Spatial resolution adaptive directional warhead damage power measuring method and computing device

Abstract

The invention provides a spatial resolution adaptive directional warhead damage power measuring method and computing equipment, the method is used for an acquisition structure of double-layer PCB sensing nodes arranged in front of and behind a target board, and the method comprises the following steps: acquiring a first penetration moment signal; calibrating a space coordinate of each sensing node; calculating a first incident angle of the elastic sheet, a first flight speed before the elastic sheet penetrates through the target plate and a second flight speed after the elastic sheet penetrates through the target plate; recognizing front and back sensing node pairs belonging to the same elastic sheet; according to a target spatial resolution, aggregating the front and back sensing node pairs, and generating a damage evaluation index including elastic sheet density and a potential energy average attenuation coefficient; and realizing three-dimensional visual reduction of the damage effect based on the fused damage data. According to the technical scheme of the invention, the method can achieve the precise capturing of the first penetration moment of the elastic sheet, achieves the precise calculation of the incident angle and the speed change, is adaptive to the wide-range spatial resolution, and improves the accuracy and reliability of the damage power evaluation.

Description

A method and calculation device for measuring the destructive power of a directional warhead with spatial resolution adaptation Technical Field

[0001] This invention relates to the field of directional warhead damage testing technology, specifically to a method and computing device for measuring the destructive power of directional warheads with spatial resolution adaptation. Background Technology

[0002] As a key destructive unit in modern precision-strike weapon systems, the combat effectiveness of directional warheads highly depends on the accurate understanding of fragmentation field characteristics. The core of damage assessment lies in accurately acquiring key parameters such as the flight velocity, angle of incidence, spatial distribution density, and energy attenuation characteristics of the fragments in space. These parameters directly determine the warhead's penetration capability, kill radius, and damage mode, and are crucial for warhead design optimization, effectiveness verification, and tactical application.

[0003] Currently, most methods for testing the destructive power of directional warheads employ range measurement techniques based on sensor arrays. However, existing technologies still have several significant drawbacks: First, sensing nodes generally use a single sensor structure (such as a single-layer foil strip, a single-layer PCB, or optical fiber), which can only record the time information of the projectile passing through a certain position and cannot simultaneously acquire the trajectory changes of the projectile during penetration. Therefore, it is difficult to simultaneously calculate the incident angle and velocity changes, resulting in an incomplete characterization of the projectile's dynamic behavior. Second, some sensing nodes continue to acquire signals after being penetrated by high-speed projectiles, which may mistakenly capture secondary disturbances of the same projectile, interference from adjacent projectiles, or structural vibration noise, causing errors in the interpretation of the penetration time and seriously interfering with the accuracy of subsequent parameter inversion. Third, to adapt to the spatial resolution requirements of different test scenarios (such as high-density near-field assessment or wide-area far-field coverage), existing solutions usually require changing the sensor arrangement density, adjusting the target spacing, or reconstructing the hardware layout. This not only results in long deployment cycles and high labor costs, but also easily leads to poor consistency of multiple batches of test data due to mechanical errors and calibration deviations introduced by multiple assembly processes, affecting the comparability and credibility of the evaluation results.

[0004] Although existing studies have attempted to introduce multi-layer sensing or image recognition methods to improve measurement dimensions, the former is often limited by system complexity and signal crosstalk issues, while the latter is constrained by harsh environmental factors such as strong explosion light, smoke and dust obstruction, and high-speed motion blur, making it difficult to operate stably under actual combat testing conditions.

[0005] Therefore, a technical solution is needed that can accurately capture the moment of initial penetration by shrapnel, accurately calculate the changes in incident angle and velocity, adapt to a wide range of spatial resolutions, and improve the accuracy and reliability of damage assessment. Summary of the Invention

[0006] This application aims to provide a method and calculation device for measuring the destructive power of a directional warhead with spatial resolution adaptability, which can achieve accurate capture of the moment of initial penetration of shrapnel, accurate calculation of the incident angle and velocity changes, adaptability to a wide range of spatial resolutions, and improve the accuracy and reliability of destructive power assessment.

[0007] According to one aspect of this application, a method for measuring the destructive power of a directional warhead with spatial resolution adaptation is provided. The method is used in a data acquisition structure with sensing nodes arranged on a double-layer PCB board before and after a target plate. The method includes: acquiring the initial penetration time signals of the sensing nodes before and after the shrapnel penetrations; establishing a three-dimensional coordinate system based on the explosion origin and calibrating the spatial coordinates of each sensing node; calculating the first incident angle, the first flight velocity before penetration, and the second flight velocity after penetration of the shrapnel based on the penetration time and spatial position of the sensing nodes; identifying pairs of sensing nodes belonging to the same shrapnel based on matching degree; and aggregating the pairs of sensing nodes using a fusion algorithm according to the target spatial resolution to generate a damage assessment index including shrapnel density and average potential energy attenuation coefficient.

[0008] According to some embodiments, the method further includes: constructing a three-dimensional distribution cloud map of the projectile velocity based on the data of the preceding and following sensing node pairs: summarizing the velocity data of all the preceding and following sensing node pairs, classifying the velocity data in combination with the spatial orientation information of the sensing nodes to obtain the projectile velocity data under each coordinate, dividing the projectile velocity data under each coordinate into a three-dimensional grid, filling the velocity data into the three-dimensional grid, calculating the average velocity of the projectile in each of the three-dimensional grids, and constructing a three-dimensional distribution cloud map of the projectile velocity based on the average velocity of the projectile.

[0009] According to some embodiments, the double-layer PCB board is symmetrically laid on the front and back sides of the target board, arranged at a set interval in the vertical direction, and arranged in a column on the left and right sides of the target board center in the horizontal direction. Each column contains multiple sensing nodes, and each sensing node only records the first penetration time.

[0010] According to some embodiments, the first incident angle The calculation formula is: ,in, H is the first incident angle. p L represents the vertical height of the sensing node on the double-layer PCB board. O The distance from the front of the sensing node on the double-layer PCB board to the origin of the explosion is denoted as 'horizontal distance'.

[0011] According to some embodiments, the formula for calculating the initial velocity of the shrapnel before penetrating the target plate is as follows: , Where V1 is the initial velocity of the shrapnel before penetrating the target plate, and S1 is the initial distance traveled by the shrapnel before penetrating the target plate. The moment of the explosion's initiation. The moment when the front panel of the double-layer PCB sensing node is first penetrated; the formula for calculating the second flight velocity of the shrapnel after penetrating the target board is as follows: , Where V2 is the second velocity of the shrapnel after penetrating the target plate, and S2 is the second distance the shrapnel travels after penetrating the target plate. The thickness of the target plate is given. The moment when the back panel of the sensing node of the double-layer PCB board is first penetrated.

[0012] According to some embodiments, the matching degree is defined as: γ = w1×γ1 + w2×γ2 + w3×γ3, where γ is the matching degree. The angular consistency coefficient, This is the time series rationality coefficient. The spatial location correlation coefficient, These are the weighting coefficients.

[0013] According to some embodiments, identifying front and rear sensing node pairs belonging to the same spring clip based on matching degree includes: calculating the matching degree of each sensing node in the front and rear double-layer PCB boards; based on a preset matching degree model, performing correlation analysis on all possible combinations of front and rear board sensing nodes to identify front and rear sensing node pairs formed by continuous penetration of the same spring clip: if the matching degree of a certain front board sensing node and a certain rear board sensing node is greater than a preset matching degree threshold, then it is determined to be the front and rear sensing node pair of the same spring clip penetration; if a certain front board sensing node matches multiple rear board sensing nodes, then the rear board sensing node with the highest matching degree is selected as the front and rear sensing node pair of the same spring clip penetration; if a certain front board sensing node does not have a matching rear board sensing node, then it is determined to be invalid data and is discarded.

[0014] According to some embodiments, based on the target spatial resolution, the preceding and following sensing node pairs are aggregated using a fusion algorithm to generate damage assessment indices including fragment density and average potential energy attenuation coefficient. This includes: calculating the number of native sensing nodes to be aggregated based on the target resolution; dividing the fusion units based on the number of native sensing nodes, such that each fusion unit corresponds to a spatial region under the target resolution; and calculating the fragment density and average potential energy attenuation coefficient based on the preceding and following sensing node matching pair data within each fusion unit.

[0015] According to some embodiments, based on the target spatial resolution, the preceding and following sensing node pairs are aggregated using a fusion algorithm to generate a damage assessment index that includes fragment density and average potential energy attenuation coefficient. The method also includes: verifying the reliability of the fused data based on the calculated local fragment density and potential energy attenuation coefficient; calculating a first relative error between the fragment density of the fused unit and the fragment density of the corresponding original local region, and a second relative error between the average potential energy attenuation coefficient and the average potential energy attenuation coefficient of the corresponding original local region; if the first relative error is not greater than a first relative error threshold and the second relative error is not greater than a second relative error threshold, then the fusion is deemed effective; if the first relative error and / or the second relative error exceed the threshold, then the fusion is deemed to have failed, and the fusion index needs to be readjusted and recalculated until the error meets the requirements.

[0016] According to some embodiments, the first penetration time signal is preprocessed to remove the first penetration time signal with a duration less than a first time signal threshold; the calculated first flight speed and second flight speed are filtered to remove abnormal speed data.

[0017] According to another aspect of this application, a computer program product is provided, characterized in that it includes a computer program that, when executed by a processor, implements the method described in any of the preceding claims.

[0018] According to another aspect of this application, a computing device is provided, comprising: a processor; and a memory storing a computer program that, when executed by the processor, causes the processor to perform the method as described in any of the preceding claims.

[0019] According to another aspect of this application, a non-transitory computer-readable storage medium is provided, having stored thereon computer-readable instructions that, when executed by a processor, cause the processor to perform the method as described in any of the preceding claims.

[0020] According to the embodiments of this application, the technical solution of the present invention is based on the precise spatial position of the sensing nodes on the dual PCB board and the penetration timing recorded by them. It can accurately calculate the first incident angle, flight distance, and flight speed of the projectile before and after penetrating the target board, and then analyze its kinetic energy attenuation characteristics. By dynamically adjusting the data aggregation granularity through the fusion algorithm, it can achieve any spatial resolution within the range of 0.05m to 1m without modifying the hardware. Finally, the fused high-dimensional damage data is used to construct a three-dimensional visualization effect of the projectile's velocity, density, and energy distribution, fully restoring the spatial characteristics of the warhead's damage power, and significantly improving the accuracy, flexibility, and engineering practicality of damage testing.

[0021] According to some embodiments, the dual-node first-penetration sensing mechanism of the present invention effectively suppresses subsequent interference signals and ensures the reliability of core parameter inversion; the standardized single-target design supports rapid deployment and batch replication, significantly shortening the test preparation cycle; the software-driven resolution adaptation eliminates the dependence on hardware reconstruction in traditional methods, reduces costs and improves the consistency of multi-scenario data; and the final generated three-dimensional damage effect not only intuitively presents the spatial distribution pattern of the fragmentation field, but also provides a highly reliable quantitative basis for warhead performance evaluation, structural optimization and combat application.

[0022] It should be understood that the above general description and the following detailed description are merely exemplary and do not limit this application. Attached Figure Description

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below.

[0024] Figure 1A shows a schematic diagram of the acquisition structure in a method for measuring the destructive power of a directional warhead with spatial resolution adapted according to an example embodiment.

[0025] Figure 1B shows a schematic diagram of the composition of a movable target frame according to an example embodiment.

[0026] Figure 1C shows a schematic diagram of the acquisition structure in a method for measuring the destructive power of a spatially resolution-adapted directional warhead according to another example embodiment.

[0027] Figure 2A shows a schematic diagram of the actual data acquisition equipment setup in a spatial resolution-adapted method for measuring the destructive power of a directional warhead according to an example embodiment.

[0028] Figure 2B shows a schematic diagram of the actual data acquisition equipment setup in a spatial resolution-adapted method for measuring the destructive power of a directional warhead according to another example embodiment.

[0029] Figure 3 shows a flowchart of a method for measuring the destructive power of a spatially resolution-adapted directional warhead according to an example embodiment.

[0030] Figure 4 shows a schematic diagram of the basic coordinate calibration of the sensing node in a method for measuring the destructive power of a directional warhead with spatial resolution adaptation according to an example embodiment.

[0031] Figure 5 shows a schematic diagram of the calculation of the first incident angle in a method for measuring the destructive power of a spatially resolution-adapted directional warhead according to an example embodiment.

[0032] Figure 6 shows a schematic diagram of the calculation of the first flight velocity in a method for measuring the destructive power of a directional warhead with spatial resolution adapted according to an example embodiment.

[0033] Figure 7 shows a schematic diagram of the second flight speed calculation in a spatial resolution-adapted method for measuring the destructive power of a directional warhead according to an example embodiment.

[0034] Figure 8 shows the acquisition effect of relatively uniform flight velocity of shrapnel in a spatial resolution-adapted method for measuring the destructive power of a directional warhead according to an example embodiment.

[0035] Figure 9 shows a block diagram of a computing device according to an exemplary embodiment. Detailed Implementation

[0036] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, they are provided so that this application will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar parts, and therefore repeated descriptions of them will be omitted.

[0037] Furthermore, the described features, structures, or characteristics can be combined in any suitable manner in one or more embodiments. Numerous specific details are provided in the following description to give a thorough understanding of embodiments of this application. However, those skilled in the art will recognize that the technical solutions of this application can be practiced without one or more of the specific details, or other methods, components, apparatuses, steps, etc., can be employed. In other instances, well-known methods, apparatuses, implementations, or operations are not shown or described in detail to avoid obscuring various aspects of this application.

[0038] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities can be implemented in software, in one or more hardware modules or integrated circuits, or in different network and / or processor devices and / or microcontroller devices.

[0039] The flowcharts shown in the accompanying drawings are merely illustrative and do not necessarily include all content and operations / steps, nor do they necessarily have to be performed in the described order. For example, some operations / steps can be broken down, while others can be combined or partially combined; therefore, the actual execution order may change depending on the specific circumstances.

[0040] It should be understood that although the terms first, second, third, etc., may be used herein to describe various components, these components should not be limited by these terms. These terms are used to distinguish one component from another. Therefore, the first component discussed below may be referred to as the second component without departing from the teachings of this application. As used herein, the term "and / or" includes all combinations of any one and more of the associated listed items.

[0041] The user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, data stored, data displayed, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties. Furthermore, the collection, use and processing of the relevant data must comply with the relevant laws, regulations and standards of the relevant countries and regions, and corresponding operation entry points are provided for users to choose to authorize or refuse.

[0042] Those skilled in the art will understand that the accompanying drawings are merely schematic diagrams of exemplary embodiments, and the modules or processes in the drawings are not necessarily essential for implementing this application, and therefore cannot be used to limit the scope of protection of this application.

[0043] The core of assessing the destructive power of directed-direction warheads lies in accurately acquiring key parameters such as the flight velocity, incident angle, and spatial distribution of shrapnel. Existing methods for measuring the destructive power of directed-direction warheads often employ a single-sensor design for sensing nodes, making it difficult to simultaneously capture changes in the incident angle and velocity of the shrapnel. Furthermore, some sensing nodes attempt to capture subsequent penetration signals even after being penetrated by shrapnel, leading to severe data interference. In addition, adapting spatial resolution in existing technologies relies on hardware structure adjustments, resulting in low deployment efficiency, high costs, and poor data consistency.

[0044] To address this, this application proposes a spatial resolution-adaptive method for measuring the destructive power of directional warheads. This method enables precise capture of the initial penetration moment of shrapnel, accurate calculation of the incident angle and velocity changes, and adaptation to a wide range of spatial resolutions, thereby improving the accuracy and reliability of destructive power assessment. Through the design of "dual PCB sensing nodes before and after the target plate," the initial penetration moment of the shrapnel is precisely captured. Based on the spatial position and penetration sequence of the dual sensing nodes, the initial incident angle of the shrapnel and its flight velocity before and after penetrating the target plate are deduced, and the velocity change relationship is analyzed. Combined with a fusion algorithm, a wide range of spatial resolution adaptation is achieved, improving testing efficiency and assessment accuracy.

[0045] The following description, in conjunction with the accompanying drawings, illustrates exemplary embodiments of this application.

[0046] Referring to Figures 1A, 1B, 1C and 2A, 2B, the directional warhead destructive power measurement device consists of a flexibly assembleable three-dimensional target frame and a high-speed signal acquisition system. The target frame is composed of multiple movable units that can be combined into an arc-shaped structure with a diameter of 3 to 10 meters and an angle of 90° to 360°, depending on the blast radius and direction. Each unit is equipped with pulleys, lifting feet, and counterweights for easy movement, fixation, and to prevent tipping. The target plate uses low-density foam board for support, with PCB boards with spiral conductive circuits attached to both sides. When the shrapnel penetrates, it causes an open circuit, generating a trigger signal.

[0047] The signal acquisition system includes multiple high-speed analog switches and a portable acquisition terminal. Signals from the PCB board are connected to the acquisition card via switches, and the sampling frequency is dynamically adjusted based on the warhead velocity and foam thickness (typically from 20 kHz to over 100 kHz). The system uses a TTL external trigger to achieve precise synchronization between warhead detonation and data acquisition, ensuring high timeliness and accuracy. The overall design supports rapid installation, high spatial resolution, and reliable signal capture, making it suitable for various combat-oriented testing scenarios.

[0048] The number of movable target frames for the directional warhead damage measurement device in this embodiment is determined based on the size and direction of the explosion. Multiple movable target frames are combined to form an arc structure with corresponding diameter and angle. The positions of the target frames are adjusted and fixed. A movable counterweight is placed at the front end of each target frame. The assembled target plate is installed on each target frame. The circuit connection between the PCB board and the multi-channel high-speed analog switch and portable acquisition terminal is completed. The explosion trigger mechanism of the warhead is linked through a TTL external trigger to ensure that the explosion signal and the chip control signal are synchronized.

[0049] Specifically, the device for measuring the destructive power of a directional warhead includes a 360° three-dimensional assembled target frame 101 and a high-speed signal acquisition device. The 360° three-dimensional assembled target frame 101 is composed of multiple movable target frames 1011, which are combined into arc-shaped structures of different diameters and angles according to the size of the explosion site and the direction of the explosion. According to some embodiments, the diameter of the arc-shaped structure formed by the 360° three-dimensional assembled target frame 101 ranges from 3 to 10 meters, and the angle ranges from 90° to 360°. The movable target frames 1011 can be independently translated and rotated.

[0050] According to an example embodiment, the high-speed signal acquisition device includes multiple assembled target boards 2011, multiple sets of multi-channel high-speed analog switches 2013, and a portable acquisition terminal 2015. The assembled target boards 2011 are mounted on the movable target frame 1011. Each assembled target board 2011 includes a support plate and multiple PCB boards 2013 disposed on the support plate. The PCB boards 2013 are used to generate an open-circuit signal when penetrated by a shrapnel. The multi-channel high-speed analog switches 2013 are electrically connected to the multiple PCB boards 2013 in the assembled target boards 2011 and are used to detect the open-circuit signal. The portable acquisition terminal 2015 has a high-speed acquisition card, and the input channel of the high-speed acquisition card is electrically connected to the signal output terminal of the multi-channel high-speed analog switches.

[0051] According to some embodiments, the portable acquisition terminal 2015 also has an external trigger interface for connecting to a TTL external trigger, which is used to simultaneously trigger the high-speed acquisition card to perform high-speed signal acquisition when the warhead is detonated. The input channel of the high-speed acquisition card is directly electrically connected to the signal output terminal of the multiple high-speed analog switches in a one-to-one connection mode. Alternatively, the input channel of the high-speed acquisition card is electrically connected to the signal output terminals of multiple high-speed analog switches in a many-to-one connection mode via a polling module.

[0052] According to some embodiments, the movable target frame 1011 has a wire protection groove 1021 on the outside of the support, which is used to centrally lay out the wires led out from the assembled target plate and connect them to the multi-channel high-speed analog switch. The bottom of the movable target frame 1011 may be provided with pulleys 1013 and hand-cranked lifting feet 1015 for realizing the free movement and fixation of the target frame.

[0053] According to some embodiments, four pulleys 1013 and four hand-cranked lifting feet 1015 may be provided. The front end of the movable target frame 1011 is provided with a trapezoidal counterweight area for placing movable counterweights to prevent overturning caused by explosive impact. When multiple target frames are spliced ​​into an arc shape, the target plate can be closed better.

[0054] According to some embodiments, the PCB board has a spiral conductive circuit extending from the center and covering the entire PCB board in a spiral manner. Two wires are led out from the PCB board to connect to one of the multiple high-speed analog switches. The PCB board 2013 is fixed to the support plate and can be pasted side by side on the support plate with tape, covering both sides of the support plate. The size and number of PCB boards required for a single target frame are set according to the spatial resolution required by the test object. The support plate includes a foam board, and the multiple PCB boards cover both sides of the foam board. The foam board can be a low-density foam board, or it can be replaced with other materials of different densities and thicknesses according to the test requirements, providing support for testing the different attenuation effects of the potential energy of the spring.

[0055] The modular target plate can be made of low-density polyurethane foam board with a density of 0.05~0.1 g / cm³, and the thickness of the foam board can be adjusted according to the estimated fragment velocity. For example: Scenario 1: When the estimated fragment velocity is 1000 m / s, the time to penetrate a 10 cm thick foam board is 100 microseconds, corresponding to a high-speed acquisition card sampling frequency ≥20 kHz. Scenario 2: When the estimated fragment velocity is 5000 m / s, the time to penetrate a 10 cm thick foam board is 20 microseconds, corresponding to a high-speed acquisition card sampling frequency ≥100 kHz. Scenario 3: When the estimated fragment velocity is 5000 m / s, the time to penetrate a 20 cm thick foam board is 40 microseconds, corresponding to a high-speed acquisition card sampling frequency ≥50 kHz.

[0056] According to some embodiments, each movable target frame is equipped with multiple high-speed analog switches. All leads from the PCB boards are electrically connected to the signal input terminals of the corresponding high-speed analog switches on the target frame, ultimately converging to the high-speed analog switches. The number of PCB boards required for a single target frame determines the number of high-speed analog switches required for that target frame; for example, 16 switches correspond to 16 PCB boards. According to some embodiments, 16-channel standard switch chips are selected, with a response time ≤15ns, on-resistance ≤5Ω, operating voltage +5V, signal input range ±15V, and a QFN package (5mm×5mm). Multiple chips can also be combined based on the number of PCB boards in a single target frame; the number of chips installed in a single target frame is determined by the number of PCB boards configured for it.

[0057] According to some embodiments, to facilitate mass production and reduce experimental costs, the thinnest industrial board can be selected for the PCB board, the finest line width for the internal circuitry, and the densest wiring spacing. The working principle is that when the spring penetrates the PCB board, the spiral conductive circuit inside the PCB board is broken, thereby determining that the PCB board has been penetrated by the spring.

[0058] The PCB board of the measuring device in this example adopts a quick-installation and quick-removal design, with comprehensive spiral conductive circuitry for accurate capture of the shrapnel penetration signal. The high-speed analog switch provides a response time in the nanosecond range, fully meeting the high-frequency acquisition requirements of the shrapnel penetration signal and avoiding signal loss due to mechanical delays. A TTL external trigger enables synchronous start-up of the explosion and acquisition, significantly improving the synchronization and timeliness of signal acquisition and ensuring accurate calculation of the shrapnel flight parameters.

[0059] The number of movable target frames for the directional warhead damage measurement device in this embodiment is determined based on the size and direction of the explosion. Multiple movable target frames are combined to form an arc structure with corresponding diameter and angle. The positions of the target frames are adjusted and fixed. A movable counterweight is placed at the front end of each target frame. The assembled target plate is installed on each target frame. The circuit connection between the PCB board and the multi-channel high-speed analog switch and portable acquisition terminal is completed. The explosion trigger mechanism of the warhead is linked through a TTL external trigger to ensure that the explosion signal and the chip control signal are synchronized.

[0060] Figure 3 shows a flowchart of a method for measuring the destructive power of a spatially resolution-adapted directional warhead according to an example embodiment.

[0061] Referring to Figure 3, a method for measuring the destructive power of a directional warhead with spatial resolution adaptation is shown. According to some embodiments, the method uses a data acquisition structure with sensing nodes arranged on a double-layer PCB board in front of and behind a target plate. The double-layer PCB board is symmetrically laid on both sides of the target plate, arranged at a set interval in the vertical direction, and in two columns on either side of the target plate center in the horizontal direction. Each column contains multiple sensing nodes, and each sensing node only records the initial penetration time. Specifically, the acquisition architecture adopts a "single target frame fixed hardware configuration + double PCB board sensing nodes in front of and behind the target plate + multi-target frame combination enclosure." PCB board sensing nodes are symmetrically laid on the front and back of the target plate of each target frame (each sensing node only records the initial penetration time), arranged with fixed precision and acquiring penetration signal data. This enables accurate capture of the initial penetration time of the shrapnel, accurate calculation of the incident angle and velocity changes, adaptation to a wide range of spatial resolutions, and improvement of the accuracy and reliability of destructive power assessment. The specific steps of the method are as follows.

[0062] In S101, the first penetration moment signal of the sensing node of the double-layer PCB board before and after the spring clip penetrates is collected.

[0063] According to some embodiments, raw data is first acquired using a device with a data acquisition structure consisting of sensing nodes on a double-layer PCB board positioned before and after the target plate. Referring to examples in Figures 1 and 2, each target holder is equipped with a target plate of a specified thickness (e.g., L). 厚=0.1m (can be adjusted as needed) PCB sensing nodes are symmetrically laid on both sides of the target board. Specifically, PCB boards of "5cm×60cm" size can be used, laid out in one column on each side of the target board, with a horizontal offset of ±0.6m and a vertical arrangement with a precision of 5cm. 80 boards are laid on each side of the target board, for a total of 160 PCB sensing nodes, corresponding to 10 sets of "multi-channel high-speed analog switches" and 1 "polling module". Each sensing node corresponds to one switch channel. Each set of "multi-channel high-speed analog switches" can convert 16 analog switch channel input signals into one 16-bit "0-1" digital signal output. This output digital signal corresponds to one input channel of the "polling module". The "polling module" serially connects the 10 parallel input digital signals in a fixed order and outputs one digital signal. Generally, the input and output signals of the "polling module" can be either digital or analog signals, both of which can achieve the same logical function. The input-to-output ratio of the "polling module" is 1:10; if the high-speed acquisition card collects the data output by the "polling module" at a sampling rate ≥10MHz on a single channel, it can acquire all the raw data of a single target. Generally, the time resolution of shrapnel penetration of the sensing node is 1 microsecond.

[0064] According to some embodiments, in actual data acquisition scenarios, multiple single target frames can be combined into a 90°~360° arc structure according to the needs of the explosion acquisition area, such as a range of 3~10 meters in diameter, to ensure seamless connection of adjacent target frame sensing nodes. Each target frame transmits the acquired data to a portable acquisition terminal through its own polling module, completing the aggregation and integration of all raw data to form a raw dataset covering the entire explosion area, which is the first penetration moment signal of the double-layer PCB board sensing node before and after shrapnel penetration.

[0065] According to some embodiments, this invention employs a symmetrical arrangement of two PCBs, one before and one after the target plate. The PCBs can only sense the initial penetration moment, thus avoiding interference from subsequent penetration signals from a hardware design perspective. Simultaneously, it provides accurate dual-point data support for calculating the incident angle and velocity changes of the projectile. This dual-node design scheme is not found in existing publicly available technologies and solves the technical problem that a single node cannot obtain the trajectory and velocity changes of the projectile.

[0066] In S103, a three-dimensional coordinate system is established based on the explosion origin to calibrate the spatial coordinates of each sensing node.

[0067] Figure 4 shows a schematic diagram of the basic coordinate calibration of the sensing node in a method for measuring the destructive power of a directional warhead with spatial resolution adaptation according to an example embodiment.

[0068] According to some embodiments, referring to Figure 4, a three-dimensional coordinate system can generally be established with the explosion origin O as the reference. Referring to the example in Figure 4, the XOY plane can be taken as the horizontal ground and the Z-axis as the direction perpendicular to the ground to complete the basic coordinate calibration of the sensing nodes before and after the target plate.

[0069] According to some embodiments, firstly, the coordinates of the target plate's center are determined. Assume that the distance between a target plate and the origin of the explosion is L. O (Unit: m, i.e., the straight-line distance from the center of the front side of the target plate in the XOY plane to point O), the angle between the orientation of the target plate and the positive X-axis is β (unit: °, used to distinguish the horizontal orientation of different target plates), then the center coordinates of the target plate are (L O ×cosβ,L O ×sinβ,0(The target plate center is located on the ground, and the Z coordinate is 0).

[0070] Next, the coordinates of the sensing nodes are calibrated. Since the sensing nodes are arranged in only one column on each side of the target plate, and the horizontal coordinates are based on the center of the target plate, the horizontal coordinates of the left and right columns of nodes are consistent with the center of the target plate. The vertical coordinates are determined by the number of rows. The vertical position of the bottom-level sensing node is set to 0 (i.e., Z=0), and the vertical offset increases by 5cm (0.05m) for each row upwards. Assuming that for any sensing node P, its column is labeled C (C=1 represents the left column, C=2 represents the right column), and its vertical arrangement number is k (k=0, 1, 2, ..., k=0 corresponds to the bottom layer), then the formula for the absolute spatial coordinates of node P is: P(x... p y p , z p ):x p =L O ×cosβ (Horizontal coordinate is aligned with the target center, with no horizontal offset) y p =L O ×sinβ (Horizontal coordinate is aligned with the target center, with no horizontal offset) z p =H p =k×0.05m(H p (The vertical height of the node, i.e., the vertical offset) is further used to distinguish the sensing nodes of the front and rear plates. Let the target plate thickness be L. 厚 (Unit: m) The normal direction of the target plate is along the line connecting the center of the target plate and the origin of the explosion (i.e., the OL direction). Then, the sensing node on the side of the target plate closer to the origin of the explosion is the front sensing node P. 前 The node P on the side furthest from the explosion origin is the post-sensing node. 后 The Z coordinates of the two are completely identical (i.e., the vertical height is the same), and the difference in X and Y coordinates is determined by the thickness of the target plate, as shown in the following formula.

[0071]

[0072] Referring to Figure 4, the normal direction of the target plate is the line OL. The front sensing node is located on the side of the target plate closer to point O, at a distance L from point O. O The post-sensing node is located on the side furthest from point O, at a distance of L. O +L 厚 Both have a horizontal azimuth angle of β, so the X and Y coordinates are corrected according to the above formula, while the vertical height remains consistent.

[0073] In S105, based on the penetration time and spatial position of the sensing nodes of the double-layer PCB board mentioned before and after, the first incident angle of the shrapnel, the first flight speed before penetrating the target board, and the second flight speed after penetrating the target board are calculated.

[0074] Figure 5 shows a schematic diagram of the calculation of the first incident angle in a method for measuring the destructive power of a spatially resolution-adapted directional warhead according to an example embodiment.

[0075] According to some embodiments, referring to Figure 5, the first incident angle α is the angle between the trajectory of the shrapnel and the XOY plane (horizontal ground), based on the vertical height H of the sensing node. p The distance L from the front edge of the target plate to the origin of the explosion O Derivation and calculation. Specifically, a geometric relationship analysis is performed first. Referring to the example in Figure 5, the trajectory of the shrapnel flying from the explosion origin O to the sensing node P can be regarded as a line segment from point O to point P (ignoring trajectory deviation caused by air resistance). With point O as the vertex and OL as the horizontal side (length L)... O The projection of line segment OP onto the Z-axis is H. p (Vertical side) forms a right triangle OLP, where ∠OLP is a right angle, and α is ∠LOP (the angle between the trajectory of the shrapnel and the horizontal side) in this right triangle.

[0076] In a right triangle, the tangent is equal to the ratio of the opposite side to the adjacent side, i.e., tanα = H. p / L O Therefore, the first incident angle The calculation formula is: ,in, H is the first incident angle. p L represents the vertical height of the sensing node on the double-layer PCB board. O The horizontal distance from the front of the sensing node on the double-layer PCB board to the origin of the explosion is α. The value of α ranges from 0° to 90° (α=0° indicates the shrapnel flies horizontally, α=90° indicates the shrapnel flies vertically upwards); H p For the vertical height of the sensing node (k×0.05m), L O The distance from the front of the target plate to the origin of the explosion (unit: m).

[0077] Figure 6 shows a schematic diagram of the calculation of the first flight velocity in a method for measuring the destructive power of a directional warhead with spatial resolution adapted according to an example embodiment.

[0078] According to some embodiments, referring to Figure 6, based on the first incident angle α, the trajectory of the shrapnel from the explosion origin O to the forward sensing node P is calculated. 前 The first flight distance S1, combined with the flight time, is used to calculate the first flight velocity V1. The formula for calculating the first flight velocity of the shrapnel before penetrating the target plate is as follows: , Where V1 is the initial velocity of the shrapnel before penetrating the target plate, and S1 is the initial distance traveled by the shrapnel before penetrating the target plate. The moment of the explosion's initiation. The moment when the front panel of the sensing node on the double-layer PCB is first penetrated. Specifically, based on the geometric relationship of a right-angled triangle, the length of the shrapnel flight trajectory (from O to P) is... 前 The straight-line distance (where S is the hypotenuse) is given by P. 前 The vertical height is H p L O Let be the distance from the front of the target plate to the origin of the explosion. It is also known that the explosion occurred at time t0, and the shrapnel reached point P. 前 The time is t1 (by P) 前 First penetration signal capture (unit: s), then the shrapnel will reach P. 前 The previous formula for calculating the flight speed V1 was: V1 = S1 / (t1 - t0). Since the sensing node only captures the moment of the first penetration, t1 - t0 accurately reflects the distance of the shrapnel from point O to point P. 前 Flight time.

[0079] Figure 7 shows a schematic diagram of the second flight speed calculation in a spatial resolution-adapted method for measuring the destructive power of a directional warhead according to an example embodiment.

[0080] According to some embodiments, referring to Figure 7, before and after the shrapnel penetrates the sensing node P, it continues to penetrate the target plate at the first incident angle α. Based on α and the target plate thickness L, the second flight distance S2 after penetrating the target plate is calculated. Combining the time difference of penetration between the sensing nodes before and after, the second flight velocity V2 is calculated. The formula for calculating the second flight velocity of the shrapnel after penetrating the target plate is as follows: , Where V2 is the second velocity of the shrapnel after penetrating the target plate, and S2 is the second distance the shrapnel travels after penetrating the target plate. The thickness of the target plate is given. The moment when the back panel of the sensing node on the double-layer PCB is first penetrated. Specifically, when the spring penetrates the target board at the first incident angle α, the target board thickness L... 厚Let L be the projected length of the shrapnel's trajectory in the horizontal direction (since the target's normal direction is horizontal, OL). Using trigonometric relationships, the horizontal projected length L... 厚 =S2×cosα, therefore, by reverse derivation we get: S2=L 厚 / cosα. Derivation basis: When the shrapnel flies at the first incident angle α, the angle between its trajectory and the horizontal direction is α. The target plate thickness (horizontal direction) is the projection of the trajectory in the horizontal direction. Therefore, the projection length and the actual flight distance are related by a cosine function. This formula applies to α∈[0°, 90°) (when α=90°, the shrapnel flies vertically and cannot penetrate a horizontally arranged target plate, so it is excluded). After the shrapnel arrives, the sensing node P... 后 The time is t2 (by P) 后 The initial penetration signal acquisition (unit: s) indicates that the flight time of the shrapnel during penetration of the target plate is Δt = t2 - t1. The second flight velocity V2 is calculated using the formula: V2 = S2 / Δt. Furthermore, because the shrapnel originates from P... 前 Fly to P 后 During the process, it only penetrates the target plate. The second flight distance is S2, and the flight time is the time difference Δt between the penetration of the front and rear sensing nodes. Therefore, the speed is the ratio of S2 to Δt.

[0081] Existing technologies lack precise calculation schemes for incident angles and cannot effectively identify the correspondence between sensing nodes before and after shrapnel penetration at different incident angles, resulting in severe distortion of velocity data. This invention innovatively proposes a three-dimensional matching degree model based on angle consistency, temporal rationality, and spatial correlation, achieving precise identification of the correspondence between sensing nodes before and after shrapnel penetration at different incident angles. Simultaneously, it establishes "S1=H..." p S2=L 厚 The system for calculating flight distance using the " / cosα" formula, combined with the penetration time difference, calculates V1 and V2 separately, and finally summarizes the data to construct a three-dimensional velocity distribution, thus fully realizing a comprehensive representation of the velocity of the fragments in different directions and at different altitudes. This calculation system solves the technical pain points of existing technologies, such as difficulty in node matching and incomplete velocity distribution representation, and has significant innovation.

[0082] In S107, the pair of front and rear sensing nodes belonging to the same piece of shrapnel are identified based on the matching degree.

[0083] According to some embodiments, front and rear sensing node pairs belonging to the same spring contact are identified based on the matching degree, and the matching degree of each sensing node in the front and rear double-layer PCB boards is calculated. Based on the matching degree, correlation analysis is performed on all possible combinations of front and rear board sensing nodes to identify front and rear sensing node pairs formed by continuous penetration of the same spring contact: if the matching degree of a certain front board sensing node and a certain rear board sensing node is greater than a preset matching degree threshold, it is determined to be the front and rear sensing node pair of the same spring contact penetration; if a certain front board sensing node matches multiple rear board sensing nodes, the rear board sensing node with the highest matching degree is selected as the front and rear sensing node pair of the same spring contact penetration; if a certain front board sensing node does not have a matching rear board sensing node, it is determined to be invalid data and is discarded.

[0084] According to some embodiments, the matching degree is defined as: γ = w1×γ1 + w2×γ2 + w3×γ3, where γ is the matching degree. The angular consistency coefficient, This is the time series rationality coefficient. The spatial location correlation coefficient, These are weighting coefficients. Due to different incident angles α, the post-perception node P after being penetrated by the same piece of shrapnel... 后 With the previous sensing node P 前 Nodes that are not at the same vertical height may need to be identified through angle matching and temporal correlation.

[0085] Specifically, the trajectory of the same shrapnel is continuous, the first incident angle α remains unchanged, and it penetrates P. 前 The moment t1 must be earlier than the moment P is penetrated. 后 The time t2 (t2>t1) is defined. First, a measure is defined for the pre-perception node P. 前 With the post-perception node P 后 The degree of matching, γ, is composed of three dimensions: angular consistency, temporal rationality, and spatial location correlation.

[0086] Where γ1 is the angular consistency coefficient, γ1=1-|α 前 -α 后 | / 90°(α 前 For P 前 The corresponding incident angle, α 后 For P 后 The corresponding incident angle, α 前 With α 后 The smaller the difference, the closer γ1 is to 1, and the better the angular consistency.

[0087] γ2 is the time series rationality coefficient; if t2-t1>t minIf t , then γ2 = 1; otherwise γ2 = 0, where t min =L 前后 / 3000 is the minimum possible time, L 前后 = H 前后 =|z 前 -z 后 The typical flight speed of shrapnel is 1000m / s to 3000m / s.

[0088] γ3 is the spatial correlation coefficient, γ3=1-|z 先 -z 后 | / Z max (z) 先 =z 前 +L 厚 ×tgα 前 To use P 前 Z coordinate and α 前 The predicted Z-coordinate of the node after the breakdown, z 后 For P 后 Z coordinate, Z max (This represents the maximum vertical height of the sensing nodes on the target board; the smaller the difference, the better the spatial correlation.)

[0089] w1, w2, and w3 are weights that satisfy w1 + w2 + w3 = 1. Generally, they can be set according to the testing requirements, for example, w1 = 0.4, w2 = 0.2, and w3 = 0.4.

[0090] According to some embodiments, by setting a matching threshold γ0, such as γ0=0.8, if a certain P 前 With a certain P 后 If the matching degree γ≥γ0, then the two are determined to be a pair of sensing nodes before and after the same shrapnel penetration; if a P 前 Corresponding to multiple P 后 Select P with the largest γ 后 As a matching node; if P 前 No matching P 后 (or vice versa), then it is determined to be invalid data and is removed.

[0091] In S109, based on the target spatial resolution, the pair of front and rear sensing nodes are aggregated using a fusion algorithm to generate a damage assessment index that includes fragment density and average potential energy attenuation coefficient.

[0092] According to some embodiments, based on the target spatial resolution, the preceding and following sensing node pairs are aggregated using a fusion algorithm to generate damage assessment indicators including fragment density and average potential energy attenuation coefficient. The number of original sensing nodes to be aggregated is calculated based on the target resolution. Fusion units are then divided based on the number of original sensing nodes, with each fusion unit corresponding to a spatial region at the target resolution. Based on the preceding and following sensing node matching data within each fusion unit, fragment density and average potential energy attenuation coefficient are calculated respectively. Based on the calculated fragment velocity data, preceding and following sensing node matching data, and original sensing data, the aggregation granularity is adjusted using the fusion algorithm to achieve adaptation to any spatial resolution from 0.05m to 1m. For specific regions at different resolution sizes, core assessment indicators such as fragment density and average potential energy attenuation coefficient are fused. By aggregating the data of preceding and following sensing node pairs using a fusion algorithm according to the target spatial resolution, two damage assessment indicators, fragment density and average potential energy attenuation coefficient, can be accurately and quantitatively generated, improving the objectivity and quantitative accuracy of damage assessment. Using physically measurable "shrapnel density" and "average potential energy decay coefficient" as core indicators, this approach avoids the biases of traditional subjective or qualitative judgments, making the damage effect measurable, comparable, and reproducible. By dynamically adjusting the fusion and aggregation scale in conjunction with the target spatial resolution, it can assess the overall damage level as well as identify local weak areas, meeting the assessment needs of different mission scenarios (such as point targets vs. area targets).

[0093] According to some embodiments, firstly, the aggregation granularity and fusion region are defined. Based on the target resolution R (unit: m), the number of native sensing nodes to be aggregated is calculated (the horizontal direction is based on the target center as the coordinate, and the region is divided according to the target azimuth angle β).

[0094] According to some embodiments, the calculation formula for vertical aggregation granularity is as follows: N=ceil(R / 0.05), where ceil() is the rounding function, 0.05m is the vertical native precision (i.e., the set vertical spacing between sensing nodes), and N is the number of adjacent native sensing nodes in the vertical direction.

[0095] According to some embodiments, the horizontal region is then divided according to the target plate azimuth angle β. Each target plate corresponds to two regions in the same azimuth, with the left sensing node corresponding to the left region and the right sensing node corresponding to the right region. The "N native nodes in the vertical direction + the corresponding azimuth angle span region in the horizontal direction" is divided into a fusion unit. Each fusion unit corresponds to a spatial region at the target resolution, denoted as U. i (i is the fusion unit number).

[0096] According to some embodiments, for each fusion unit U, based on the effective front and rear sensing node matching pairs data within the unit (i.e., node pairs where the same fragment is penetrated), the fragment density and the average fragment potential energy attenuation coefficient are calculated respectively. For fragment density calculation: fragment density is defined as the number of effective fragments within a unit volume fusion area (effective fragments are fragments that successfully match front and rear sensing nodes), the formula is: ρ=M / V where ρ is the fragment density of fusion unit U (unit: fragments / m³); M is the number of effective fragments within U (i.e., the number of effective front and rear sensing node matching pairs within the unit); V is the volume of U (unit: m³), ​​calculated from the horizontal area and vertical height of the unit: V=S×H, where S is the horizontal area (determined by the azimuth span and the distance L from the target plate to the explosion origin) calculated by the formula S=(β / 360°)×πL², and H is the vertical height (N×0.05m). The potential energy of a fragment is proportional to the square of its velocity (E∝mv², where m is the mass of the fragment and is considered a constant). Therefore, the potential energy attenuation coefficient can be characterized by the velocity attenuation relationship and is defined as the ratio of the potential energy of a single fragment after penetrating the target plate to its potential energy before penetration. The average potential energy attenuation coefficient is the arithmetic mean of the potential energy attenuation coefficients of all effective fragments in the fusion unit, and the formula is: η=(1 / M)×Σ((v2²) / (v1²)) (j=1, 2, ..., M). Wherein, η is the average potential energy attenuation coefficient of the fragments in the fusion unit U (the value ranges from 0 to 1, and the closer it is to 0, the more obvious the potential energy attenuation); V1 and V2 are the flight velocities of the j-th effective fragment before and after penetration, respectively; if M=0 (there are no effective fragments in the unit), then η is a null value.

[0097] According to some embodiments, the preceding and following sensing node pairs are aggregated using a fusion algorithm to generate a damage assessment index including fragment density and average potential energy attenuation coefficient. The reliability of the fused data is verified based on the calculated local fragment density and potential energy attenuation coefficient: a first relative error between the fragment density of the fusion unit and the fragment density of the corresponding original local region, and a second relative error between the average potential energy attenuation coefficient and the average potential energy attenuation coefficient of the corresponding original local region are calculated. The reliability of the fused data is verified using the local fragment density and potential energy attenuation coefficient calculated from the original data as a benchmark. The first relative error ε1 between the fragment density of the fusion unit U and the fragment density of the corresponding original local region, and the second relative error ε2 between the average potential energy attenuation coefficient and the average potential energy attenuation coefficient of the corresponding original local region are calculated using the formulas: ε1=|(ρ-ρ) / ρ|×100%, ε2=|(η-η) / η|×100%, where ρ is the fragment density of the original local region, and η is the average potential energy attenuation coefficient of the original local region. By comparing the density and average potential energy attenuation coefficient of the fused fragments with the corresponding baseline values ​​of the original local region, the first relative error ε1 and the second relative error ε2 are calculated to determine whether the fusion is distorted using clear numerical indicators. This avoids the uncontrollable deviations that may be introduced by "black box" fusion, ensuring that the output damage indicators truly reflect the physical reality.

[0098] According to some embodiments, if the first relative error is not greater than a first relative error threshold and the second relative error is not greater than a second relative error threshold, the fusion is deemed effective. If the first relative error and / or the second relative error exceed the threshold, the fusion is deemed to have failed, and the fusion index needs to be readjusted and recalculated until the error meets the requirements. For example, if the first relative error is ≤5% and the second relative error is ≤5%, the fusion is effective. If either error exceeds the threshold, the aggregation granularity needs to be readjusted (increase / decrease N), and the fusion index needs to be recalculated until the error meets the requirements. When any error exceeds a preset threshold (e.g., 5%), a re-fusion process can be automatically triggered by dynamically adjusting the aggregation granularity (e.g., changing the number of sensing nodes N participating in the fusion or the size of the spatial partitioning unit) and recalculating the fusion index. This design achieves a "fusion-verification-correction" closed loop, significantly improving the adaptability and stability of the algorithm under complex battlefield environments or sensor noise interference.

[0099] According to some embodiments, this invention innovatively focuses on core evaluation indicators such as fragment density and average potential energy attenuation coefficient, and synergistically combines them with the requirement for wide-range resolution adaptation. By precisely dividing the fusion unit, core evaluation indicators are calculated for specific areas under the target resolution. While achieving wide-range resolution adaptation from 0.05m to 1m, it ensures that the fused data directly serves the core requirement of damage assessment, avoiding data distortion caused by redundant parameter fusion, and improving the relevance and practicality of the fused data. This collaborative adaptation logic breaks through the limitations of "generalized fusion of basic parameters" in existing technologies, achieving a precise match between adaptation requirements and evaluation requirements.

[0100] According to some embodiments, the method further includes achieving a three-dimensional visualization and reconstruction of the damage effect based on the fused damage data. Based on the damage data generated after fusion in step S109, including the fragment density and average potential energy attenuation coefficient corresponding to each spatial unit, a three-dimensional geometric model of the target object is constructed, and the damage indicators are mapped to the corresponding spatial positions in the model to achieve a three-dimensional visualization and reconstruction of the damage effect. Specifically, the system divides the target area into multiple voxels or mesh units according to a preset spatial resolution, with each unit associated with its corresponding fragment density and potential energy attenuation coefficient; the damage intensity of each unit is rendered in the three-dimensional scene using color gradients, transparency, or heatmaps, thereby intuitively presenting areas of dense fragment distribution, areas with high energy attenuation, and areas with potential structural failure.

[0101] According to some embodiments, the 3D visualization reconstruction supports multi-view observation, local magnification, and dynamic playback functions, facilitating users to comprehensively understand the spatial morphology and development process of damage from different angles. By precisely aligning quantified damage indicators with the target geometry, not only is the intuitiveness and interpretability of damage assessment results improved, but also high-fidelity visualization data is provided for subsequent damage mechanism analysis, warhead effectiveness verification, and protective structure optimization. Simultaneously, this visualization model can serve as an important component of the digital twin battlefield, fused with other reconnaissance or simulation data to support higher-level operational assessment and decision-making applications.

[0102] Figure 8 shows the acquisition effect of relatively uniform flight velocity of shrapnel in a spatial resolution-adapted method for measuring the destructive power of a directional warhead according to an example embodiment.

[0103] According to some embodiments, referring to Figure 8, the measurement method further includes: constructing a three-dimensional distribution cloud map of the projectile velocity based on the data of the preceding and following sensing node pairs; summarizing the velocity data of all preceding and following sensing node pairs, classifying the velocity data in combination with the spatial orientation information of the sensing nodes to obtain the projectile velocity data under each coordinate, dividing the projectile velocity data under each coordinate into a three-dimensional grid, filling the velocity data into the three-dimensional grid, calculating the average projectile velocity of each three-dimensional grid, and constructing a three-dimensional distribution cloud map of the projectile velocity based on the average projectile velocity. Summarizing the velocity data of all valid preceding and following sensing node pairs (including the first flight velocity V1 and the second flight velocity V2). Combining the spatial orientation information of the nodes, constructing a three-dimensional velocity distribution of projectiles in different directions and at different heights. Specifically, data classification is first performed. Classification is based on the horizontal azimuth angle β (distinguishing different directions) and vertical height H of the sensing nodes. p (Distinguishing between different heights) Classify V1 and V2 to obtain each (β, H) p The velocity data of the fragment in coordinate system ) is then obtained. Next, a 3D mesh is created. The mesh is defined with the horizontal azimuth angle β as the polar angle and the vertical height H as the coordinate system. p Using the Z-axis and velocity values ​​(V1 or V2) as the third dimension, a three-dimensional mesh is created. The horizontal accuracy of the mesh is determined by twice the number of target frames, and the vertical accuracy is set according to target requirements (e.g., H). p (Each 0.05m is a grid cell). Then, the 3D grid is filled with velocity values ​​and visualized. The classified velocity data is filled into the corresponding 3D grid cells, and the average velocity of each grid cell is calculated. A velocity distribution cloud map is generated using 3D modeling tools, intuitively presenting the velocity distribution characteristics of fragments at different directions and heights, thus completing the 3D velocity distribution construction. The figure below shows the acquisition effect of relatively uniform flight velocity of the fragments in the 360° direction. This realizes the transformation from discrete sensing node data to a continuous, visualized damage field model, providing intuitive and quantitative technical support for the analysis of fragmentation field uniformity of directional warheads, identification of energy focusing areas, and comprehensive assessment of damage effectiveness.

[0104] According to some embodiments, the method further includes preprocessing the first penetration moment signal to remove first penetration moment signals with a duration less than a first time signal threshold. A signal threshold is set (circuit break duration ≥ 10 μs), and electromagnetic interference and vibration interference signals with a duration < 10 μs are removed, retaining valid first penetration signals. For first penetration moment signals with a duration less than 10 μs, they are determined to be transient noise signals caused by electromagnetic interference or mechanical vibration and are removed, retaining only valid first penetration signals that meet the duration requirement.

[0105] According to some embodiments, the calculated first and second flight velocities are filtered to remove abnormal velocity data. Further, the first flight velocity V1 (velocity before penetration) and the second flight velocity V2 (velocity after penetration) calculated based on the effective penetration signal are screened for rationality: if V2 ≥ V1, it violates the physical law that velocity inevitably decreases due to energy dissipation during the shrapnel penetration of the target plate, and this set of velocity data is determined to be abnormal or invalid and is removed. Sensing node data that does not match corresponding preceding and following nodes, and node pairs with a matching degree γ < γ0, are all determined to be invalid data and removed. Sensing node data that does not match corresponding preceding and following nodes, and data that, although forming node pairs, have a matching degree γ less than the preset matching threshold γ0, are all determined to be invalid data and removed. This processing can effectively eliminate erroneous associations caused by sensor loss of synchronization, spatial positioning deviation, or signal distortion, ensuring that the preceding and following sensing data relied upon for subsequent damage assessment have reliable consistency and physical correspondence in time and space. The aforementioned preprocessing and screening mechanisms can effectively suppress the impact of sensor noise, environmental interference, and signal mis-triggers on damage assessment, significantly improve the accuracy of penetration moment identification and the physical consistency of flight speed calculation, thereby laying a high-quality data foundation for the reliable generation of key damage indicators such as fragment density and average potential energy attenuation coefficient.

[0106] In practical testing scenarios, the initial steps involve setting up the acquisition structure and installing and deploying the hardware. Specifically, this involves assembling a single target frame. Assemble a movable target frame, securing it with two 50kg counterweights at the front. Assemble a target plate with a thickness of L=0.1m. Symmetrically lay 5cm×60cm PCB sensing nodes on both sides of the target plate, with one column on each side of the target plate, arranged vertically at 5cm intervals (bottom node Z=0), using insulating tape to attach them to a 1.2m×2.0m low-density foam board. Organize the signal output wires to the protective groove. Connect 10 sets of ADG1416 high-speed analog switches to the PCB board, one node corresponding to one channel, and then fix them to the polling module (polling switching time ≤0.05μs). Based on the requirements of the blast area (e.g., 5-meter diameter, 360° full enclosure), multiple single target frames are combined into a circular structure. Positioning is adjusted to ensure alignment of adjacent target frames, and all target frame rollers and lifting feet are fixed. The distance L from each target plate to the blast origin is set to 2.5m, and the horizontal azimuth angle β of each target plate is allocated according to the combination requirements (e.g., for 8 target frames, β would be 0°, 45°, 90°, 135°, 180°, 225°, 270°, and 315° respectively). The polling module of each target frame is connected to a portable acquisition terminal (built-in multi-channel high-speed acquisition card, 10MHz sampling rate, 16-bit resolution), and a TTL external trigger (trigger voltage 3.3V~5V) is connected to the blast trigger controller to complete power connection and pre-charging.

[0107] Subsequently, the initial penetration time signals of the sensing nodes on the double-layer PCB board before and after shrapnel penetration were collected. The acquisition terminal was activated, with a sampling rate of 10MHz and an acquisition duration of 100ms set; the directional warhead detonation was triggered, and the detonation and acquisition were synchronized via a TTL external trigger. All raw data (including P) was collected from each target. 前 P 后 The first penetration times (t1, t2) are recorded and transmitted to the terminal for aggregation.

[0108] Next, data analysis is performed. First, the coordinates of the sensing nodes are calibrated. A target plate with β=0°, L=2.5m, L=0.1m is selected, and the H of the first node (k=1) above the bottom layer is... p =0.05m, then the preceding sensing node P 前 The coordinates are (2.5×cos0°, 2.5×sin0°, 0.05) = (2.5m, 0m, 0.05m); Post-sensing node P 后 The coordinates are ((2.5+0.1)×cos0°, (2.5+0.1)×sin0°, 0.05) = (2.6m, 0m, 0.05m).

[0109] Calculation of the first incident angle: Substitute H p =0.05m, L=2.5m, we get α=arctg(0.05 / 2.5)=arctg(0.02)≈1.146°.

[0110] Calculation of the first flight distance S1 and the first flight speed V1: S1≈2.5m, if t0=0s, t1=2.5ms, then V1=1000m / s (example value, actual value should be based on test data).

[0111] The second flight distance S2 and the second flight speed V2 are calculated as follows: S2 = L / cosα ≈ 0.1m. If t2 = 2.7ms and Δt = 0.2ms, then V2 = 500m / s (example value, actual values ​​should be based on test data).

[0112] Front and rear plate sensing node matching: Select another P of the target plate with β=0° 后 (Z=0.05m), α is calculated. 后 ≈1.146°, γ1=1-|1.146°-1.146°| / 90°=1, t2-t1=0.2ms>t min , γ2=1, |z 前 -z 后 Since |=0 and γ3=1, we have γ=0.4×1+0.4×1+0.2×1=1≥0.8, which means we are considered a matching node pair.

[0113] Outlier removal and inspection: After verification, V2 < V1, no outlier data was found.

[0114] Based on this, according to the user-specified spatial resolution (e.g., any value within the range of 0.05m to 1m), the original discrete data is dynamically aggregated into several fusion units using software algorithms. Core indicators for damage assessment, such as fragment density and average potential energy attenuation coefficient, are calculated for each unit, and an error verification mechanism is introduced to ensure the fusion results are not distorted. Finally, the system maps these indicators onto a three-dimensional spatial grid, generating an intuitive and continuous cloud map of fragment velocity and damage intensity distribution, and outputting a structured damage power assessment report. This comprehensively supports the performance verification, design optimization, and operational effectiveness analysis of directed-mode warheads. The entire process is completed with fixed hardware configurations, eliminating the need for repeated adjustments to the target rack layout, significantly improving testing efficiency, data consistency, and assessment reliability.

[0115] According to some embodiments, the present invention also provides a computer program product, which includes a computer program stored in a non-transitory computer-readable storage medium. When the computer program is loaded and executed by a processor, it can implement the measurement method described in any of the preceding claims. This program can be deployed on computing platforms such as DPUs, embedded processing units, edge computing devices, or cloud servers. By calling sensor data interfaces and performing modules such as signal preprocessing, node matching, velocity calculation, fusion aggregation, and 3D visualization, it fully supports the automated processing of the entire process from raw sensing signals to highly reliable damage assessment results. By adopting the above-mentioned computer program product, the damage assessment measurement method can be run efficiently on a general computing architecture without relying on dedicated hardware, significantly reducing system deployment costs and maintenance complexity. Simultaneously, the data validity verification mechanism embedded in the program (such as penetration signal duration filtering, velocity physical law verification, node matching degree threshold judgment, etc.) ensures the reliability of the assessment input. Combined with spatial resolution-based fusion algorithms and 3D visualization reconstruction functions, it not only improves the quantitative accuracy and spatial resolution of damage indicators but also enhances the intuitiveness and interpretability of the assessment results. This program can be widely used in scenarios such as intelligent munitions effectiveness verification, range test analysis, rapid battlefield damage assessment, and digital twin simulation, providing real-time, accurate, and traceable software-level support for the "reconnaissance-control-strike-assessment" combat closed loop.

[0116] According to some embodiments, the technical solution of this invention, by symmetrically arranging double-layer PCB sensing nodes before and after the target plate and limiting them to recording only the moment of the first penetration of the shrapnel, fundamentally avoids interference caused by subsequent penetration signals, structural vibrations, or electromagnetic noise, significantly improving the signal-to-noise ratio and reliability of the original data, and laying a solid foundation for the accurate inversion of key parameters such as incident angle and flight velocity. Based on this, the system abandons the traditional generalized data processing mode and instead focuses on the core physical quantities truly relevant to damage assessment—such as the shrapnel density per unit volume and the average potential energy decay coefficient reflecting energy retention capability—allowing the analysis results to directly serve the warhead effectiveness judgment, effectively avoiding interference from redundant information in the assessment conclusions. In field tests, there is no need to readjust the hardware structure due to changes in resolution or coverage; adaptation can be completed solely through software configuration, improving deployment efficiency by more than 50%. Meanwhile, the system can flexibly handle different explosion scenarios with diameters ranging from 3 to 10 meters, and supports dynamic software adjustment of any spatial resolution within a range of 0.05 meters to 1 meter. It can be used for fine characterization of high-density fragments in the near field, as well as macroscopic assessment of large-area damage areas in the far field, comprehensively meeting the testing needs of various directional warheads. More importantly, this "fixed hardware + intelligent fusion" technical approach completely changes the previous practice of relying on multiple dedicated sensor arrays to adapt to different testing conditions, significantly reducing the costs of repeated equipment procurement, calibration, and maintenance. Practical application verification shows that overall hardware-related costs have been reduced by more than 60%. Furthermore, due to consistent hardware configuration and unified data processing logic, the results of multiple batches of tests exhibit high consistency and comparability. In summary, this invention not only improves the accuracy and specificity of damage force measurement, but also achieves significant breakthroughs in engineering practicality, deployment flexibility, and economy, providing efficient and reliable technical support for the research, verification, and optimization of directional warheads.

[0117] Figure 9 shows a block diagram of a computing device according to an example embodiment of this application.

[0118] As shown in Figure 9, the computing device 30 includes a processor 12 and a memory 14. The computing device 30 may also include a bus 22, a network interface 16, and an I / O interface 18. The processor 12, memory 14, network interface 16, and I / O interface 18 can communicate with each other via the bus 22.

[0119] Processor 12 may include one or more general-purpose CPUs (Central Processing Units), microprocessors, or application-specific integrated circuits, for executing relevant program instructions. According to some embodiments, computing device 30 may also include a high-performance display adapter (GPU) 20 for accelerating processor 12.

[0120] Memory 14 may include a machine-readable medium in the form of volatile memory, such as random access memory (RAM), read-only memory (ROM), and / or cache memory. Memory 14 is used to store one or more programs containing instructions, as well as data. Processor 12 may read the instructions stored in memory 14 to perform the methods described above according to embodiments of this application.

[0121] The computing device 30 can also communicate with one or more networks via the network interface 16. The network interface 16 may be a wireless network interface.

[0122] Bus 22 can include address bus, data bus, control bus, etc. Bus 22 provides a path for exchanging information between components.

[0123] It should be noted that, in specific implementations, the computing device 30 may also include other components necessary for normal operation. Furthermore, those skilled in the art will understand that the device described above may only include the components necessary for implementing the embodiments of this specification, and not necessarily all the components shown in the figures.

[0124] This application also provides a computer-readable storage medium having a computer program stored thereon, which, when executed by a processor, implements the steps of the above-described method. The computer-readable storage medium may include, but is not limited to, any type of disk, including floppy disks, optical disks, DVDs, CD-ROMs, microdrives, as well as magneto-optical disks, ROMs, RAMs, EPROMs, EEPROMs, DRAMs, VRAMs, flash memory devices, magnetic cards or optical cards, nanosystems (including molecular memory ICs), network storage devices, cloud storage devices, or any type of medium or device suitable for storing instructions and / or data.

[0125] This application also provides a computer program product including a non-transitory computer-readable storage medium storing a computer program operable to cause a computer to perform some or all of the steps of any of the methods described in the above method embodiments.

[0126] Those skilled in the art will clearly understand that the technical solutions of this application can be implemented using software and / or hardware. In this specification, "unit" and "module" refer to software and / or hardware capable of independently performing or cooperating with other components to perform a specific function, where the hardware may be, for example, a field-programmable gate array (FPGA), integrated circuit, etc.

[0127] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that this application is not limited to the described order of actions, as some steps may be performed in other orders or simultaneously according to this application. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to this application.

[0128] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0129] In the several embodiments provided in this application, it should be understood that the disclosed apparatus can be implemented in other ways. For example, the apparatus embodiments described above are merely illustrative; for instance, the division of units is only a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the coupling or direct coupling or communication connection shown or discussed may be through some service interface; the indirect coupling or communication connection between apparatuses or units may be electrical or other forms.

[0130] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple network units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0131] Furthermore, the functional units in the various embodiments of this application can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0132] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage device. Based on this understanding, the technical solution of this application, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a memory and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods of the various embodiments of this application.

[0133] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0134] The exemplary embodiments of this application have been specifically shown and described above. It should be understood that this application is not limited to the detailed structures, arrangements, or implementation methods described herein; rather, this application is intended to cover various modifications and equivalent arrangements contained within the spirit and scope of the appended provisions.

Claims

1. A method for measuring the destructive power of a directional warhead with spatial resolution adaptation, characterized in that, The method is used for the acquisition structure of sensing nodes deployed on a double-layer PCB board before and after a target plate. The method includes: acquiring the first penetration time signals of the sensing nodes on the double-layer PCB board before and after the shrapnel penetrates the target plate; establishing a three-dimensional coordinate system based on the explosion origin and calibrating the spatial coordinates of each sensing node; calculating the first incident angle, the first flight velocity before penetrating the target plate, and the second flight velocity after penetrating the target plate based on the penetration time and spatial position of the sensing nodes on the double-layer PCB board before and after the shrapnel penetrates the target plate; identifying the pairs of sensing nodes before and after the shrapnel belong to the same shrapnel based on the matching degree; and aggregating the pairs of sensing nodes before and after the shrapnel through a fusion algorithm based on the target spatial resolution to generate a damage assessment index that includes the shrapnel density and the average potential energy attenuation coefficient.

2. The measurement method according to claim 1, characterized in that, Also includes: Based on the data from the preceding and following sensing node pairs, a three-dimensional distribution cloud map of the projectile velocity is constructed: the velocity data of all preceding and following sensing node pairs are summarized, and the velocity data is classified in combination with the spatial orientation information of the sensing nodes to obtain the projectile velocity data under each coordinate. Based on the projectile velocity data under each coordinate, a three-dimensional mesh is divided, and the velocity data is filled into the three-dimensional mesh. The average velocity of the projectile in each three-dimensional mesh is calculated, and a three-dimensional distribution cloud map of the projectile velocity is constructed based on the average velocity of the projectile.

3. The measurement method according to claim 1, characterized in that, The double-layer PCB board is symmetrically laid on the front and back sides of the target board. It is arranged at a set interval in the vertical direction and in the horizontal direction, with a column on each side of the target board center as the reference. Each column contains multiple sensing nodes, and each sensing node only records the first penetration time.

4. The measurement method according to claim 1, characterized in that, First incident angle The calculation formula is: ,in, H is the first incident angle. p L represents the vertical height of the sensing node on the double-layer PCB board. O The distance from the front of the sensing node on the double-layer PCB board to the origin of the explosion is denoted as 'horizontal distance'.

5. The measurement method according to claim 1, characterized in that, The formula for calculating the initial velocity of the shrapnel before it penetrates the target plate is as follows: ， Where V1 is the initial velocity of the shrapnel before penetrating the target plate, and S1 is the initial distance traveled by the shrapnel before penetrating the target plate. The moment of the explosion's initiation. The moment when the front panel of the double-layer PCB sensing node is first penetrated; the formula for calculating the second flight velocity of the shrapnel after penetrating the target board is as follows: ， Where V2 is the second velocity of the shrapnel after penetrating the target plate, and S2 is the second distance the shrapnel travels after penetrating the target plate. The thickness of the target plate is given. The moment when the back panel of the sensing node of the double-layer PCB board is first penetrated.

6. The measurement method according to claim 1, characterized in that, The matching degree is defined as: γ = w1×γ1 + w2×γ2 + w3×γ3, where γ is the matching degree. The angular consistency coefficient, This is the time series rationality coefficient. The spatial location correlation coefficient, These are the weighting coefficients.

7. The measurement method according to claim 1, characterized in that, Identifying front and rear sensing node pairs belonging to the same spring clip based on matching degree includes: calculating the matching degree of each sensing node in the front and rear double-layer PCB boards; based on a preset matching degree model, performing correlation analysis on all possible combinations of front and rear board sensing nodes to identify front and rear sensing node pairs formed by continuous penetration of the same spring clip: if the matching degree of a certain front board sensing node and a certain rear board sensing node is greater than a preset matching degree threshold, it is determined to be the front and rear sensing node pair of the same spring clip penetration; if a certain front board sensing node matches multiple rear board sensing nodes, the rear board sensing node with the highest matching degree is selected as the front and rear sensing node pair of the same spring clip penetration; if a certain front board sensing node does not have a matching rear board sensing node, it is determined to be invalid data and is discarded.

8. The measurement method according to claim 1, characterized in that, Based on the target spatial resolution, the preceding and following sensing node pairs are aggregated using a fusion algorithm to generate damage assessment indices including fragment density and average potential energy attenuation coefficient. This includes: calculating the number of native sensing nodes to be aggregated based on the target resolution; dividing the data into fusion units based on the number of native sensing nodes, such that each fusion unit corresponds to a spatial region at the target resolution; and calculating the fragment density and average potential energy attenuation coefficient based on the preceding and following sensing node matching pair data within each fusion unit.

9. The measurement method according to claim 8, characterized in that, Based on the target spatial resolution, the preceding and following sensing node pairs are aggregated using a fusion algorithm to generate damage assessment indices that include fragment density and average potential energy attenuation coefficient. The method also includes: verifying the reliability of the fused data based on the calculated local fragment density and potential energy attenuation coefficient; calculating the first relative error between the fragment density of the fused unit and the fragment density of the corresponding original local region, and the second relative error between the average potential energy attenuation coefficient and the average potential energy attenuation coefficient of the corresponding original local region; if the first relative error is not greater than a first relative error threshold and the second relative error is not greater than a second relative error threshold, the fusion is deemed effective; if the first relative error and / or the second relative error exceed the threshold, the fusion is deemed to have failed, and the fusion indices need to be readjusted and recalculated until the errors meet the requirements.

10. A computing device, characterized in that, include: processor; And a memory storing a computer program that, when executed by the processor, causes the processor to perform the method as described in any one of claims 1-9.

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