CN113074591A - Double-target-surface multi-lattice acoustic precision target and warhead shock wave Mach angle testing method - Google Patents
Double-target-surface multi-lattice acoustic precision target and warhead shock wave Mach angle testing method Download PDFInfo
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- CN113074591A CN113074591A CN202110389526.3A CN202110389526A CN113074591A CN 113074591 A CN113074591 A CN 113074591A CN 202110389526 A CN202110389526 A CN 202110389526A CN 113074591 A CN113074591 A CN 113074591A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B35/00—Testing or checking of ammunition
- F42B35/02—Gauging, sorting, trimming or shortening cartridges or missiles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41J—TARGETS; TARGET RANGES; BULLET CATCHERS
- F41J5/00—Target indicating systems; Target-hit or score detecting systems
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Abstract
The invention relates to the technical field of multi-parameter measurement of a target range, in particular to a method for testing a double-target-surface multi-lattice acoustic precision target and a warhead shock wave Mach angle, which comprises a front target surface, a rear target frame, a shock wave detector array, a shock wave signal processing circuit and a data processing upper computer, wherein the front target surface and the rear target surface are vertically arranged and are mutually parallel; the shock wave detector array consists of n shock wave detection units and is used for collecting shock wave signals transmitted to each detection unit by shock waves in the process that the warhead vertically enters the target surface. The invention can solve the problem of multi-parameter measurement of the prior shooting range under the condition of ensuring high precision, simultaneously makes up the immature application of the prior bullet shock wave Mach angle measurement technology, can obtain the flight speed, the landing coordinates and the bullet shock wave Mach angle of the bullet and has high measurement precision.
Description
Technical Field
The invention relates to the technical field of target range multi-parameter measurement, in particular to a double-target-surface multi-lattice distribution acoustic precision target and a warhead shock wave Mach angle testing method.
Background
In the process of the standing target precision test of modern weapons, in order to guarantee the safety of testers and the repeatability of a measurement system, the most used method is a non-contact test technology at present. The non-contact testing technology occupies a main position in the shot coordinate detection technology at home and abroad, the testing technologies mostly measure by means of sound, light, radar, image processing and other scientific technologies, and the impact points can be positioned by utilizing respective measuring models, even a ballistic line equation is solved. Compared with a contact type test technology, the non-contact type test technology has the advantages of resource saving, low damage rate, high repeatability and the like, so that the non-contact type test method is favored in the vertical target precision test. In the vertical target precision test of the conventional ballistic weapon, compared with the technologies such as light, electricity, radar and graphic processing, the acoustic method impact point detection technology has the advantages of small environmental influence factors, good self-protection, low cost, good maneuverability, wide applicable projectile range and the like. Acoustic targets have been increasingly used in systems for measuring range ballistic parameters when firing tubular weapons, particularly small arms, in live action.
Aerodynamic studies have shown that when a projectile flies in the air at supersonic velocity, the warhead will compress the surrounding air creating a compressional wave interface, i.e., shock wave. The shock waves generated by different objects and different flight conditions are different, and the pneumatic characteristics of the flyer are reflected by the shock wave conditions. The bullet shock wave is a conical wave front formed by the supersonic bullet under strong compression on air in the flight process. The Mach angle is taken as a parameter for visually describing the conical wave front, the research of the test technology has very important influence on analyzing the motion attitude, the aerodynamic characteristics, the blocking condition and the like of the supersonic bullet in the outer ballistic flight, and has certain reference value on measuring the flying speed of the bullet and optimizing the shape design of the bullet.
At present, methods for measuring the shock wave Mach angle of a projectile mainly comprise two main types, namely a method based on shock wave capture and a measuring method based on a precision target. Shock wave capture-based methods include schlieren photography and shot tracking methods of the shock field tensor. The schlieren photography method is a shock wave tracking and capturing method based on optical imaging, and utilizes parabolic mirror reflection, knife edge imaging and high-speed camera for collection. The method can completely record the shot flight picture in the imaging range, has visual guiding significance for researching the pneumatic characteristics of shot flight, but is limited by the problems of site space requirements, light path debugging and the like, and cannot form an integrally designed measuring instrument. The shot tracking method based on the shock field tensor is not deep enough in the current research and is still in the research simulation and experimental inversion stage of a theoretical algorithm. At present, the most widely applied method at home and abroad is a precision target measuring method, and the most widely applied method is an acoustic precision target in the aspect of shock wave detection. The acoustic target captures the shock signal through piezoelectric induction mainly using a shock probe. The supersonic warhead generates disturbance superposition and forms shock waves in the process of compressing air media, the air density near the shock wave surface changes along with the disturbance superposition to cause the pressure intensity to change, and the detector detects the arrival of the shock wave surface by utilizing piezoelectric induction. Compared with other methods, the technology is mature at present.
The scheme is given in a document with the patent application number of '200610102134. X' and the name of 'shock wave target reporting system', and an upper computer and a lower computer are connected through wireless communication; the lower computer consists of a T-shaped array shock wave sensor group, a microprocessor and a wireless data transmission module; the upper computer consists of a wireless data transmission module, a computer and a display; the wireless data transmission module is connected with a computer, and the output end of the computer is connected with the display. Static and dynamic target scoring is realized. The shock wave target scoring system can only measure the shot landing coordinate parameters, is not suitable for measuring the shot shock wave Mach angle and does not make relevant discussion on the problem.
In the document with the patent application number of '201210054057.0', entitled 'full-angle incidence shock wave target-reporting device based on sensor three-dimensional arrangement', the shock wave target-reporting device comprises seven shock wave sensors which form a three-dimensional arrangement, a signal acquisition and microprocessor, a wireless data transmission module and a computer. The output ends of the seven shock wave sensors which are arranged in a three-dimensional way are connected with a signal acquisition and microprocessor, the data acquisition and microprocessor is connected with a wireless data transmission module, and the rear end of the wireless data transmission module is connected with a computer. The vertical incidence target scoring, the oblique incidence target scoring and the dynamic target scoring of the projectile are realized. The full-angle incident shock wave target reporting device can only measure the shot landing coordinate parameters, is not suitable for measuring the shot shock wave Mach angle and does not make relevant discussion on the problem.
Disclosure of Invention
In order to overcome the defects of single measurement parameter and poor test precision in the prior art, the invention provides a double-target-surface multi-lattice distribution acoustic precision target and a warhead shock wave Mach angle test method.
In order to achieve the purpose, the invention adopts the technical scheme that:
a double-target-surface multi-lattice acoustic precision target comprises a front target surface, a rear target frame, a shock wave detector array, a shock wave signal processing circuit and a data processing upper computer, wherein the front target surface and the rear target surface are vertically arranged and are mutually parallel; the shock wave detector array consists of n shock wave detection units and is used for collecting shock wave signals transmitted to each detection unit by shock waves in the process that the warhead vertically enters the target surface; the shock wave signal processing circuit comprises a charge amplifying circuit, a second-order band-pass filter circuit, a second-zero-crossing hysteresis comparison circuit, an optical coupling isolation circuit and a single-pulse trigger circuit, used for sequentially finishing the amplification, filtering, comparison and coupling of the original shock wave signal acquired by each detection unit and outputting a single pulse signal, the output signals of the n-path shock wave processing circuit are connected to different IO pins of a programmable logic device CPLD (or FPGA) device, the single pulse signal triggers the logic of a counter inside the CPLD (or FPGA) to time, and recording the time when the shock waves diffuse in the front target surface and the rear target surface and reach the n detection units, calculating the time difference when the shock waves reach different detection units, transmitting the recorded time data to a data processing upper computer, calculating the flight speed of the projectile, the landing coordinates of the projectile and the Mach angle of the shock waves of the projectile head by the data processing upper computer through software loaded in the data processing upper computer, and generating and printing a report.
Furthermore, the shock wave detector array is arranged on the rear target frame, the contact surface of the shock wave detector array is subjected to shock absorption treatment, and the rear target frame structure adopts a corresponding polygonal structure or a corresponding circular structure according to the arrangement shape of the shock wave detector array.
Furthermore, the front target surface adopts a target-free frame design, is connected with the rear target surface and is fixed with a single shock wave detector, and the formed two parallel front target surfaces and the rear target surface have a certain distance in the ballistic direction.
The invention also provides a warhead shock wave Mach angle testing method, which adopts the double-target-surface multi-lattice acoustic precision target to realize testing and comprises the following steps:
when the projectile vertically enters and passes through the front target surface and the rear target surface, signal changes are sequentially generated on the n shock wave detection units in the shock wave detector array, and the shock wave signal processing circuit calculates the time difference between the shock wave surface and different detection units, wherein the time t when the projectile vertically enters and passes through the front target surface and the rear target surface comprisesAA`The time t between the target surface and the different detection units of the target surface after the shot is emitted and the shock wave reaches the target surfaceBA、tCA、tDAEtc. (the number of time differences is equal to or greater than 3 and then the number of detection units arranged on the target surface increases);
based on the target distance between the front and rear target surfaces, the time t for the projectile to vertically enter and pass through the front and rear target surfacesAA`Calculating the average time of the shot vertically crossing the precision target according to a double-zone intercept velocity measurement method; and based on tBA、tCA、tDAPositioning and analyzing the rear target surface according to a TDOA sound delay positioning method to obtain the pellet landing coordinates and the apparent velocity of the shock wave diffusing in the target plane;
and finally, calculating the size of the shock wave Mach angle according to the aerodynamic theory and the relationship among the projectile flight speed, the shock wave diffuse apparent speed and the shock wave Mach angle.
The method is suitable for measuring the target field trajectory parameters of the supersonic projectile under vertical incidence, can solve the problem of multi-parameter measurement of the existing target field under the condition of ensuring high precision, simultaneously makes up the immature application of the existing bullet shock wave Mach angle measurement technology, can obtain the flight speed, landing coordinates and the bullet shock wave Mach angle of the bullet and has high measurement precision.
Drawings
FIG. 1 is a schematic composition of the present invention;
FIG. 2 is a schematic geometric diagram in an XYZ coordinate system of the present invention;
FIG. 3 is a schematic illustration of shock wave propagation as a projectile passes over a target;
FIG. 4 is a schematic diagram of the working principle of the present invention;
wherein: 1-shock wave detector E; 2-vertical target surface entering projectile lane line; 3-a rear target surface shock wave detector D; 4-shock wave signal processing circuit; 5-rear target surface shock wave detector A; 6-pill; 7-rear target surface shock wave detector B; 8-rear target frame; 9-rear target surface detector C.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, an embodiment of the present invention provides a dual-target multi-lattice acoustic precision target, which includes a front target surface and a rear target surface that are vertically disposed and parallel to each other, a rear target frame 8, a shock wave detector array, a shock wave signal processing circuit 4, and a data processing upper computer, wherein a shock wave detector E is disposed on a front side surface of the front target surface, and a shock wave detector array disposed in a regular polygonal or circular array is disposed on the rear target surface corresponding to the front target surface along a direction perpendicular to the front target surface; the shock wave detector array consists of n shock wave detection units and is used for collecting shock wave signals transmitted to each detection unit by shock waves in the process that the warhead vertically enters the target surface; the shock wave signal is processed by the shock wave signal processing circuit and then 5 paths of counting pulses (corresponding to the arrival time of the shock wave surface detected by 5 shock wave detectors) are output to an IO port of a programmable logic device FPGA (or CPLD), the rising edge of the counting pulses triggers a counter in the programmable logic device to work, relative time difference data is obtained after timing work is completed and sent to a computer data processing upper computer, the flying speed of the projectile, the landing coordinates of the projectile and the Mach angle of the shock wave of the projectile head are calculated according to a mathematical model, and a report is generated and printed.
The arrangement structure of the double-target-surface multi-lattice distribution acoustic precision target device is shown in fig. 2, the shock wave detector array is arranged on the rear target frame structure, specifically, at least 4 shock wave detectors are arranged on the rear target frame in total and are arranged in a regular polygon or circular shape, one shock wave detector and the shock wave detector with the single front target surface are uniformly distributed in the direction along the vertical target surface, the shock wave detector is fixed at the arrangement point of the rear target frame by adopting an angle-adjustable structure, and the outgoing line of the shock wave detector is shuttled inside the rear target frame.
Referring to fig. 2, the computer host computer first calculates the average velocity of the projectile passing through the target after receiving the relative time difference data. When the speed is measured by the double-target surface multi-lattice acoustic precision target, the fixed-distance time measurement principle of a double-area cutting device is adopted. The front target surface is used as an initial target of the speed measuring system, and the initial time is recorded by a shock wave detector E; the rear target surface is used as a cut-off target of the speed measuring system, and the cut-off time is recorded by the shock wave detector C. The speed of the projectile under vertical incidence is measured by using the zone intercept velocity measurement principle, and the flying speed is used for calculating the time of the projectile flying through the front and rear target surfaces according to the projectile signals output by the acoustic sensors of the front and rear targets
The distance between the front and rear target surfaces being
The velocity at which the projectile flies past the predetermined point is calculated as follows:
the speed can be attenuated due to the influence of resistance in the flying process of the projectile, so the measured speed is actually the speed of the projectile at a preset speed measuring point in a diagram, but the projectile can be considered to do uniform linear motion in the measuring process due to the relatively limited target distance.
Referring to FIG. 3, the projectile shock wave propagation velocity is analyzed aerodynamically in the target plane, as in FIG. 3, the target plane is the target plane as the projectile passes through the rear target planeThe in-plane shock wave is set as supersonic speed projectile flying speed
Mach angle of the shot shock wave is
Shock waves are in
Apparent velocity of propagation in a plane of
Then there is
The bullet point part is a disturbance point generated by shock waves, and the Mach angle changes along with the change of the flight speed of the projectile. According to the analysis of the aerodynamic characteristics of the shock wave, the diffusion speed of the shock wave surface of the bullet tip along the bullet path line direction is equal to the flight speed of the bullet; the diffusion speed of the shock wave in the direction vertical to the shock wave surface of the elastic tip is the ambient sound velocity; the diffusion speed of the shock wave in the front and rear target surfaces is the apparent speed.
Referring to fig. 2, the measured parameters of the rear target surface are used to calculate the measured projectile landing coordinates and apparent velocity of the shock wave propagating in the target plane. Analyzing the rear target surface multipoint acoustic positioning array: suppose the time difference of the shot shock wave reaching the shock wave detector B and the sensor A is
The time difference between the arrival at sensor C and sensor A is
The time difference between arrival at sensors D and A is
Performing location analysis on the rear target surface by using TDOA soundAnd (4) simultaneously solving by a chemical positioning method to calculate the shot impact point coordinate and the apparent speed. When more than 4 shock wave detectors are arranged on the rear target surface and are arranged in a regular polygonal or circular array, the corresponding multi-element nonlinear equation set (3) needs to be reasonably changed.
And (3) simultaneously (1), (2) and (3) calculating the Mach angle of the shot shock wave.
Referring to fig. 4, the double-target-surface multi-lattice distributed acoustic precision target device is provided with a shock wave signal processing circuit and a programmable logic device FPGA (or CPLD), wherein the shock wave signal processing circuit comprises a charge amplifying circuit, a second-order band-pass filter circuit, a second zero-crossing hysteresis comparison circuit, an optical coupling isolation circuit and a single pulse trigger circuit; the shock wave pressure sensor is connected with the charge amplifier, the shock wave pressure sensor has the characteristics of high sensitivity and quick response time, the collection of shock wave signals is completed by the shot shock wave pressure sensor and the changed charge quantity is output, the charge amplifier converts the charge into voltage, the low-input bias current precision amplifier adopted in the shock wave pressure sensor has very low bias current and very high input impedance, and the conversion coefficient of the charge amplifier is 1 mv/pC. The charge amplifier is connected with the second-order band-pass filter circuit, the pass band frequency of the second-order band-pass filter circuit is 1kHz to 20kHz, the pass band gain is about 1 time, and explosion shock waves and muzzle shock waves existing in a target range experiment can be effectively filtered. The signal is input into a secondary zero-crossing hysteresis comparison circuit after passing through a band-pass filter, the secondary zero-crossing hysteresis comparison circuit adopts a high-speed precise voltage comparator, the primary comparison level has anti-interference performance, the interference signal with lower amplitude is filtered, and the secondary comparison level is zero, so that the turnover at a 180-degree phase position is realized. And then, the signal is output to an optical coupling isolation circuit by a secondary zero-crossing hysteresis comparison circuit, the analog/digital circuit isolation is realized by using a high-speed optical coupling chip, and a +/-12V pulse signal is converted into a 0-5V TTL signal for detecting a single-pulse trigger circuit. The single-pulse trigger circuit adopts a double monostable trigger to detect the falling edge output by the optocoupler chip, and designs a pulse signal with primary output of 10ms by utilizing the double monostable trigger; the secondary input port detects the rising edge of the primary output, and the pulse width of the secondary output of 1ms is designed. The secondary trigger is not triggered any more during the output period of the primary pulse trigger, so that the function of shielding an interference signal for 10ms is realized, and ground reflected waves from shot shock waves can be effectively shielded. The signal output end of the single pulse trigger circuit is connected with an IO port of a programmable logic device FPGA (or CPLD), and the programmable logic device triggers an internal counter to time by detecting the rising edge of the single pulse signal.
Referring to fig. 4, to prevent the counter from false triggering, the FPGA first performs digital filtering processing on the received signal when receiving the signal from the single pulse triggering circuit, and mainly filters signals with too short and too long duration of single pulse. The complete monopulse signal is then detected by the state machine (first detecting the rising edge, then the falling edge). After the falling edge of the first single pulse is detected, the internal counters start counting in a unified mode, counting results are sequentially placed into the register through shifting, and the last counting value data are sent to the upper computer through the UART after passing through the parallel-serial module.
Referring to fig. 5, the programmable logic device transmits data to the upper computer after completing the timing work, and the data processing is completed by the upper computer software. The upper computer firstly detects whether the precision target equipment is accessed, and after the equipment is successfully accessed, relevant parameters are input by a tester, and then the upper computer starts to prepare for receiving data. When an abnormal value is received, the abnormal value is ignored and stays in the data reception ready state. After the data are successfully received, the data are processed through a model algorithm, namely the calculation (1) of the projectile flight speed, the solution of a multi-element nonlinear equation set (3) related to the target landing coordinate and the shock wave diffusion apparent velocity and the calculation of the projectile shock wave Mach angle are completed, and the calculation result is stored. And finally generating a report and printing.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (5)
1. The utility model provides a many dot matrixes acoustic precision targets of two target surfaces, includes perpendicular preceding target surface and back target surface, back target frame, shock wave detector array, shock wave signal processing circuit and the data processing host computer of placing and being parallel to each other, its characterized in that: a shock wave detector E is arranged on the front side surface of the front target surface, and a shock wave detector array which is arranged in a regular polygonal or circular array is arranged on the rear target surface corresponding to the front target surface along the direction vertical to the front target surface; the shock wave detector array consists of n shock wave detection units and is used for collecting shock wave signals transmitted to each detection unit by shock waves in the process that the warhead vertically enters the target surface; the shock wave signal processing circuit sequentially amplifies, filters, compares and couples the original shock wave signals collected by each detection unit and finally outputs a single pulse signal, the output signals of the n-channel shock wave processing circuit are connected to different IO pins of the CPLD device, the single pulse signal triggers the logic of a counter in the CPLD device to time, the time when the shock wave reaches the n detection units when the shock wave spreads in the front target surface and the rear target surface is recorded, the time difference when the shock wave reaches the different detection units is calculated, and the recorded time data is transmitted to the data processing upper computer.
2. The dual-target multi-lattice acoustic precision target of claim 1, wherein: the shock wave detector array is arranged on the rear target frame, the contact surface of the shock wave detector array is subjected to shock absorption treatment, and the rear target frame structure adopts a corresponding polygonal structure or a corresponding circular structure according to the arrangement shape of the shock wave detector array.
3. The dual-target multi-lattice acoustic precision target of claim 1, wherein: the front target surface adopts a design without a target frame, is connected with the rear target surface and is fixed with a single shock wave detector, and the formed two parallel front target surfaces and the rear target surface have a certain distance in the ballistic direction.
4. A warhead shock wave Mach angle testing method is characterized in that: testing is achieved with the dual-target multi-lattice acoustic precision target of any of claims 1-3.
5. The warhead shock wave mach angle testing method of claim 4, wherein: the method comprises the following steps:
when the projectile vertically enters and passes through the front target surface and the rear target surface, signal changes are sequentially generated on the n shock wave detection units in the shock wave detector array, and the shock wave signal processing circuit calculates the time difference between the shock wave surface and different detection units, wherein the time t when the projectile vertically enters and passes through the front target surface and the rear target surface comprisesAA`The time t between the target surface and the different detection units of the target surface after the shot is emitted and the shock wave reaches the target surfaceBA、tCA、tDA；
Based on the target distance between the front and rear target surfaces, the time t for the projectile to vertically enter and pass through the front and rear target surfacesAA`Calculating the average time of the shot vertically crossing the precision target according to a double-zone intercept velocity measurement method; and based on tBA、tCA、tDAPositioning and analyzing the rear target surface according to a TDOA sound delay positioning method to obtain the pellet landing coordinates and the apparent velocity of the shock wave diffusing in the target plane;
and finally, calculating the size of the shock wave Mach angle according to the aerodynamic theory and the relationship among the projectile flight speed, the shock wave diffuse apparent speed and the shock wave Mach angle.
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| CN202110389526.3A CN113074591A (en) | 2021-04-12 | 2021-04-12 | Double-target-surface multi-lattice acoustic precision target and warhead shock wave Mach angle testing method |
| ZA2021/08409A ZA202108409B (en) | 2021-04-12 | 2021-10-29 | Double-target-surface multi-lattice distributed acoustic precision target and warhead shock wave mach angle testing method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113607011A (en) * | 2021-08-17 | 2021-11-05 | 西安工业大学 | Ballistic parameter measurement system and measurement method based on acousto-optic signal triggering |
| CN115031585A (en) * | 2022-05-30 | 2022-09-09 | 南京理工大学 | Double-array acoustic vertical target oblique incidence impact point positioning method |
| CN115876041A (en) * | 2023-01-12 | 2023-03-31 | 西安工业大学 | Supersonic velocity target outer trajectory parameter measuring device and measuring method |
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2021
- 2021-04-12 CN CN202110389526.3A patent/CN113074591A/en not_active Withdrawn
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113607011A (en) * | 2021-08-17 | 2021-11-05 | 西安工业大学 | Ballistic parameter measurement system and measurement method based on acousto-optic signal triggering |
| CN115031585A (en) * | 2022-05-30 | 2022-09-09 | 南京理工大学 | Double-array acoustic vertical target oblique incidence impact point positioning method |
| CN115031585B (en) * | 2022-05-30 | 2024-04-05 | 南京理工大学 | Double-array acoustic vertical target oblique incidence impact point positioning method |
| CN115876041A (en) * | 2023-01-12 | 2023-03-31 | 西安工业大学 | Supersonic velocity target outer trajectory parameter measuring device and measuring method |
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Application publication date: 20210706 |