocity field |
| CN117147093A (en) * | 2023-10-30 | 2023-12-01 | 中国航空工业集团公司沈阳空气动力研究所 | Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft |
| CN117147090A (en) * | 2023-10-30 | 2023-12-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Device and method for adjusting position and posture of pressure measuring rail in acoustic explosion test |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7546977B2 (en) * | 2003-07-03 | 2009-06-16 | Lockheed-Martin Corporation | Passive aerodynamic sonic boom suppression for supersonic aircraft |
| US8833153B2 (en) * | 2012-09-20 | 2014-09-16 | The Boeing Company | Correction of pressure signals measured during supersonic wind tunnel testing |
| US10146903B2 (en) * | 2015-11-11 | 2018-12-04 | The Boeing Company | High fidelity and high efficiency method for sonic boom predictions in supersonic flights |
-
2024
- 2024-02-22 CN CN202410194980.7A patent/CN117760681B/en active Active
Patent Citations (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7302839B1 (en) * | 2006-06-22 | 2007-12-04 | Cessna Aircraft Company | Method and system for gathering pressure signature data using a scaled model in a wind tunnel |
| CN107074345A (en) * | 2014-08-14 | 2017-08-18 | 湾流航空航天公司 | System and method for controlling the pressure field around airborne vehicle in-flight |
| KR102009845B1 (en) * | 2018-03-08 | 2019-08-12 | 국방과학연구소 | Wind-tunnel test device for flow through type vehicle and wind-tunnel test method using thereof |
| CN208818458U (en) * | 2018-11-15 | 2019-05-03 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of space near field sonic boom feature high precision measuring device |
| RU2697569C1 (en) * | 2018-11-29 | 2019-08-15 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Device for investigating near field of model pressure in a wind tunnel |
| CN209841336U (en) * | 2019-06-27 | 2019-12-24 | 中国空气动力研究与发展中心高速空气动力研究所 | A test device for measuring and testing the sonic boom in a temporary supersonic wind tunnel |
| CN110132528A (en) * | 2019-06-27 | 2019-08-16 | 中国空气动力研究与发展中心高速空气动力研究所 | A temporary supersonic wind tunnel sonic boom measurement test device and measurement method |
| CN210487222U (en) * | 2019-10-28 | 2020-05-08 | 中国航空工业集团公司沈阳空气动力研究所 | Jet flow model sonic explosion characteristic wind tunnel test device |
| CN210603820U (en) * | 2019-11-01 | 2020-05-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Continuous pressure distribution measuring device in air inlet channel for hypersonic wind tunnel |
| CN110686858A (en) * | 2019-11-07 | 2020-01-14 | 中国空气动力研究与发展中心 | Sound explosion measurement wind tunnel test data processing method |
| CN111103117A (en) * | 2020-03-18 | 2020-05-05 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Low-speed wind tunnel integration direction dynamic pressure combination probe measuring device |
| CN218646558U (en) * | 2022-12-20 | 2023-03-17 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Wind tunnel dynamic pressure measuring device |
| CN116952523A (en) * | 2023-09-12 | 2023-10-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Near-field acoustic explosion signal optical measurement method based on velocity field |
| CN117147093A (en) * | 2023-10-30 | 2023-12-01 | 中国航空工业集团公司沈阳空气动力研究所 | Wind tunnel test measuring device for acoustic explosion characteristics of low acoustic explosion supersonic civil aircraft |
| CN117147090A (en) * | 2023-10-30 | 2023-12-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Device and method for adjusting position and posture of pressure measuring rail in acoustic explosion test |
Non-Patent Citations (1)
| Title |
|---|
| "基于探针的声爆测量风洞试验技术研究";杨洋;《实验流体力学》;20231231;第37卷(第6期);92-100 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117760681A (en) | 2024-03-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103674223B (en) | noise source testing device, system and method | |
| CN102818738B (en) | Rebound apparatus calibrating device and using method thereof | |
| CN103674232B (en) | Sound intensity acquisition device for testing noise source | |
| CN104751918A (en) | Device and method for measuring deformation of fuel assembly | |
| CN103529126A (en) | Ultrasonic automatic detection system and detection method of workpiece with clearance gridding-shaped multi-slope curve surfaces | |
| CN118332919A (en) | Building curtain wall engineering detection method | |
| CN103149277A (en) | Phased array ultrasound detecting scanning path optimizing method based on defect detection rate | |
| CN108519444A (en) | A kind of accurate measurement method of contact line defective locations | |
| CN107270814A (en) | A kind of prefabricated assembled wind-tunnel high accuracy install control method | |
| CN102297900B (en) | Multichannel parallel and synchronous acquisition method for ultrasonic pulse signal | |
| CN117760681B (en) | Combined type acoustic explosion test device and method suitable for large supersonic wind tunnel | |
| CN103994819A (en) | Engine noise test method | |
| CN102944609B (en) | Complete multichannel white body welding spot detection system | |
| CN104314801A (en) | Test system of propulsive water-jet pump based on echoic environment and test method thereof | |
| CN206832987U (en) | A kind of parameters,acoustic measurement apparatus of side scan sonar | |
| CN105866255A (en) | Through type ultrasonic rapid detecting die and detecting method thereof | |
| CN218995261U (en) | Nondestructive testing device for concrete filled steel tube excitation sound measurement | |
| CN111811425A (en) | Device and method for detecting shallow holes of skin of aviation composite material honeycomb panel | |
| CN110018391A (en) | GIS fault accurate positioning method and positioning system based on vibration signals | |
| CN113092588A (en) | Ultrasonic phased array detection device and detection method | |
| CN116465635B (en) | An engine condition detection system and method | |
| CN115824083A (en) | A Coordinate Measurement Method of High Pressure Closed Integral Blade Ring | |
| CN203659445U (en) | Fuel assembly deformation measuring device | |
| CN116298543A (en) | Automatic trolley and drawing method for drawing electromagnetic map of inner and outer fields | |
| CN115752517A (en) | A method and system for checking movement accuracy of inertial navigation equipment |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |