CN108801433B - Continuous measurement system and method for bulk acoustic velocity on main impact thermal insulation line of transparent medium - Google Patents
Continuous measurement system and method for bulk acoustic velocity on main impact thermal insulation line of transparent medium Download PDFInfo
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Abstract
The invention provides a system and a method for continuously measuring the bulk acoustic velocity on a main impact thermal insulation line of a transparent medium, which can continuously measure the bulk acoustic velocity on the main impact thermal insulation line of the transparent medium in a single-shot experiment, simultaneously record the velocity history of an obtained shock wave surface and the spatial track of a plane shock wave boundary generated by lateral sparsity by utilizing the reflection characteristic of strong impact on detection laser and the sensitivity of an imaging system on the surface type of a reflecting surface, and associate the bulk acoustic velocity of a wave rear body with the shock wave velocity to obtain the bulk acoustic velocity of the shock wave rear body; the invention reduces the strict limit on the loading condition, simultaneously fully utilizes the spatial information of the imaging system and realizes the measurement of the ultra-high pressure impact sound velocity.
Description
Technical Field
The invention relates to the field of sound velocity measurement in high-pressure equation of state research, in particular to a system and a method for continuously measuring the sound velocity of a body on a main impact heat insulation line of a transparent medium, which can realize ultrahigh-pressure impact sound velocity measurement.
Background
The response characteristic of the material under high pressure has important significance for a plurality of physical research fields such as earth and planet physics, inertial confinement fusion, modeling of the first-nature principle and the like. In various representations of response characteristics of the material, the sound velocity reflects the propagation characteristics of small stress disturbance in a medium, carries various modulus information of the material, is a mechanical property of the material in a certain thermodynamic state, and is an important means for researching a state equation, a constitutive relation, phase change (including solid-solid phase change) and material composition of the material. In the research of the planet physics and the weapon physics, the pressure range can reach the order of millions to ten million atmospheric pressures, and the sound velocity measurement under the high pressure is always an important difficulty in the research of the high pressure physics.
the shock compression is a main means for obtaining high pressure, the main form of the shock compression is shock waves, the shock wave front is uncompressed substances, the shock waves are compressed substances, the thickness of the shock waves is very thin, and the shock waves can be regarded as discontinuous jumps.
In order to measure the sound velocity of a material in an impact compression state, small stress disturbance needs to be introduced into an impact wave rear state, and the propagation velocity of the small disturbance in the state is measured. Under uniaxial strain loading conditions, there are two main types of perturbations: small transverse disturbances and small longitudinal disturbances, and the actual measurement is mainly unloading disturbances. Professor Al' tshuler L.V. of Russian famous impact dynamics experts is a predecessor of high-pressure sound velocity measurement, sound velocity measurement under 100GPa impact pressure of various metal materials is carried out as early as 1960, and experimental study is carried out on transverse disturbance and longitudinal disturbance. The lateral disturbance method is to record a one-dimensional plane range of a side sparse pair of constant shock waves reaching the rear surface of a sample by using a stripe camera, and the measurement accuracy of a disturbance boundary is limited under the current test condition, so that the later stage research mainly focuses on a sparse longitudinal disturbance pursuit method. In 1982, McQueen, Hopson et al improved the method for sparsely measuring the longitudinal wave sound velocity by pursuing, provided an optical analysis method, and greatly promoted the research on the impact sound velocity. The principle is that after a sample, window materials such as bromoform and the like which strongly emit light under impact loading and have light-emitting intensity very sensitive to pressure are introduced, and the arrival time of sparse waves is determined by recording the light-emitting intensity change, so that the longitudinal wave sound velocity and the bulk sound velocity are given. After the last 90 century, with the development of an interferometric velocity measurement technology with extremely high time resolution, the corresponding particle velocity can be obtained while carrying out the pursuit sparse time measurement, so that the sound velocity on the unloading line corresponding to the falling edge of the wave profile can be given. A team led by Tanhua professor of fluid physics research institute makes a lot of work on the aspect of measuring the impact sound velocity, a series of researches on the problems of longitudinal wave sound velocity, bulk wave sound velocity, relevant strength, phase change and the like are carried out on a typical metal material within 200GPa, and the research has higher influence internationally. At present, the sound velocity measurement on the main impact adiabatic line still takes longitudinal wave transit time measurement as a main means, the biggest problem encountered by the method is that a shock wave which is regularly transmitted is needed, the stability of the shock wave generated by direct energy deposition (such as high-power laser, high-energy particle beams and the like) at the present stage is still impossible to be compared with the impact of a flyer, the state and the thickness of the flyer are required to be known no matter in direct collision or reverse collision, and the precision requirement of the impact sound velocity measurement (especially a low-impedance sample) in a high-pressure section by a catch-up method is difficult to meet by the existing flyer driving technology (8 km/s of an air cannon driving flyer and 30km/s of a magnetic driving flyer) under the constraint conditions.
Therefore, the existing sound velocity measurement has the following defects:
firstly, the steady-state propagation of the shock wave under the ultrahigh pressure is difficult to realize, so that the pursuing process of disturbance propagation cannot accurately reflect the sound velocity.
The shock wave of steady state propagation is all produced with the high-speed flyer striking, and the line pressure is millions of atmospheric pressures at present. Experiments have been carried out to generate shock waves at higher pressures, usually by other driving means, such as high peak power lasers, pulsed power devices, etc., which are characterized by particularly stable shock waves that are difficult to generate. Therefore, the catch-up method is not suitable for ultra-high pressure sound velocity measurement.
Secondly, the method for measuring the lateral sparsity of the rear surface of the sample cannot accurately give the bending point of the shock wave surface, and the sound velocity result cannot be accurately given
The work of the former soviet union is that the impact luminescence signal of the free surface of a sample is measured, only the difference before and after the signal appears can be distinguished, and the essential difference between a planar area and a non-planar area cannot be completely and clearly given, so that the identification precision of a bending point is poor, and the sound velocity result is also poor.
Disclosure of Invention
In order to overcome the technical problems of the existing sound velocity measurement, the invention provides a continuous measurement system and a method for the bulk sound velocity on the main impact heat insulation line of a transparent medium, which can continuously measure the bulk sound velocity on the main impact heat insulation line of the transparent medium in a single-shot experiment, utilize the reflection characteristic of strong impact on detection laser and the sensitivity of an imaging system on the surface type of a reflecting surface, simultaneously record the velocity history of an obtained shock wave surface and the spatial track of a plane shock wave boundary generated by lateral sparsity, and associate the bulk sound velocity of a wave rear body with the shock wave velocity to obtain the bulk sound velocity of the shock wave rear body; the invention reduces the strict limit on the loading condition, simultaneously fully utilizes the spatial information of the imaging system and realizes the measurement of the ultra-high pressure impact sound velocity.
The invention is realized by the following technical scheme:
the system comprises a loading mechanism, a substrate, a sample to be measured and a line imaging diagnosis system;
the loading mechanism is used for generating unsteady shock waves along the main shock insulation line under the Tpa pressure to realize transverse plane one-dimensional loading; the substrate, the sample to be detected and the line imaging diagnosis system are sequentially arranged along the propagation direction of the unsteady shock wave; the sample to be detected is a transparent sheet, the transparent sheet is tightly attached to the substrate, the side surface of the transparent sheet is a free surface and is vertical to the substrate, and the side surface is positioned in the field of view of the line imaging diagnosis system;
the time when the unsteady shock wave reaches the surface of the substrate corresponds to the time when the shock wave enters the sample, the line imaging diagnosis system starts to record the time and the speed of the shock wave in the process from the time when the shock wave enters the sample to the time when the shock wave leaves the sample and plane shock wave reflection boundary track data, and the relationship between the sound velocity after the shock wave and the shock wave speed is obtained after the data is processed.
When the compressed state of the shock wave reaches or exceeds the metalized or ionized state of a sample, the wave rear medium is strongly reflected to the detection laser, the reflection signal of the plane shock wave can return to the detection system, and the lateral sparsity can cause the shock wave speed close to a vertical boundary to become slow, so that the shock wave surface is shown to be bent backwards, the bent wave surface reflection signal cannot return to the detection system, the measured high-brightness reflection area gradually becomes smaller along with the gradual propagation of the sparse wave to the inside of the plane area, and the boundary of the high-brightness area is the track of the shock wave bending point (namely the reflection boundary track of the plane shock wave).
Specifically, the loading mechanism directly irradiates the ablation layer with high-power laser to generate shock waves which enter the substrate.
Specifically, the loading mechanism is a high-speed flyer, and the flyer impacts the substrate to form shock waves in the substrate.
Specifically, the loading mechanism is the induced X ray ablation layer that produces of high power laser in the heavy metal cavity, produces the shock wave and gets into the base plate, the base plate includes isolation layer and basic unit, and the isolation layer setting is on the basic unit face towards the loading mechanism for eliminate the preheating effect that X ray and electron produced base plate and sample.
Specifically, the isolation layer is made of heavy metal elements, and the base layer is made of aluminum.
Specifically, based on the relationship between the high pressure sound velocity and the high pressure state of the material, the shock wave velocity U is obtained by direct measurementsAnd obtaining the high pressure sound velocity C by merging the side sparse boundaryb
In the formula, CbAt the speed of sound, UsFor actual measured shock wave velocity, Upα is the included angle between the tangent of the sparse track at the side of the shock wave and the propagation direction of the shock wave.
Further, in order to reduce the influence of interference fringes, the line imaging diagnosis system comprises an interference speed measurement system and a non-interference return light brightness measurement system.
In addition, based on the continuous measurement system, the invention also provides a continuous measurement method for the sound velocity of the bulk on the main impact thermal insulation line of the transparent medium, which comprises the following steps:
1) installation of a measuring system: the installation layout of the measuring equipment is carried out according to the continuous measuring system, when in installation, a sample to be measured is tightly attached to the substrate, the side surface of the sample to be measured is a free surface and is vertical to the substrate, the vertical side surface of the sample to be measured is ensured to be positioned in the visual field of the line imaging diagnosis system, and the distance from the visual field boundary of the sample area to the vertical side surface is more than 1.5 times of the thickness of the sample;
2) and (3) continuous measurement: the loading mechanism generates a transverse uniform plane one-dimensional loading shock wave, the shock wave enters a sample to be tested through the substrate, and a line imaging system records the shock wave speed, the transit time and the space track of a plane shock wave boundary generated by lateral sparsity in the process from the time when the shock wave enters the sample to be tested to the time when the shock wave leaves the sample to be tested;
3) data processing: the wave rear body sound velocity is related to the shock wave velocity, and the wave rear body sound velocity is obtained based on the shock wave velocity, the transit time and the shock wave side sparse track data which can be directly measured.
The invention has the following advantages and beneficial effects:
1. the system and the method can form strong impact loading in the transparent medium, can obtain the continuous change of the sound velocity of the body on the main impact heat insulation line of the ultrahigh pressure section of the transparent medium in the process of one experiment, overcome the defect that the existing sound velocity measurement experiment can only measure one state point on the impact heat insulation line, and certainly, the invention not only can measure the sound velocity corresponding to the state experienced by the experimental impact wave at one time, but also can only measure a certain state point;
2. according to the continuous measurement system and the method, the reflection characteristic of strong impact on the detection laser and the sensitivity of the imaging system on the surface type of the reflecting surface are utilized, the velocity history of the obtained impact wave surface and the spatial track of the lateral sparse boundary are recorded at the same time, the wave rear body sound velocity is related with the impact wave velocity, the wave rear body sound velocity can be rapidly and accurately measured, the severe limit on the loading condition is reduced, the spatial information of the imaging system is fully utilized, and the ultrahigh pressure impact sound velocity measurement is realized;
3. the relative precision of the continuous measurement and the multiple impact experiment measurement of the sound velocity realized by the invention is greatly improved, and the response of the sensitive area is far better than that of the multiple impact experiment, such as the detection of a phase change point, so that the sound velocity measurement precision is greatly improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this application, illustrate embodiment(s) of the invention and together with the description serve to explain the principles of the invention. In the drawings:
fig. 1 is a structural view of a measurement system according to a first embodiment of the present invention.
Fig. 2 is a structural view of a measurement system according to a second embodiment of the present invention.
Fig. 3 is a structural view of a measurement system according to a third embodiment of the present invention.
FIG. 4 is a graph of the shock wave edge side sparse trace of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.
Example 1
As shown in fig. 1, the system for continuously measuring the sound velocity of a body on a main impact thermal insulation line of a transparent medium comprises a loading mechanism, a substrate, a sample to be measured, and a line imaging diagnostic system, wherein the line imaging diagnostic system in this embodiment adopts a line imaging laser velocity interferometer (line imaging VISAR);
in the embodiment, the loading mechanism directly irradiates the ablation layer with high-power laser to generate shock waves which enter the substrate, and generates unsteady shock waves along the main shock insulation line under the pressure of Tpa, so that one-dimensional loading of a transverse plane is realized; the substrate, the sample to be detected and the line imaging diagnosis system are sequentially arranged along the propagation direction of the unsteady shock wave; the sample to be detected is a transparent sheet, the transparent sheet is tightly attached to the substrate, the side surface of the transparent sheet is a free surface and is vertical to the substrate, and the side surface is positioned in the view field of the line imaging diagnosis system;
the time when the unsteady shock wave reaches the surface of the substrate corresponds to the time when the shock wave enters the sample, the line imaging diagnosis system starts to record the time and the speed of the shock wave in the process from the time when the shock wave enters the sample to the time when the shock wave leaves the sample and plane shock wave reflection boundary track data, and the relationship between the sound velocity after the shock wave and the shock wave speed is obtained after the data is processed.
The sample is a transparent thin sheet, as shown in fig. 1, and is closely attached to the substrate, and the side surface of the sample is a free surface and perpendicular to the substrate, and the sample is installed so that the perpendicular side surface of the sample is located in the field of view of the line imaging diagnostic system. Thus, when the shock wave reaches the surface of the substrate, data of the moment can be given in the online imaging diagnosis system, and the moment corresponds to the moment when the shock wave enters the sample, namely the moment when the side rarefaction wave starts to enter. After the shock wave enters the sample, because the wave rear medium is in a dense plasma state, the detection light emitted by the line imaging diagnostic system is reflected back to the diagnostic system at the wave front to cause stripe deviation and give shock wave speed information. Meanwhile, the shock wave close to the side surface starts to be bent, when the bending angle is too large, so that the included angle between the reflected light and the optical axis is larger than the receiving angle of the imaging system, the reflected signal of the bending surface is lost, the image surface is presented as a dark area, the reflected signal gradually spreads to the inside of the plane area along with the sparse wave, the measured high-brightness reflecting area gradually becomes smaller, and the boundary of the high-brightness reflecting area is the shock wave edge side sparse track as shown in fig. 4.
The velocity vector diagram after wave is shown in figure 1, the propagation of weak disturbance takes a disturbance source as a circle center and circularly propagates to the periphery, and the satellite velocity U exists in the propagation processpTo U withpdt from the top as centre of a circle, using Cbdt is a radius and draws a circle, the intersection point of the circumference and the shock wave surface at the dt moment is the starting point of the shock wave surface bending, the included angle between the connecting line from the starting point to a new bending point (namely the tangent line of the sparse track at the side of the shock wave) and the propagation direction of the shock wave is α, and the following relations are satisfied:
in the formula of UsFor actually measuring the shock wave velocity, corresponding U is given according to literature datapthe most important measurement parameter is the time-dependent measurement of α (t), in fact more precisely α (U)s). The variable measured directly in the experiment was Us(t) and a side sparse boundary Y (t), and obtaining the high-pressure sound velocity C through data processingb。
In this embodiment, the line imaging diagnosis system includes an interferometric velocity measurement system and a non-interferometric return light brightness measurement system; thus, a smooth bright and dark boundary can be seen in the recorded result of the system, and the influence of the stripe is avoided.
Example 2
The present embodiment 2 is different from embodiment 1 in that the loading mechanism is a high-speed flyer, which strikes a substrate to form a shock wave in the substrate. As shown in fig. 2.
Example 3
The difference between the embodiment 3 and the embodiment 1 is that the loading mechanism 1 irradiates an ablation layer with X-rays generated by high-power laser induced in a heavy metal cavity to generate shock waves to enter a substrate; in addition, because radiation temperature is higher in the heavy metal cavity, can produce obvious preheating effect to base plate and the sample that awaits measuring, introduce high Z element for this reason in the base plate as the isolation layer, adopt this kind of structure of isolation layer-basic unit as the base plate in this embodiment, and the isolation layer setting is on the basic level face towards loading mechanism, and the isolation layer adopts heavy metal element to make in this embodiment, and the basic unit adopts aluminium to make, and its effect includes two parts: firstly, the preheating effect of X-rays and electrons on a substrate and a sample can be eliminated to a great extent; secondly, when the ablation shock wave enters the sample through the substrate, the waveform is converted into a triangular wave from the quasi-trapezoid of the ablation surface, namely the shock wave entering the sample can hardly see the platform area, and the test precision is greatly improved. As shown in fig. 3.
Example 4
Based on the continuous measurement system described in the above embodiment, the present invention further provides a continuous measurement method for the bulk acoustic velocity on the main impact thermal insulation line of the transparent medium, which includes the following steps:
1) installation of a measuring system: the installation layout of the measuring equipment is carried out according to the continuous measuring system, when in installation, a sample to be measured is tightly attached to the substrate, the side surface of the sample to be measured is a free surface and is vertical to the substrate, the vertical side surface of the sample to be measured is ensured to be positioned in the visual field of the line imaging diagnosis system, and the distance from the visual field boundary of the sample area to the vertical side surface is more than 1.5 times of the thickness of the sample;
2) and (3) continuous measurement: the loading mechanism generates a transverse uniform plane one-dimensional loading shock wave, the shock wave enters a sample to be tested through the substrate, and a line imaging system records the shock wave speed, the transit time and the space track of a plane shock wave boundary generated by lateral sparsity in the process from the time when the shock wave enters the sample to be tested to the time when the shock wave leaves the sample to be tested;
3) data processing: the wave rear body sound velocity is related to the shock wave velocity, and the wave rear body sound velocity is obtained based on the shock wave velocity, the transit time and the shock wave side sparse track data which can be directly measured.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (7)
1. The continuous measurement system of the bulk acoustic velocity on the main impact heat insulation line of the transparent medium is characterized by comprising a loading mechanism, a substrate, a sample to be measured and a line imaging diagnosis system;
the loading mechanism is used for generating unsteady shock waves along the main shock insulation line under the Tpa pressure to realize transverse plane one-dimensional loading; the substrate, the sample to be detected and the line imaging diagnosis system are sequentially arranged along the propagation direction of the unsteady shock wave; the sample to be detected is a transparent sheet, the transparent sheet is tightly attached to the substrate, the side surface of the transparent sheet is a free surface and is vertical to the substrate, and the side surface is positioned in the field of view of the line imaging diagnosis system;
the time when the unsteady shock wave reaches the surface of the substrate corresponds to the time when the shock wave enters the sample, the line imaging diagnosis system starts to record the time and the speed of the shock wave in the process from the time when the shock wave enters the sample to the time when the shock wave leaves the sample and plane shock wave reflection boundary track data, and the relationship between the sound velocity after the shock wave and the shock wave speed is obtained after the data is processed;
based on the relation between the high pressure sound velocity and the high pressure state of the material, the shock wave velocity U is obtained by direct measurementsAnd shock wave side sparse trackTo obtain a high pressure sound velocity Cb
In the formula, CbAt the speed of sound, UsFor actual measured shock wave velocity, Upα is the included angle between the tangent of the sparse track at the side of the shock wave and the propagation direction of the shock wave.
2. The continuous measurement system of claim 1, wherein the loading mechanism generates a shock wave into the substrate for the high power laser to directly irradiate the ablation layer.
3. The continuous measurement system of claim 1, wherein the loading mechanism is a high speed flyer that impacts a substrate, creating a shock wave in the substrate.
4. The continuous measuring system of claim 1, wherein the loading mechanism is an X-ray ablation layer induced by high power laser in the heavy metal cavity to generate shock waves into the substrate, the substrate comprises an isolation layer and a base layer, and the isolation layer is disposed on the base layer facing the loading mechanism for eliminating the preheating effect of the X-ray and the electrons on the substrate and the sample.
5. The continuous measurement system of claim 4, wherein the isolation layer is made of a heavy metal element and the base layer is made of aluminum.
6. The continuous measurement system of claim 1, wherein the line imaging diagnostic system comprises an interferometric velocimetry system and a non-interferometric return light brightness measurement system.
7. The method for continuously measuring the sound velocity of the body on the main impact thermal insulation line of the transparent medium is characterized by comprising the following steps of:
1) installation of a measuring system: the arrangement for installing the measuring device according to the continuous measuring system of any one of claims 1 to 6, wherein the sample to be measured is tightly attached to the substrate, the side surface of the sample to be measured is a free surface and is perpendicular to the substrate, so that the perpendicular side surface of the sample to be measured is ensured to be positioned in the visual field of the line imaging diagnostic system, and the distance from the visual field boundary of the sample area to the perpendicular side surface is more than 1.5 times of the thickness of the sample;
2) and (3) continuous measurement: the loading mechanism generates a transverse uniform plane one-dimensional loading shock wave, the shock wave enters a sample to be tested through the substrate, and a line imaging system records the shock wave speed, the transit time and the space track of a plane shock wave boundary generated by lateral sparsity in the process from the time when the shock wave enters the sample to be tested to the time when the shock wave leaves the sample to be tested;
3) data processing: the wave rear body sound velocity is related to the shock wave velocity, and the wave rear body sound velocity is obtained based on the shock wave velocity, the transit time and the shock wave side sparse track data which can be directly measured.
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