CN111175435A - Device and method for measuring propagation characteristics of detonation waves - Google Patents
Device and method for measuring propagation characteristics of detonation waves Download PDFInfo
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Abstract
The invention provides a measuring device for deflagration wave propagation characteristics, which comprises a shock tube, wherein a plurality of pressure probes and flame detectors are sequentially arranged on the side wall of the shock tube along the length direction of the shock tube, the flame detectors are connected with an ion-electric signal conversion circuit, and the pressure probes and the ion-electric signal conversion circuit are both connected with a data acquisition system. The flame detector of the deflagration wave propagation characteristic measuring device directly uses flame ions generated in the combustion reaction process to determine the position of the combustion wave, so that the measuring result of the combustion surface is more accurate and reliable; in addition, the device utilizes pressure probe and flame detector to realize shock wave face-burning wave face synchronous measurement, and because flame detector surveys the burning wave more accurate, makes the arrival time of measuring shock wave and burning wave more have the referential, can the same detonation wave of cross-section shock wave and the arrival time of burning wave of the same detonation wave of audio-visual observation, is favorable to audio-visual observation detonation wave propagation characteristic.
Description
Technical Field
The invention belongs to the technical field of deflagration experiments, and particularly relates to a device and a method for measuring transient deflagration state and propagation characteristics in a gas phase deflagration small scale.
Background
A deflagration wave is a combustion wave that propagates at subsonic speeds of several meters to several hundred meters per second. The detonation phenomenon widely exists in the nature, is the earliest physical phenomenon known by human beings, and is closely related to the development of human civilization. The detonation wave is composed of a shock wave generated by the pressure change of the front compressed air and a combustion surface generated by the chemical reaction at the rear (as shown in figure 1). Under ideal conditions, the precursor shock wave forms positive feedback to increase flame combustion efficiency, the combustion wave can be gradually accelerated, the distance between the combustion wave and the front shock wave is reduced, and when the combustion wave and the shock wave coincide, a more violent detonation phenomenon that the shock wave and the combustion wave are strongly coupled can be generated. The research of the propagation characteristics of the deflagration wave has great significance for knowing the deflagration wave, researching the process of converting deflagration into detonation, improving the evaluation capability of deflagration damage to combustible mixed gas, preventing the generation of deflagration and even detonation phenomena in the labor production process and reducing and avoiding the damage of deflagration phenomena to personnel and property.
In the conventional measurement of a deflagration wave, the arrival time of a shock wave is generally obtained by measuring the pressure with a pressure sensor, or the arrival time of a combustion surface is obtained by obtaining an optical fiber signal with an optical fiber, and the state of the deflagration wave is mostly estimated by measuring the velocity of the shock wave or the velocity of the combustion wave.
A series of related products have been developed abroad. A related product of the pressure measurement system is the PREWAQ type explosive pressure wave test device of edison corporation of america (IDEASCIENCE). The device utilizes optical fibers to measure the detonation velocity, such as the earliest fiber detonation velocity instrument being the fiber detonation velocity instrument of the Contini-Torto (Kontinito) of Switzerland, the VOD-8 fiber detonation velocity instrument of the Edison company of America. But since foreign instrument manufacturers block the technology in China, the product price is high.
In the aspect of domestic pressure measurement, Zhang Shi faithful and the like adopt heat flow signals as signal triggering sources to realize shock wave velocity transient measurement, and a shock wave velocity measurement system is obtained, can only measure the arrival time of shock waves but not the arrival time of combustion waves, and therefore cannot be used for researching the propagation law of detonation waves.
In the aspect of domestic optical signal measurement, ginger estuarine and the like at the university of north and middle have tested the signal of the detonation velocity through the channel optical fiber, and therefore the arrival time of the combustion surface is obtained. However, when deflagration just occurs, the flame of the combustion surface is weak, the brightness is low, and the flame is not enough to trigger the optical fiber acquisition system to acquire the arrival signal of the combustion surface, so that the triggering time is late, the total observation of deflagration waves is delayed to a certain extent, and in the experimental process, the end part of the optical fiber is easy to deposit carbon, and the observation effect of the experiment is seriously influenced. In addition, as the combustion wave in the deflagration wave is integrally measured by adopting the optical fiber to have certain delay, the distance between the measured shock wave and the combustion wave has larger error compared with the real distance, and the measured distance has no reference, the existing optical fiber measurement technology cannot be used for synchronously measuring the shock wave and the combustion wave, so that the existing optical fiber measurement technology cannot be used for researching the propagation rule of the deflagration wave.
At present, for the current research on deflagration waves, no device exists for measuring and comparing shock waves and combustion waves generated by deflagration simultaneously so as to measure the propagation characteristics of deflagration waves.
Disclosure of Invention
An object of the present invention is to provide a measuring apparatus of propagation characteristics of a detonation wave, thereby solving the problems in the prior art.
In order to achieve the purpose, the invention provides a deflagration wave propagation characteristic measuring device which comprises a shock tube, wherein a high-energy igniter is arranged at one side end part of the shock tube, an air inlet and an air outlet are sequentially arranged on the side wall of the shock tube close to the high-energy igniter, the air inlet is connected with a gas mixing system, the air outlet is connected with a vacuum pump, a plurality of pressure probes and flame detectors are sequentially arranged on the side wall of the shock tube along the length direction of the shock tube, the flame detectors are connected with an ion-electric signal conversion circuit, and the pressure probes and the ion-electric signal conversion circuit are both connected with a data acquisition system.
The flame detector comprises a tungsten needle, a ceramic sleeve, a tetrafluoroethylene sleeve and a clamping sleeve adapter which are arranged from inside to outside in sequence and are spaced from each other.
The outer diameter of the tungsten needle is 0.5mm, and the length of the tungsten needle is 70 mm; the external diameter of ceramic bushing is 3mm, and length is 46mm to be equipped with two holes that are used for holding the tungsten needle, the downthehole diameter is 0.7mm, and the hole interval is 1mm, and is fixed through silica gel between tungsten needle and the ceramic bushing.
The ion-electric signal conversion circuit comprises a plurality of single circuits which are connected in parallel, each single circuit corresponds to one flame detector, each single circuit comprises a power supply, a first resistor, a capacitor and a shared resistor which are sequentially connected between the positive pole and the negative pole of the power supply, and a diode, a second resistor and an ion probe which are sequentially connected between one end of the first resistor, which is far away from the positive pole of the power supply, and the negative pole of the power supply, and the ion probe is connected with the tungsten needle of the flame detector.
The power supply and the shared resistor of the ion-electric signal conversion circuit are shared by a plurality of single circuits, and the rest parts are arranged in parallel with each other.
The number of the flame detectors is more than that of the pressure probes, and each pressure probe corresponds to one flame detector in the length direction of the shock tube.
The pressure probes are arranged on the upper side wall of the shock tube, and the number of the pressure probes is 8. The flame detectors are arranged on the lower side wall of the shock tube, and the number of the flame detectors is 10.
And a pressure gauge is arranged on the side wall of the shock tube far away from the high-energy igniter, and a stop valve is also connected between the shock tube and the pressure gauge.
In another aspect, the present invention provides a method for measuring propagation characteristics of a deflagration wave, including:
s1: building a measuring device according to the propagation characteristics of the detonation waves, and adding premixed gas through an air inlet of the measuring device;
s2: closing the air inlet and the air outlet of the gas generator, triggering a high-energy igniter, and igniting premixed gas to enable gas in the pipeline to deflagrate to generate deflagration waves;
s3: collecting shock wave signals of deflagration waves by using a pressure probe, and collecting combustion wave signals of the deflagration waves by using a flame detector;
s4: collecting shock wave signals collected by the pressure probes and combustion wave signals collected by the flame detectors by using a data collection system to obtain the time for the shock wave signals and the combustion wave signals to reach the pressure probes and the flame detectors;
s5: and (5) opening the air outlet after the experiment is finished.
The step S4 further includes: and calculating the speed of the combustion wave and the shock wave according to the time of the shock wave and the combustion wave signals reaching each pressure probe and the flame detector.
The deflagration wave propagation characteristic measuring device adopts the flame detector, the ion-electric signal conversion circuit and the data acquisition system to form a combustion wave acquisition system, the flame detector is contacted with flame to generate an ion signal which can generate weak current, and the converted electric signal can be acquired by the data acquisition system through the amplification of the ion-electric signal conversion circuit; in addition, the deflagration wave propagation characteristic measuring device realizes synchronous measurement of shock wave surface and combustion wave surface by utilizing the pressure probe and the flame detector, and the flame detector can measure the combustion wave more accurately, so that the time of arrival of the shock wave and the combustion wave is measured more referably, the time of arrival of the shock wave and the combustion wave of the same deflagration wave on the same section can be observed visually, the deflagration wave propagation characteristic can be observed visually, and the deflagration wave propagation rule can be revealed.
Drawings
FIG. 1 is a schematic structural view of a typical deflagration wave;
fig. 2 is a schematic configuration diagram of a measuring apparatus of propagation characteristics of a detonation wave according to an embodiment of the invention;
FIG. 3 is a schematic view of a flame detector of the deflagration wave propagation characteristic measuring apparatus shown in FIG. 2;
FIG. 4 is a circuit diagram of an ion-electric signal conversion circuit of the apparatus for measuring propagation characteristics of a deflagration wave as shown in FIG. 2
FIG. 5 is a waveform diagram of a combustion wave signal and a shockwave signal collected by a pressure probe and a flame detector.
Fig. 6 is a velocity-distance image of a combustion wave and a shock wave of a deflagration wave.
Detailed Description
The present invention will be further described with reference to the following specific examples. It should be understood that the following examples are illustrative only and are not intended to limit the scope of the present invention.
Fig. 2 shows a deflagration wave propagation characteristic measurement device according to an embodiment of the present invention, which utilizes a pressure sensor, and flame detector technology to synchronously and continuously measure the propagation characteristic of gas phase deflagration. This measuring device 10 of detonation wave propagation characteristic includes shock tube 1, one side tip of this shock tube 1 is equipped with high energy point firearm 11, produce the electric spark that the discharge energy is 40J with the single, shock tube 1 is close to and is equipped with air inlet 12 and gas outlet 13 on the lateral wall of high energy point firearm 11 in proper order, air inlet 12 links to each other with a gas mixing system, a combustible gas after being used for adding the premixing, a vacuum pump is connected to gas outlet 13, an air in the pipeline is taken out before the experiment, and take out the detonation product in the pipeline after the experiment, get rid of the influence of other factors. And a pressure gauge 14 is arranged on the side wall of the shock tube 1 far away from the high-energy igniter 11 and used for observing the pressure in the tube in real time. A stop valve is also connected between the shock tube 1 and the pressure gauge 14, and the stop valve is closed during experiments to prevent the pressure gauge from being damaged by high pressure. The side wall of the shock tube 1 is sequentially provided with a plurality of pressure probes 2 and flame detectors 3 along the length direction of the shock tube, the flame detectors 3 are connected with an ion-electric signal conversion circuit 4 (shown in figure 4), and the pressure probes 2 and the ion-electric signal conversion circuit 4 are both connected with a high-frequency data acquisition system (not shown in figure).
The shock tube 1 is a rigid pipeline and a stainless steel square pipeline with the length of 3m, and the pipe diameter of the pipeline is 65 mm.
The pressure probes 2 are arranged on the upper side wall of the shock tube 1, and the number of the pressure probes is 8. The flame detectors 3 are arranged on the lower side wall of the shock tube 1, and the number of the flame detectors is 10. The pressure probe 2 and the flame detector 3 can be arranged according to the size of experimental equipment and specific experimental requirements, the number of the pressure probes is not limited, and the pressure probes and the flame detectors can be expanded as required. The positions of the pressure probe 2 and the flame detector 3 can be changed or installed on the side wall of the shock tube 1 according to the specific situation of the experimental equipment, but the pressure probe 2 and the flame detector 3 need to be installed on the same section to obtain the time of the combustion wave and the shock wave reaching the same section to obtain the instantaneous characteristic of the deflagration wave. The number of the flame detectors 3 is more than that of the pressure probes 2, each pressure probe 2 corresponds to one of the flame detectors 3 in the length direction of the shock tube 1, namely, each pressure probe 2 and one of the flame detectors 3 are located on the same cross section perpendicular to the length direction of the shock tube 1, so that the time of arrival of the combustion wave and the shock wave at the same position can be obtained, and the propagation characteristic of the detonation wave can be observed. In this embodiment, the number of the flame detectors 3 is 2 more than that of the pressure probes 2, and the more flame detectors 3 are disposed at a position of the shock tube 1 close to the high-energy igniter 11.
The pressure probe 2 is a PCB pressure probe, the model number of the pressure probe is 113B24, and eight pressure probes are provided and are sequentially marked as P1, P2, … and P8 from left to right. The distances between the eight pressure probes 2 and the high-energy igniter 11 are respectively 0.8m,1m,1.2m,1.4m,1.6m,1.8m,2m and 2.55 m. Therefore, when the shock wave passes through the pressure probe 2, the pressure probe 2 generates a signal, a high-frequency data acquisition system is used for collecting the signal to obtain the arrival time of the shock wave, and the speed of the shock wave of each section can be calculated. The number and spacing of the pressure probes 2 can be determined by experimental observation needs. The pressure probe 2 is fixed on the shock tube 1 through a threaded hole of M20 specification and a cutting ferrule adapter of M20 specification which are arranged on the shock tube 1 at proper distances, a tetrafluoroethylene sleeve is sleeved on the cutting ferrule adapter, and a proper amount of silica gel is coated at the joint of the cutting ferrule adapter and the tetrafluoroethylene sleeve to ensure the air tightness of the device.
The number of the flame detectors 3 on the shock tube 1 is 10, and the 10 are respectively marked as I1, I2, … and I10 from left to right. The distances between the flame detector 3 and the high-energy igniter 11 are respectively 0m (namely, the same plane with the high-energy igniter 11), 0.5m, 0.8m,1m,1.2m,1.4m,1.6m,1.8m,2m and 2.55 m.
As shown in fig. 3, the flame detector 3 includes two tungsten needles 31, a ceramic sleeve 32, a tetrafluoroethylene sleeve 33 and a ferrule adapter 34 of M20 specification, which are arranged in sequence from inside to outside and spaced from each other, wherein the tungsten needle 31 has an outer diameter of 0.5mm and a length of 70 mm; the ceramic sleeve 32 is used for protecting the tungsten needle 31 and fixing the position of the tungsten needle 31, the outer diameter of the ceramic sleeve 32 is 3mm, the length of the ceramic sleeve is 46mm, two holes for accommodating the tungsten needle 31 are formed, the inner diameter of each hole is 0.7mm, the distance between the holes is 1mm, and the tungsten needle 31 and the ceramic sleeve 32 are fixed through silica gel; the tetrafluoroethylene sleeve 33 is used for enhancing the air tightness of the flame detector, and the tetrafluoroethylene sleeve 33 is 6mm in outer diameter, 3.1mm in inner diameter and 44mm in length.
Therefore, the gas is combusted to generate plasma, when the positive and negative plasma generated by the flame reaches the tungsten needle 31, a passage is formed between the two tungsten needles 31, and the flame plays a role in conduction; when the ferrule adapter 34 is screwed down, the tetrafluoroethylene sleeve 33 will deform, ensuring the air tightness of the connection with the ferrule adapter 34. The ferrule adapter 34 is used for connecting the tungsten needle 31 of the flame detector 3 with a shock tube.
The specific structure of the ion-electric signal conversion circuit 4 is shown in fig. 4. It includes a plurality of capacitors, resistors and diodes. The ion-electric signal conversion circuit 4 comprises a single circuit or a plurality of single circuits connected in parallel, each single circuit (single circuit) corresponds to one flame detector 3, and comprises a power supply U, a first resistor R1, a capacitor C1 and a shared resistor R0 which are sequentially connected between the positive electrode and the negative electrode of the power supply U, and a diode 43, a second resistor R2 and an ion probe O1 which are sequentially connected between one end of the first resistor R1 far away from the positive electrode of the power supply U and the negative electrode of the power supply U, wherein the ion probe is connected with a tungsten needle 31 of the flame detector. The single circuit thus converts the ion signal detected by the flame detector into an electrical signal that can be collected by the data acquisition system.
When the ion-electric signal conversion circuit 4 comprises a plurality of single circuits connected in parallel, the power supply U and the shared resistor R0 of the ion-electric signal conversion circuit 4 are shared by the plurality of single circuits, and the rest parts are connected in parallel, so that if a plurality of flame detectors are needed, a certain number of ion-electric signal conversion circuits are connected in parallel only according to experimental needs. In this embodiment, the voltage of the power source U is 200-400V, the first resistor R1 is a 20M Ω resistor, the second resistor R2 is a 12k Ω resistor, and the shared resistor R0 is a 4k Ω resistor. The capacitance C1 is a 1nF capacitance.
The data acquisition system is PXIe-1071 from NI corporation, which connects the ion-to-electrical signal conversion circuit 4 to the output generated by the pressure probe 2 through its BNC-2110 adapter module, thereby collecting and storing the output signal by the data acquisition system. The BNC-2110 adaptation module is a part of a data acquisition system and is used for connecting a BNC female head for transmitting electric signals.
Based on the measuring device for the propagation characteristics of the detonation waves, the method for measuring the propagation characteristics of the detonation waves comprises the following specific steps:
step S1: a measuring device 10 according to the propagation characteristics of the detonation wave described above is set up to introduce premixed gas at a predetermined initial pressure through its inlet 12. The type of the premixed gas can be determined according to the experiment requirement, and the experiment is that the volume fraction ratio is 1: 2 methane-oxygen premix gas;
step S2: closing the switches of the air inlet 12 and the air outlet 13, triggering the high-energy igniter 11, igniting the premixed gas, so that the gas in the pipeline is subjected to deflagration to generate deflagration waves, and the deflagration waves can be transmitted downstream;
wherein, the shock tube 1 is equipped with the manometer on keeping away from the lateral wall of high energy point firearm 11, consequently, still include in the step: before the high-energy igniter 11 is triggered, the pressure gauge 14 is switched off.
Step S3: when the shock wave and the combustion wave of the deflagration wave are propagated to the downstream, a pressure probe 2 is used for collecting shock wave signals, and a flame detector 3 is used for collecting combustion wave signals;
step S4: the data acquisition system is used for collecting shock wave signals acquired by the pressure probes 2 and combustion wave signals acquired by the flame detectors 3, so that the time for the shock waves and the combustion wave signals to reach the pressure probes 2 and the flame detectors 3 is obtained, the distance change between the shock waves and the combustion waves can be observed, and the speed of the combustion waves and the shock waves can be calculated according to the time.
Step S5: at the end of the experiment, the vent 13 was opened. Specifically, the vacuum pump connected to the air outlet 13 is used to pump vacuum, and the next experiment is prepared.
As shown in fig. 5, the signals above the horizontal axis are shock wave signals collected by the pressure probe 2 and are P1 to P8 in sequence from left to right, and the signals below the horizontal axis are combustion wave signals collected by the flame detector 3 and are I1 to I0 in sequence from left to right. As can be seen from the figure, on the pressure probe 2 and the first section (P1 and I3) of the pressure probe 2, the shock wave signal arrives at the pressure probe 2 earlier than the combustion wave signal arrives at the corresponding flame detector 3; whereas on the latter section the time of arrival of the shockwave signal and the combustion wave signal at the respective pressure probe 2 and flame detector 3 is substantially the same. It is stated that in a first section the flame propagates deflagratively, and in a second section the combustion wave overtakes the leading shock wave, the flame propagates deflagratively, i.e. the conversion of the deflagration wave into a detonation wave is completed between the first section and the second section.
The experimental data corresponding to the shockwave signal collected by the pressure probe 2 and the combustion wave signal collected by the flame detector 3 as shown in fig. 5 is shown in fig. 6 below, where the horizontal axis is the distance from the firing head and the vertical axis is the velocity of the shockwave and the combustion wave in each stage, where the red point is the velocity of the shockwave, the blue point is the velocity of the combustion wave, the first blue point is the velocity of the combustion wave between I1 and I2, the first red point is the velocity of the shockwave between P1 and P2, and so on. As can be seen from the data in fig. 6, the combustion wave accelerates the process of chasing the shock wave, and at x ═ 1m, the flame is also after the shock wave, passing through the section of x ═ 1m slower by 166us than the shock wave. The distance between the combustion wave and the shock wave gradually decreases. At x 1.2m, the flame and the shock wave pass through a cross section of x 1.2m simultaneously. The process of converting deflagration to detonation is completed in the distance of 1-1.2 m. The post-combustion wave has the same velocity as the shock wave at a distance x of 1.2 m.
The above embodiments are merely preferred embodiments of the present invention, which are not intended to limit the scope of the present invention, and various changes may be made in the above embodiments of the present invention. All simple and equivalent changes and modifications made according to the claims and the content of the specification of the present application fall within the scope of the claims of the present patent application. The invention has not been described in detail in order to avoid obscuring the invention.
Claims (10)
1. The utility model provides a measuring device of detonation wave propagation characteristic, includes shock tube (1), and one side tip of this shock tube (1) is equipped with high energy point firearm (11), is equipped with air inlet (12) and gas outlet (13) on the lateral wall that is close to high energy point firearm (11) of shock tube (1) in proper order, and air inlet (12) link to each other with a gas mixing system, and a vacuum pump is connected in gas outlet (13), its characterized in that, be equipped with a plurality of pressure probe (2) and flame detector (3) along its length direction in proper order on the lateral wall of shock tube (1), flame detector (3) link to each other with an ion-electricity signal conversion circuit (4), pressure probe (2) with ion-electricity signal conversion circuit (4) all link to each other with a data acquisition system.
2. The deflagration wave propagation characteristic measuring device according to claim 1, wherein the flame detector (3) comprises two tungsten needles (31), a ceramic sleeve (32), a tetrafluoroethylene sleeve (33) and a ferrule adapter (34) which are arranged in sequence from inside to outside and spaced from each other.
3. A deflagration wave propagation characteristic measurement device according to claim 2, characterized in that the tungsten needle (31) has an outer diameter of 0.5mm and a length of 70 mm; the external diameter of ceramic bushing (32) is 3mm, and length is 46mm to be equipped with two and be used for holding the hole of tungsten needle (31), the downthehole diameter is 0.7mm, and the hole interval is 1mm, fixes through silica gel between tungsten needle (31) and ceramic bushing (32).
4. A deflagration wave propagation characteristic measuring device according to claim 1, characterized in that said ion-electric signal conversion circuit (4) comprises a plurality of single circuits connected in parallel to each other, each of said single circuits corresponding to one of said flame detectors (3), said single circuits comprising a power source (U), a first resistor (R1), a capacitor (C1) and a shared resistor (R0) connected in sequence between the positive and negative poles of the power source (U), and a diode (43), a second resistor (R2) and an ion probe (O1) connected in sequence between the end of the first resistor (R1) remote from the positive pole of the power source (U) and the negative pole of said power source (U), said ion probe being connected to the tungsten needle (31) of said flame detector.
5. A deflagration wave propagation characteristic measuring device according to claim 4, characterized in that the power supply (U) and the shared resistance (R0) of said ion-electric signal conversion circuit (4) are common to a plurality of single circuits, the rest being arranged in parallel with each other.
6. A deflagration wave propagation characteristic measuring device according to claim 1, characterized in that the number of flame detectors (3) is greater than the number of pressure probes (2), each pressure probe (2) corresponding to one of the flame detectors (3) along the length of the shock tube (1).
7. A deflagration wave propagation characteristic measuring device according to claim 6, characterized in that the number of pressure probes (2) is 8 on the upper side wall of said shock tube (1), and the number of flame detectors (3) is 10 on the lower side wall of said shock tube (1).
8. A deflagration wave propagation characteristic measuring device according to claim 1, characterized in that a pressure gauge (14) is arranged on the side wall of the shock tube (1) far away from the high-energy igniter (11), and a stop valve is connected between the shock tube (1) and the pressure gauge (14).
9. A method of measuring a propagation characteristic of a detonation wave, comprising:
step S1: setting up a deflagration wave propagation characteristic measuring device according to any one of claims 1 to 8, through an air inlet (12) of which premixed gas is added;
step S2: closing the air inlet (12) and the air outlet (13) of the gas generator, triggering the high-energy igniter (11) to ignite the premixed gas, so that the gas in the pipeline generates deflagration and generates deflagration waves;
step S3: collecting shock wave signals of deflagration waves by using a pressure probe (2), and collecting combustion wave signals of the deflagration waves by using a flame detector (3);
step S4: collecting shock wave signals collected by the pressure probes (2) and combustion wave signals collected by the flame detectors (3) by using a data collection system to obtain the time for the shock waves and the combustion wave signals to reach the pressure probes (2) and the flame detectors (3);
step S5: and (5) opening the air outlet (13) after the experiment is finished.
10. A method for measuring propagation characteristics of a deflagration wave according to claim 9, wherein said step S4 further includes: and calculating the speed of the combustion wave and the shock wave according to the time of arrival of the shock wave and the combustion wave signals at each pressure probe (2) and each flame detector (3).
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