CN113671209B - Space resolution-based flyer velocity field measurement system and attitude dynamic characterization method - Google Patents
Space resolution-based flyer velocity field measurement system and attitude dynamic characterization method Download PDFInfo
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- G01P3/00—Measuring linear or angular speed; Measuring differences of linear or angular speeds
- G01P3/64—Devices characterised by the determination of the time taken to traverse a fixed distance
- G01P3/68—Devices characterised by the determination of the time taken to traverse a fixed distance using optical means, i.e. using infrared, visible, or ultraviolet light
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Abstract
The invention discloses a flying piece velocity field measuring system based on spatial resolution and a posture dynamic characterization method.A microscopic PDV speed measuring probe distributes laser emitted by a multi-point PDV speed measuring host machine according to preset measuring points, penetrates through a transparent window and then is projected onto the surface of a flying piece; the micro PDV speed measuring probe collects the return light of different measuring point positions on the surface of the flyer; the multi-point PDV speed measurement host generates an optical interference signal corresponding to Doppler frequency shift caused by the movement of the flyer, and converts the optical interference signal into a corresponding high-frequency electric signal; the high-broadband digital oscilloscope is used for recording high-frequency electric signals output by the multi-point PDV speed measurement host; the data processing device is used for analyzing and processing the electric signals to obtain the speed of the free surface of the flyer at different measuring points and the speed history of the interface particles when the flyer impacts the transparent window. The invention can simultaneously realize the accurate measurement of the speed of the free surface of the flyer and the speed process of the interface particles, and realize the continuous time resolution characterization of the attitude of the flyer.
Description
Technical Field
The invention belongs to the technical field of testing of initiating explosive devices, and particularly relates to a flyer velocity field measuring system based on spatial resolution and an attitude dynamic characterization method.
Background
The impact sheet detonator was originally proposed in 1976 by Stroud of researchers in Lawrence-Livermo national laboratories, USA, and the use of bridge foil electric explosion to drive the flyer to detonate the low-sensitivity explosive has the advantages of insensitivity to electromagnetic interference, capability of providing accurate time sequence and outputting stable pressure, so that the impact sheet detonator is widely applied to the military field, aerospace, petroleum, mining and other industries. The energy transmission and action process of the impact sheet detonator mainly comprises three closely-connected stages: the metal bridge foil electric explosion, the electric explosion plasma drive flyer acceleration and flyer impact initiation initiating explosive. The attitude (integrity, planarity) and kinetic energy (velocity field and thickness field distribution) of the flyer striking the initiating explosive are the most critical physical quantities, and are influenced by the coupling of a plurality of factors such as a previous discharge circuit, a bridge foil, the flyer and a bore, and the like, and whether the initiating explosive can be reliably excited so as to detonate a subsequent detonation sequence is determined. In order to realize the performance characterization and the optimized design of the impact sheet detonator, the flying sheet attitude in the whole action process must be diagnosed. Because the size of the impact piece detonator is small (the bore diameter is about 400-.
As early as 1989, boberg. r.e. from the LLNL national laboratory in the united states evaluated the shape of the impact sheet by recording the moment when the impact sheet detonator flying sheet struck the organic glass surface with a scanning camera. Scientific researchers in an AWE laboratory in England in 2017 adopt a visible light high-speed photography technology to shoot the morphology and the posture of a flyer from two directions facing the movement direction of the flyer and perpendicular to the movement direction of the flyer, and are limited by dynamic blurring caused by 5 ns exposure time of a high-speed camera, and plasma and the flyer of bridge foil electric explosion cannot be distinguished due to limited penetration capacity of visible light, so that quantitative flyer speed and posture quantitative data cannot be given. The progress of the X-ray photo technology based on the synchronous radiation source makes the better research on the flying process of the impact sheet detonator possible. In 2016, on an Advanced Photon Source (APS) device of Argonne national laboratory in America, researchers adopt an X-ray phase contrast computer tomography technology with relatively strong penetrating power to obtain 2D and 3D dynamic images of flying piece bending, breaking and stretching in the flying process of the impact piece detonator at 4 moments for the first time. The X-ray imaging technology is a technology which is more successful in the field of the attitude diagnosis of the shock piece detonator flying piece at present, the method has the advantages that the image is visual, the attitude information of the flyer at a plurality of moments is obtained to a certain extent in a projection imaging mode, the method has the defects that the technology is projected by line integral, in the unidirectional diagnosis, although the spatial resolution is high, the information along the projection direction is overlapped, if multi-angle projection is adopted and the computer tomography technology is combined for three-dimensional reconstruction, the requirements on hardware such as an X-ray source, an X-ray framing camera and the like are extremely high, otherwise three-dimensional data of a position Z (X, y, t) and a thickness h (X, y, t) with high resolution are difficult to obtain, in addition, the imaging technology can only obtain the average speed of the flyer at a plurality of moments, and cannot realize continuous high-precision measurement of the speed history of the flyer, so that the method is extremely disadvantageous for subsequent evaluation of the performance of the flyer impacting the initial medicament.
Therefore, a dynamic flying piece attitude performance characterization technology is urgently needed to be developed, quantitative characterization of flying piece attitude can be realized, high economy is achieved, performance characterization of the action process of the impact piece detonator is served, and requirements of action mechanism research, margin evaluation and optimization design of the impact piece detonator are further met.
Disclosure of Invention
The invention provides a flying piece velocity field measuring system based on spatial resolution, which can simultaneously realize accurate measurement of flying piece free surface velocity and interface particle velocity history, and further realize continuous time resolution representation of flying piece integrality, planarity, thickness and other postures.
The invention is realized by the following technical scheme:
the flying piece velocity field measurement system based on spatial resolution comprises a transparent window, a microscopic PDV speed measurement probe, a multi-point PDV speed measurement host, a high-broadband digital oscilloscope and a data processing device;
the transparent window is arranged at the outlet of the bore of the impact sheet detonator component;
the microscopic PDV speed measurement probe enables laser emitted by the multi-point PDV speed measurement host to penetrate through the transparent window according to preset measuring point distribution and then to be projected to the surface of a flying piece in a gun bore;
the microscopic PDV speed measurement probe collects the return light of different measuring point positions on the surface of the flyer and transmits the return light to the multi-point PDV speed measurement host;
the multi-point PDV speed measurement host generates an optical interference signal corresponding to Doppler frequency shift caused by the movement of the flyer, converts the optical interference signal into a corresponding high-frequency electric signal and transmits the high-frequency electric signal to the high-broadband digital oscilloscope; the multi-point PDV speed measurement host is provided with a measurement channel matched with the number of measurement points of the microscopic PDV speed measurement probe;
the high-broadband digital oscilloscope is used for recording high-frequency electric signals output by the multi-point PDV speed measurement host;
the data processing device is used for analyzing and processing the high-frequency electric signals recorded by the high-bandwidth digital oscilloscope to obtain the flying piece free surface speeds of different measuring points and the interface particle speed history of the flying piece impacting the transparent window so as to represent the flying piece posture.
Preferably, the transparent window of the present invention is formed by processing lithium fluoride, organic glass or sapphire.
Preferably, the microscopic PDV speed measuring probe is provided with 7-81 measuring points within the bore diameter of 0.45-0.60 mm, and the measuring points are distributed without overlapping within the bore height range.
Preferably, the micro PDV velocimetry probe of the present invention adopts a non-imaging mode based on a lens array or an imaging mode based on a single lens or a lens group.
Preferably, the transparent window adopts a lithium fluoride window, the thickness of the window is millimeter, and antireflection films are plated on two sides.
Preferably, the micro PDV speed measurement probe adopts a compact optical fiber array probe, 19 measurement points are distributed in total, and the 19 measurement points can cover the characteristic area of the bridge foil.
Preferably, the high-broadband digital oscilloscope meets the requirements of the PDV speed measurement host machine on the bandwidth and the sampling rate of the speed before the flyer impact.
In a second aspect, the invention provides a flying piece attitude dynamic characterization method, which includes:
the speed of the free surface of the flyer and the speed process of the particles impacting the transparent window interface of the flyer at different spatial positions are obtained by simultaneously measuring the flyer speed field measuring system;
and (3) performing time and space correlation analysis on the speed of the free surface of the flyer at different spatial positions and the speed history of the flyer impacting the transparent window interface particles to obtain the attitude information of the flyer.
Preferably, the time and space correlation analysis of the speed of the free surface of the flyer at different spatial positions and the speed history of the flyer impacting the transparent window interface particles specifically comprises:
obtaining the free surface speed, the interface particle speed, the impact time and the impact pulse width according to the free surface speed of the flyer and the interface particle speed process of the flyer impacting the transparent window;
representing the integrity of the flyer according to the existence of measuring point signals at different spatial positions;
representing the planarity of the flyers according to the time difference of the flyers at different spatial positions impacting the transparent window;
calculating the thickness of the flyer at each space position according to the pulse width at the space position;
and characterizing the relative difference of the thicknesses of the flyers at different spatial positions according to the pulse widths of the flyers at the different spatial positions, which impact the transparent window.
Preferably, the method of the present invention further comprises:
and reconstructing the three-dimensional posture of the flyer when the flyer impacts the transparent window according to the integrity, the planarity, the thickness and the relative difference of the thickness of the flyer.
The invention has the following advantages and beneficial effects:
compared with a diagnosis mode which is relatively intuitive but not quantitative in X-ray imaging technology, the invention adopts the micro PDV speed measurement probe to measure the speed field with spatial resolution, adopts the transparent window as a target, can simultaneously realize the accurate measurement of the speed of the free surface of the flyer and the speed course of the interface particle, and further obtains the take-off time of the interface particle speed, the speed of the interface particle and the impact pulse width, thereby representing the key physical quantity information such as the collision moment of the flyer, the collision pressure of the flyer, the impact pulse width of the flyer and the like.
Compared with the X-ray imaging technology, the method has the advantages of low experimental cost and short period.
The invention realizes the continuous time resolution representation of the integrity, the planarity and the thickness of the flyer based on the analysis and interpretation of the measurement results of the free surface speed and the interface particle speed history of the spatial resolution, thereby realizing the three-dimensional and quantitative representation of the attitude of the flyer of the impact sheet detonator in the real sense.
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 schematic block diagram of a measurement system of the present invention.
FIG. 2 is a schematic diagram of a measuring optical path layout according to the present invention.
Fig. 3 is a schematic diagram of velocity measurement light spot distribution according to the present invention.
Fig. 4 is a measurement diagram of the distribution of speed measurement light spots according to the present invention.
Fig. 5 is a schematic diagram of the full speed history of the free surface of the flyer measured by the invention.
FIG. 6 is a schematic diagram of the velocity history of the flying-chip interface particles measured by the present invention.
Reference numbers and corresponding part names in the drawings:
1-base, 2-bridge foil, 3-flying piece, 4-bore, 5-transparent window, 6-micro PDV speed measuring probe, 7-laser, 8-measuring point.
Detailed Description
Hereinafter, the term "comprising" or "may include" used in various embodiments of the present invention indicates the presence of the invented function, operation or element, and does not limit the addition of one or more functions, operations or elements. Furthermore, as used in various embodiments of the present invention, the terms "comprises," "comprising," "includes," "including," "has," "having" and their derivatives are intended to mean that the specified features, numbers, steps, operations, elements, components, or combinations of the foregoing, are only meant to indicate that a particular feature, number, step, operation, element, component, or combination of the foregoing, and should not be construed as first excluding the existence of, or adding to the possibility of, one or more other features, numbers, steps, operations, elements, components, or combinations of the foregoing.
In various embodiments of the invention, the expression "or" at least one of a or/and B "includes any or all combinations of the words listed simultaneously. For example, the expression "a or B" or "at least one of a or/and B" may include a, may include B, or may include both a and B.
Expressions (such as "first", "second", and the like) used in various embodiments of the present invention may modify various constituent elements in various embodiments, but may not limit the respective constituent elements. For example, the above description does not limit the order and/or importance of the elements described. The foregoing description is for the purpose of distinguishing one element from another. For example, the first user device and the second user device indicate different user devices, although both are user devices. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without departing from the scope of various embodiments of the present invention.
It should be noted that: if it is described that one constituent element is "connected" to another constituent element, the first constituent element may be directly connected to the second constituent element, and a third constituent element may be "connected" between the first constituent element and the second constituent element. In contrast, when one constituent element is "directly connected" to another constituent element, it is understood that there is no third constituent element between the first constituent element and the second constituent element.
The terminology used in the various embodiments of the invention is for the purpose of describing particular embodiments only and is not intended to be limiting of the various embodiments of the invention. As used herein, the singular forms are intended to include the plural forms as well, unless the context clearly indicates otherwise. Unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as commonly understood by one of ordinary skill in the art to which various embodiments of the present invention belong. The terms (such as those defined in commonly used dictionaries) should be interpreted as having a meaning that is consistent with their contextual meaning in the relevant art and will not be interpreted in an idealized or overly formal sense unless expressly so defined herein in various embodiments of the present invention.
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 present embodiment provides a flying piece velocity field measurement system based on spatial resolution, which includes a transparent window 5, a micro PDV (Photonic Doppler Velocimeter) speed measurement probe, a multi-point PDV speed measurement host, a high-bandwidth digital oscilloscope, and a data processing device.
Wherein a transparent window 5 is mounted at the exit of the bore 4 of the ballistic sheet detonator assembly.
The transparent window 5 of this embodiment is used for replacing the primary explosive in the real impact piece detonator subassembly, and the process of simulation flyer striking primary explosive can adopt materials processing such as lithium fluoride, organic glass, sapphire to form.
The microscopic PDV speed measurement probe enables laser emitted by the multi-point PDV speed measurement host to penetrate through the transparent window 5 as required (according to preset light spot distribution) and then to be projected to the surface of the flying piece 3 in the bore 4; and collecting the returning light on the surface of the flyer 3 and transmitting the returning light back to the multi-point PDV speed measurement host.
The micro PDV speed measuring probe of the embodiment carries out space-resolved speed field measurement, and 7-81 measuring points can be arranged in the bore diameter of 0.45 mm-0.60 mm according to actual requirements, so that extremely high space-resolved measurement is realized. Implementations of micro-PDV velocimetry probes include, but are not limited to, non-imaging based lens arrays or imaging based on individual lenses or groups of lenses.
The multi-point PDV speed measurement host generates an optical interference signal corresponding to Doppler frequency shift caused by movement of the flyer 3 based on an optical Doppler effect, converts the optical interference signal into a corresponding high-frequency electric signal, and is provided with a measurement channel matched with the number of measurement points of the micro-PDV probe.
The high-broadband digital oscilloscope is used for recording high-frequency electric signals output by the multi-point PDV speed measurement host, and meets the requirements of the PDV speed measurement host on the broadband and sampling rate of the speed before the flyer impact.
The data processing device is used for processing the high-frequency electric signals recorded by the high-bandwidth digital oscilloscope, obtaining the flying piece free surface speeds of different measuring points and the interface particle speed history (the free surface speed and the interface particle speed associated with the space position) of the flying piece impacting the transparent window 4, giving attitude information such as the integrity, the planarity, the speed field, the thickness field and the like of the flying piece through the association reading of the speed histories of the different measuring points, and outputting animation of the flying piece flying acceleration process.
The working principle of the measurement system of the embodiment is specifically as follows:
the multi-point PDV speed measurement host machine emits laser which is transmitted to a microscopic PDV speed measurement probe through an optical fiber, and the microscopic PDV speed measurement probe projects the laser to the surface of a flying piece in a bore after penetrating through a transparent window according to preset light spot distribution; when the shock piece detonator assembly acts, a bridge foil 2 of the shock piece detonator assembly is electrically exploded to generate plasma to drive a flying piece 3 to move in a gun bore 4, the flying piece 3 can impact a transparent window 5 at the outlet of the gun bore 4, laser projected onto the flying piece 3 by a microscopic PDV speed measurement probe can cause the return light of the laser to generate Doppler frequency shift when the flying piece 3 moves and impacts the transparent window 5, the return light is collected by the microscopic PDV speed measurement probe and then transmitted back to a multi-point PDV speed measurement host by an optical fiber, and interference signals formed in the multi-point PDV speed measurement host are converted into high-frequency electric signals by a photoelectric detector in the speed measurement host; the high-frequency electric signal is transmitted to a high-broadband digital oscilloscope for recording through a high-frequency cable; high-frequency electric signal data files of a plurality of measuring points recorded by the high-bandwidth oscilloscope are transmitted to the data processing device in an online or offline mode, the data processing device processes the high-frequency electric signals and gives attitude information such as speed history, flying piece integrity, planarity, thickness field and the like and animation.
Example 2
In this embodiment, the measurement system proposed in the above embodiment 1 is used to measure the velocity of the free surface of the flyer in the bore and the velocity of the particle at the interface of the flyer hitting the transparent window at the same time.
In the embodiment, a lithium fluoride (LiF) window is adopted and installed at the outlet of a bore, the thickness of the window is in millimeter order, for example, about 4mm, and 1550 nm antireflection film is plated on two sides, so as to improve the signal-to-noise ratio of the PDV velocity measurement signal.
A microscopic PDV speed measurement probe with spatial resolution is arranged above a lithium fluoride window, the microscopic PDV speed measurement probe of the present embodiment adopts a compact fiber array probe, an experimental layout is shown in fig. 2, speed measurement light spots are distributed as shown in fig. 3, 19 measurement points are distributed in a bore, the 19 measurement points are not overlapped in the height range of the bore, 1 measurement point is arranged at the center, 6 measurement points are distributed with a first circle radius of R1=100 μm, 12 measurement points are distributed with a second circle radius of R2=200 μm, R1 and R2 can be adjusted according to the size of a bridge foil and the diameter of the bore, substantially cover the characteristic region of the bridge foil, and can meet the space-time resolution measurement requirement of a PDV flying piece velocity field to a certain extent. In further preferred embodiments, the spot distribution, number of spots, etc. may be varied accordingly, depending on the change in the location of the feature of interest during the measurement.
As shown in fig. 4, in this embodiment, the infrared camera is used to measure the light spot distribution of the developed optical fiber probe, and the distance between the probe and the photosensitive surface of the infrared camera is adjusted to obtain a light spot image with the light spot distribution varying with the distance between the target surfaces, and the result shows that the diameter of the light spot is between 30 μm and 60 μm within the height range of the bore of about 0.4 mm, and the light spot diameter is not overlapped with each other, so as to avoid the mutual crosstalk of PDV velocity measurement interference signals between the measurement points.
In this embodiment, 3 multi-point PDV speed measurement hosts are adopted, each multi-point PDV speed measurement host includes 8 channels, 19 channels (corresponding to 19 measurement points) are used in the experiment, 5 digital oscilloscopes are matched, the bandwidth of each digital oscilloscope is greater than or equal to 5GHz, and the sampling rate is greater than or equal to 20 GSa/s.
In the embodiment, the free surface velocity and the interface particle velocity frequency spectrum of the flyer obtained by the system measurement are respectively shown in fig. 5 and fig. 6, and it can be seen from fig. 5 and fig. 6 that there is an obvious jump in the velocity curve when the flyer impacts on the LiF window. By processing the velocity spectrogram, the velocity history of the flight piece in the bore and the impact window can be obtained, and the free surface velocity, the impact time and the impact pulse width of the flight piece at the impact time of each measuring point position can be further read out (the free surface velocity of the flight piece can reflect the acceleration process of the flight piece, and the interface particle velocity of the flight piece impacting the transparent window can be read out to obtain the information of the impact time, the impact pulse width and the like).
Based on the mechanism that the loading pulse width generated when the material of the impact window (i.e., LiF window) is selected is determined by the thickness of the flyer and the interface particle velocity (or flyer impact velocity) of the flyer impact window, the present embodiment can characterize the flyer thickness according to the pulse width when obtaining the flyer velocity (or interface particle velocity).
In the embodiment, sufficient measuring points are arranged on the surface of the flyer, so that the measurement of the free velocity history and the interface particle velocity history of different spatial positions can be realized, and the attitude information such as the integrity, the planarity and the like of the flyer can be obtained by performing correlation analysis and interpretation on the data in time and spatial dimensions.
The integrity of the flyer (the effective area of the flyer) is represented by the existence of the measuring point signals at different spatial positions; representing the planarity (the shape of a collision surface) of the flying piece by the time difference of the flying piece of each measuring point impacting a transparent LiF window; the relative difference in flying disc thickness (thickness from collision surface to driving surface) is characterized by the pulse width of each station flying disc striking the LiF window. And assuming that the flyer has no phenomena of lamination, delamination and the like, the three-dimensional posture of the flyer before impact can be reconstructed according to the phenomena.
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 (8)
1. A flying piece attitude dynamic characterization method is characterized by comprising the following steps:
simultaneously measuring by adopting a flyer velocity field measuring system based on spatial resolution to obtain flyer free surface velocities at different spatial positions and a flyer impact transparent window interface particle velocity process;
the flying piece velocity field measurement system based on spatial resolution comprises a transparent window, a microscopic PDV speed measurement probe, a multi-point PDV speed measurement host, a high-broadband digital oscilloscope and a data processing device;
the transparent window is arranged at the outlet of the bore of the impact sheet detonator component;
the microscopic PDV speed measurement probe enables laser emitted by the multi-point PDV speed measurement host to penetrate through the transparent window according to preset measuring point distribution and then to be projected to the surface of a flying piece in a gun bore;
the microscopic PDV speed measurement probe collects the return light of different measuring point positions on the surface of the flyer and transmits the return light to the multi-point PDV speed measurement host;
the multi-point PDV speed measurement host generates an optical interference signal corresponding to Doppler frequency shift caused by the movement of the flyer, converts the optical interference signal into a corresponding high-frequency electric signal and transmits the high-frequency electric signal to the high-broadband digital oscilloscope; the multi-point PDV speed measurement host is provided with a measurement channel matched with the number of measurement points of the microscopic PDV speed measurement probe;
the high-broadband digital oscilloscope is used for recording high-frequency electric signals output by the multi-point PDV speed measurement host;
the data processing device is used for analyzing and processing the high-frequency electric signals recorded by the high-bandwidth digital oscilloscope to obtain the flying piece free surface speeds of different measuring points and the interface particle speed history of the flying piece impacting the transparent window so as to represent the flying piece posture;
time and space correlation analysis is carried out on the speed of the free surface of the flyer at different spatial positions and the speed history of the flyer impacting transparent window interface particles, and attitude information of the flyer can be obtained; the association parsing process specifically includes:
obtaining the free surface speed, the interface particle speed, the impact time and the impact pulse width according to the free surface speed of the flyer and the interface particle speed process of the flyer impacting the transparent window;
representing the integrity of the flyer according to the existence of measuring point signals at different spatial positions;
representing the planarity of the flyers according to the time difference of the flyers at different spatial positions impacting the transparent window;
calculating the thickness of the flyer at each space position according to the pulse width at the space position;
and characterizing the relative difference of the thicknesses of the flyers at different spatial positions according to the pulse widths of the flyers at the different spatial positions, which impact the transparent window.
2. The flying piece attitude dynamic characterization method according to claim 1, wherein the transparent window is machined from lithium fluoride, organic glass or sapphire.
3. The flying piece attitude dynamic characterization method according to claim 1, wherein the microscopic PDV speed probe is provided with 7-81 measuring points within the bore diameter of 0.45-0.60 mm, and the measuring points are distributed without overlapping within the bore height range.
4. The flying-film attitude dynamic characterization method according to claim 1, wherein the micro PDV speed probe adopts a non-imaging mode based on a lens array or an imaging mode based on a single lens or a lens group.
5. The flying piece attitude dynamic characterization method according to claim 1, wherein the transparent window is a lithium fluoride window, the window thickness is millimeter-scale, and antireflection coatings are plated on both sides.
6. The flying piece attitude dynamic characterization method according to claim 1, wherein the micro PDV speed measurement probe adopts a compact fiber array probe, 19 measurement points are distributed in total, and the 19 measurement points can cover the characteristic area of the bridge foil.
7. The flying piece attitude dynamic characterization method according to any one of claims 1-6, wherein the high-bandwidth digital oscilloscope meets the bandwidth and sampling rate requirements of the PDV velocity measurement host for measuring the velocity of the flying piece before impact.
8. The flying blade attitude dynamic characterization method according to any one of claims 1-6, further comprising:
and reconstructing the three-dimensional posture of the flyer when the flyer impacts the transparent window according to the integrity, the planarity, the thickness and the relative difference of the thickness of the flyer.
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| CN111912302B (en) * | 2020-07-22 | 2022-04-15 | 北京理工大学 | Detonation-driven flyer impact multi-sample insensitive high-energy explosive impact detonation test system |
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