CN112254591A - Testing device for gas detonation driven ultra-high-speed emission - Google Patents
Testing device for gas detonation driven ultra-high-speed emission Download PDFInfo
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- CN112254591A CN112254591A CN202011131932.1A CN202011131932A CN112254591A CN 112254591 A CN112254591 A CN 112254591A CN 202011131932 A CN202011131932 A CN 202011131932A CN 112254591 A CN112254591 A CN 112254591A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
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Abstract
The invention discloses a testing device for gas detonation driven ultra-high speed launching, which comprises a model and a target chamber measuring section at a certain distance position from the model, wherein four observation windows, namely an A window, a B window, a C window and a D window, are sequentially arranged at the target chamber measuring section at certain intervals and are respectively connected with a delay controller, a laser system and a camera are arranged at the position of the D window, a projectile sequentially passes through the detection point A window, the B window and the C window, the flying speed is calculated by calculating the flying time between adjacent detection windows, then the time needing to be delayed is calculated, the delay controller outputs the delay time to control the laser system to flash, and the camera captures a schlieren image of the projectile passing through the D window. The stability of the system is higher; the sensitivity is better, and the phenomenon of no triggering is avoided; the experimental data is richer, and the analysis by experimenters is convenient; the time can be corrected manually and accurately.
Description
Technical Field
The invention belongs to the technical field of ultrahigh-speed projectile/model test experimental equipment, and particularly relates to a testing device for ultrahigh-speed launching driven by gas detonation.
Background
The testing device for gas detonation driven ultra-high speed launching is used for measuring the flow field, attitude and speed of a flight model, and needs to establish a measurement and control system based on a plurality of sets of shadow (schlieren) photographic systems and configured with a model detection and reference system on a target chamber measuring section to obtain test data and pictures.
The method generally adopted in the prior art is a single observation window principle, the flying speed is calculated by calculating the distance of the AB point of the projectile/the flying time of the AB point, and then the time needing to be delayed is calculated. But the system has two observation windows, and the system can not work normally under the condition that any one observation window is failed.
The principle of the particle detector generally adopted in the prior art is that light emitted by a laser is converted into parallel light after passing through a convex lens, then a light spot is shrunk through a convex lens at a receiving end, a photoelectric detector is used for outputting an analog signal, and the analog signal passes through a comparator to output a pulse, namely a projectile passes through an output pulse (as shown in the attached figure 1 of the specification).
And detecting the falling edge by using a single chip microcomputer, and considering the time of the falling edge as the time of the projectile passing through the window.
In use, some drawbacks of the prior art are found:
1. low sensitivity and often no triggering.
The projectile has very high speed, and the change of light intensity caused in the process of flying quickly is too small, so that the detection system cannot detect the projectile, the projectile is not triggered, and the projectile cannot take a picture normally.
2. The false triggering condition is more.
Violent vibration exists during the bombing, and although corresponding measures are taken structurally, the light intensity change caused by the change of the light path cannot be avoided, so that the detector is triggered by mistake.
The bombing gas flow and contaminant gases cause the photodetector to falsely detect the signal.
3. The data for analysis is not sufficient after testing.
The signals acquired by the acquisition card are not enough to completely analyze the experimental process, and the reason of the test failure cannot be analyzed from the signals of the detector when the test fails. The accuracy of the measurement cannot be improved from the signal analysis when the experiment is normal.
In summary, the original system in the prior art only calculates the velocity, and the projectile does not move at a perfect uniform velocity in the horizontal direction under the condition that the vacuum degree is not high enough or the bombing gas enters the projectile flight space. Therefore, how to redesign the testing device and the detection method, and improve the testing principle, the invention provides the testing system which has high sensitivity, can accurately analyze the passing of the projectile from the complex working conditions on the spot and can store enough information, and has important practical significance.
Disclosure of Invention
Aiming at the problems in the prior art, the invention aims to provide a testing device for gas detonation driven ultra-high-speed emission.
The technical scheme adopted by the invention is as follows:
a testing device for ultra-high-speed launching driven by gas detonation comprises a model and a target chamber measuring section at a certain distance from the model, wherein four observation windows, namely a window A, a window B, a window C and a window D, are sequentially arranged at the target chamber measuring section at certain intervals and are respectively connected with a delay controller, a laser system and a camera are arranged at the window D, projectiles sequentially pass through the window A, the window B and the window C at a detection point, the flying speed is calculated by calculating the flying time between adjacent detection windows, the time needing to be delayed is calculated, the delay time is output by the delay controller to control the laser system to flash, and schlieren images of the projectiles passing through the window D are captured by the camera.
Further, the velocity calculation formula of the target chamber measurement section and the acceleration calculation formula of the projectile are as follows:
wherein v iscVelocity of the projectile at the C window, vaProjectile velocity at window A, t3The time required for the projectile to travel from the initial position to the C window, t1The time required for the projectile to travel from the initial position to the window A, tcdThe time required for the projectile to travel from the C window to the D window; a is the acceleration of the projectile; scdThe distance from the C window to the D window is traveled.
Furthermore, the three windows of the window A, the window B and the window C of the target chamber measuring section are triggered normally, or under the condition that any one single window is invalid, the speed is calculated, and the calculation and the delay are output according to the acceleration calculated by the previous stage.
Furthermore, the laser system comprises a resonant cavity laser and a photoelectric detector, the laser intensity output by the resonant cavity laser is in sine fluctuation, and a signal detected on the photoelectric detector is sine wave.
Furthermore, the laser system is also provided with a comparator, and the sine wave detected on the photoelectric detector is converted into square wave after passing through the comparator.
Furthermore, the laser system adopts the FPGA to detect the time of the projectile passing through the window, when the projectile flies through, the pulse width of the square wave changes, and the FPGA is adopted to analyze the pulse width of the square wave to obtain the time of the projectile flying through.
Furthermore, the laser system is also provided with an oscilloscope card, the oscilloscope card is used for collecting and storing, and the trigger signal is used for controlling the storage starting time of the oscilloscope card. The method specifically comprises the following steps: the waveforms are stored by using a 50M oscilloscope card, and are used as trigger signals of the oscilloscope card when the oscilloscope card is bombed, and the trigger length can be flexibly set according to the test time, so that the oscilloscope card is convenient for a user to analyze.
Furthermore, the model adopts a two-section structural design and comprises a camera system used for imaging, the camera system comprises a laser light source, a horizontal schlieren instrument, a vertical schlieren instrument, a collimating mirror, a reference flange, window glass, a camera and a camera controller, the collimating mirror is installed at the window glass through the reference flange, the horizontal schlieren instrument and the vertical schlieren instrument are installed through the collimating mirror, the laser light source is connected with the horizontal schlieren instrument through an optical fiber in the horizontal direction, and the laser light source is connected with the vertical schlieren instrument through an optical fiber in the vertical direction.
Furthermore, the model adopts a two-section structural design and comprises a flash control and measurement system and a processing and acquisition system, wherein the flash control and measurement system comprises a laser light source, a photoelectric detector and a controller, the processing and acquisition system comprises a PXI acquisition system, an industrial personal computer and a switch, the photoelectric detector is connected with the controller through a coaxial cable, and the controller outputs a control signal to control the laser power source to flash; the controller and the camera controller are communicated through a local area network and are connected to the switch, the switch is connected with the industrial personal computer, and pictures shot by the camera are uploaded to the industrial personal computer through the local area network.
The invention has the beneficial effects that:
by analyzing the integral structure of the system, aiming at the defects of the prior art, the invention adopts a two-section design in space and replaces a light source (resonant laser) used for detection, and has great progress in the following points compared with the prior art:
1) the stability is higher, and the system just fails under the condition that at least two windows in the three windows in the target chamber measurement section fail, and the probability of this kind of condition is only 4.2%, has greatly improved the stability of system.
2) The sensitivity is better, the phenomenon of no triggering is avoided, even if the light intensity change is too small in the process of rapidly flying the projectile, the detection system can still detect the projectile and avoid the non-triggering, and therefore normal photographing is achieved.
3) The experimental data are richer, the analysis of experimenters is convenient, after a new light source is adopted, a signal detected on a photoelectric detector is a sine wave, the sine wave is converted into a square wave after a comparator is used, the pulse width of the square wave is analyzed by using an FPGA (field programmable gate array), and the bullet flying time can be obtained more accurately.
4) The method has the advantages of quick error correction, convenient system maintenance, easy identification of which link the error occurs through waveform analysis when the error occurs in the experiment, and artificial accurate time correction through analysis of the pulse width variation waveform of the projectile passing through the window.
Drawings
FIG. 1 is a prior art output waveform of a projectile pass;
FIG. 2 is a schematic diagram of the structure of the device for the measurement section of the model and the target chamber according to the present invention;
FIG. 3 is a waveform of the output of the present invention without a projectile passing therethrough;
FIG. 4 is a graph of the output waveform with a projectile passing therethrough in accordance with the present invention;
FIG. 5 is a schematic diagram of the overall structure of the testing device for ultra-high speed emission driven by gas detonation in the present invention;
FIG. 6 is a schematic diagram of the field installation of the testing device for ultra high speed gas detonation driven launching in the present invention;
1. a horizontal schlieren instrument a; 2. a photodetector a; 3. a controller; 4. a control signal; 5. a laser light source a; 6. a laser light source b; 7. a horizontal schlieren instrument b; 8. a horizontally oriented optical fiber a; 9. a vertically oriented optical fiber a; 10. a photodetector b; 11. a laser light source c; 12. an optical fiber b; 13. a vertically oriented optical fiber b; 14. a collimating mirror; 15. a reference flange a; 16. a window glass a; 17. a window glass b; 18. a reference flange b; 19. a switch; 20. a data acquisition system connected to the control room; 21. vertical schlieren instrument.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
Example 1
As shown in figure 2, the testing device for gas detonation driven ultra-high speed launching comprises a model and a target chamber measuring section at a certain distance from the model, wherein four observation windows, namely a window A, a window B, a window C and a window D, are sequentially arranged at the target chamber measuring section at certain intervals and are respectively connected with a delay controller, a laser system and a camera are arranged at the window D, a projectile sequentially passes through the windows A, B and C at detection points, the flying speed is calculated by calculating the flying time between adjacent detection windows, then the time needing to be delayed is calculated, the delay controller outputs the delay time to control the laser system to flash, and the camera captures a schlieren image of the projectile passing through the window D.
As shown in fig. 2, if the three windows are triggered normally, not only the velocity but also the acceleration of the projectile can be calculated, so that the calculation of the delay time between CDs is more precise.
Wherein v iscVelocity of the projectile at the C window, vaProjectile velocity at window A, t3The time required for the projectile to travel from the initial position to the C window, t1The time required for the projectile to travel from the initial position to the window A, tcdThe time required for the projectile to travel from the C window to the D window; a is the acceleration of the projectile; scdThe distance from the C window to the D window is traveled.
And the speed can still be calculated under the condition that the single window is invalid, and calculation and output delay are carried out according to the acceleration calculated by the previous stage, so that the stability of the system is improved.
According to the test, the probability of failure of each window is about 1/8, a failure system in any one of two windows fails, the probability of system failure is 15/64 (23.4%), the probability of system failure is only 22/512 (4.2%) under the condition that at least two of three windows fail, the stability of the system is greatly improved, the stability of the system can be continuously improved under the condition that the windows are continuously increased, and three windows are enough in consideration of comprehensive cost and construction difficulty.
As shown in fig. 3 and 4: the pulse width change of the passing shot has detailed characteristics, and can be easily distinguished from the pulse width change of vibration and detonation gas interference. As shown in fig. 3 and 4, the pulse passed by the projectile becomes gradually larger and smaller, and the maximum pulse width can be selected as a timing time point (at the time the projectile is in the center of the window) by using the FPGA, so that the measurement accuracy is improved. The pulse change caused by vibration is large and small, and the time and amplitude of the pulse width change caused by the bombing gas are very large, so that the signal characteristics are obvious and can be easily distinguished without calculation. The system sensitivity is improved, and the probability of system false triggering is reduced.
The laser system uses a resonant cavity laser, and the laser light intensity output by the laser fluctuates in a sine wave mode. After the novel light source is adopted, a signal detected on the photoelectric detector is a sine wave, the sine wave is converted into a square wave by using the comparator, when the bullet flies, the pulse width of the square wave is changed, the pulse width of the square wave is analyzed by using the FPGA, and the bullet flying time can be obtained more accurately. The FPGA is adopted to distinguish the pulse width, the resolution ratio can reach 1ns, and the sensitivity is greatly improved.
The laser system is also provided with an oscilloscope card, the oscilloscope card is used for collecting and storing, and the trigger signal is used for controlling the storage starting time of the oscilloscope card, so that the analysis by a user is facilitated.
The waveforms are stored by using a 50M oscilloscope card, and the waveforms are used as trigger signals of the oscilloscope card when the oscilloscope card is bombed, and the trigger length can be flexibly set according to the test time.
Example 2
On the basis of the embodiment, different from the embodiment 1, the model of the testing device for gas detonation driven ultra-high-speed emission adopts a two-stage structural design, comprises a camera system used for imaging, a measurement and control system for controlling flash and a processing and acquisition system,
the photographing system comprises a laser light source, a horizontal schlieren instrument, a vertical schlieren instrument, a collimating mirror, a reference flange, window glass, a camera and a camera controller, wherein the collimating mirror is installed at the window glass through the reference flange, the horizontal schlieren instrument and the vertical schlieren instrument are installed through the collimating mirror, the laser light source is connected with the horizontal schlieren instrument through an optical fiber in the horizontal direction, and the laser light source is connected with the vertical schlieren instrument through an optical fiber in the vertical direction;
the flash control measurement and control system comprises a laser light source, a photoelectric detector and a controller,
the processing and collecting system comprises a PXI collecting system, an industrial personal computer and a switch,
the photoelectric detector is connected with the controller through a coaxial cable, and the controller outputs a control signal to control the laser power supply to flash; the controller and the camera controller are communicated through a local area network and are connected to the switch, the switch is connected with the industrial personal computer, and pictures shot by the camera are uploaded to the industrial personal computer through the local area network.
As shown in fig. 5, the testing device for gas detonation driven ultra-high speed launching is divided into two ends, the front end is an explosion-discharging section, the rear end is a testing end, and the front end is provided with a horizontal schlieren instrument a1, a photoelectric detector a2, a controller 3, a control signal 4 and a laser light source a 5; the rear end is provided with a laser light source b6, a horizontal schlieren instrument b7, a horizontal optical fiber a8, a vertical optical fiber a9, a photoelectric detector b10, a laser light source c11, an optical fiber b12, a vertical optical fiber b13, a collimating mirror 14, a reference flange a15, window glass a16, window glass b17, a reference flange b18, a switch 19, a data acquisition system 20 connected to a control room and a vertical schlieren instrument 21; when the detonation projectile passes through the explosion unloading section, the impact of the detonation gas on the experiment can be effectively isolated, the measurement is carried out, important information such as an initial speed value can be provided for a later-stage test section, and the flight attitude and the schlieren image of the projectile at the explosion unloading section are shot.
As shown in fig. 6, 8 observation windows are sequentially arranged at the same horizontal line from front to back, each observation window is respectively provided with a laser light curtain, and corresponding laser, camera power supply, camera controller, photoelectric converter and delay trigger, in the control chamber an industrial control computer and a local area network are set, the projectiles pass through windows A, B and C … … H of the detection points in sequence through the industrial personal computer, the flying speed is calculated by calculating the flying time between adjacent detection windows, then calculating the time needed to be delayed, outputting the delay time through the delay controller to control the laser of the laser system to flash, turning on the power supply of the camera, controlling the camera to take pictures along the vertical direction and the horizontal direction by the camera controller, and (4) capturing a schlieren image of the shot passing through the window through the camera, and transmitting the schlieren image shot by the camera to the industrial personal computer through the local area network.
The above description is not meant to be limiting, it being noted that: it will be apparent to those skilled in the art that various changes, modifications, additions and substitutions can be made without departing from the true scope of the invention, and these improvements and modifications should also be construed as within the scope of the invention.
Claims (9)
1. A testing device for ultra-high-speed launching driven by gas detonation is characterized by comprising a model and a target chamber measuring section arranged at a certain distance from the model, wherein four observation windows, namely an A window, a B window, a C window and a D window, are sequentially arranged at the target chamber measuring section at certain intervals and are respectively connected with a delay controller, a laser system and a camera are arranged at the D window, projectiles sequentially pass through the A window, the B window and the C window at detection points, the flying speed is calculated by calculating the flying time between adjacent detection windows, the time needing to be delayed is calculated, the delay controller outputs the delay time to control the laser system to flash, and schlieren images of the projectiles passing through the D window are captured by the camera.
2. The apparatus for testing ultra high speed launching driven by gas detonation as claimed in claim 1, wherein the velocity calculation formula of the target chamber measurement section and the acceleration calculation formula of the projectile are as follows:
wherein v iscVelocity of the projectile at the C window, vaProjectile velocity at window A, t3The time required for the projectile to travel from the initial position to the C window, t1The time required for the projectile to travel from the initial position to the window A, tcdThe time required for the projectile to travel from the C window to the D window; a is the acceleration of the projectile; scdThe distance from the C window to the D window is traveled.
3. The device for testing ultra-high speed emission by gas detonation drive according to claim 2, wherein the three windows of the window A, the window B and the window C of the target chamber measuring section are triggered normally, or in case of failure of any one of the windows, the speed is calculated, and the calculation and the output delay are performed according to the acceleration calculated by the previous stage.
4. The apparatus as claimed in claim 1, wherein the laser system comprises a resonant cavity laser and a photodetector, the laser intensity outputted from the resonant cavity laser fluctuates sinusoidally, and the signal detected by the photodetector is sinusoidal.
5. The device for testing ultra-high speed emission driven by detonation of gas as claimed in claim 4, wherein the laser system is further provided with a comparator, and the sine wave detected by the photodetector is converted into square wave after passing through the comparator.
6. The device for testing the ultra-high speed launching of the detonation-driven gas as claimed in claim 5, wherein the laser system employs the FPGA to detect the time of the projectile passing through the window, when the projectile flies through, the pulse width of the square wave changes, and the FPGA is used to analyze the pulse width of the square wave to obtain the time of the projectile flying through.
7. The device for testing ultra-high speed emission driven by gas detonation as claimed in any one of claims 4-6, wherein the laser system is further provided with an oscilloscope card, the oscilloscope card is used for collecting and storing the data, and the trigger signal is used for controlling the storage start time of the oscilloscope card.
8. The device for testing ultra-high speed emission of gas detonation drive according to any one of claims 1-6, wherein the model is designed in a two-stage structure, and comprises a camera system for imaging, the camera system comprises a laser source, a horizontal schlieren instrument, a vertical schlieren instrument, a collimating mirror, a reference flange, a window glass, a camera and a camera controller, the collimating mirror is mounted at the window glass through the reference flange, the horizontal schlieren instrument and the vertical schlieren instrument are mounted through the collimating mirror, the laser source is connected with the horizontal schlieren instrument through an optical fiber in the horizontal direction, and the laser source is connected with the vertical schlieren instrument through an optical fiber in the vertical direction.
9. The testing device of the ultra-high-speed emission driven by the gas detonation as claimed in claim 8, wherein the model is designed in a two-stage structure and comprises a flash control and measurement system and a processing and acquisition system, the flash control and measurement system comprises a laser light source, a photoelectric detector and a controller, the processing and acquisition system comprises a PXI acquisition system, an industrial personal computer and a switch, wherein the photoelectric detector and the controller are connected through a coaxial cable, and the controller outputs a control signal to control the flash of the laser power supply; the controller and the camera controller are communicated through a local area network and are connected to the switch, the switch is connected with the industrial personal computer, and pictures shot by the camera are uploaded to the industrial personal computer through the local area network.
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| CN113670118A (en) * | 2021-09-18 | 2021-11-19 | 中国工程物理研究院流体物理研究所 | Method, device and system for synchronizing projectile and flash |
| CN114166122A (en) * | 2021-12-02 | 2022-03-11 | 中国工程物理研究院流体物理研究所 | Automatic target adjusting device |
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