339results about "Ammunition testing" patented technology

The invention relates to the technical field of trajectory analysis, in particular to a trajectory aiming trajectory analysis method which comprises the following steps: acquiring wind speed time-varying data and centroid parameters, calculating wind disturbance stress and screening a maximum value, judging a rotating direction trend, executing pitch angle consistency judgment, and calculating an angle adjustment rate to generate boundary parameters. The method comprises the steps of analyzing a target speed trend to judge delay, calculating a deviation trend difference value, extracting wind disturbance sudden change to mark a high-sensitivity zone, judging that deviation coincides with the high-sensitivity zone, and generating a dynamic correction instruction set. Modeling analysis is carried out on a target delay trend by combining a direction included angle and mode difference change in a target speed trend sequence, and a trajectory correction mapping relation is constructed by combining flight parameters and timestamps, so that the adjustability and striking precision of an overall hit path are effectively improved.

The invention relates to a bending moment-torque composite loading device for testing the load capacity of a steering engine, and belongs to the technical field of ammunition weapon system testing. In the device, the pressure head, the pressurizing rod and the composite loading slip ring synchronously rotate along with the rotation of the rudder wing, so that the applied pressure can be ensured to be always perpendicular to the rudder surface and is closer to the real wind resistance working condition during flight. The bending moment output device and the torque output device are coupled together through the composite loading slip ring, so that the bending moment and the torque can be loaded at the same time and are closer to the actual flight condition.

The invention discloses a device and method for testing the cross-medium water entry of a navigation body under the wave condition, and relates to the technical field of missile body water entry testing equipment.The device for testing the cross-medium water entry of the navigation body under the wave condition comprises an experimental water tank, and a wave maker is arranged in the experimental water tank; the adjusting module comprises a launching platform capable of adjusting the inclination angle; the emission module comprises an emitter and a driving source, the emitter is arranged on the emission platform, the driving source is in butt joint with one end of the emitter, the other end of the emitter is provided with a rectification structure, and high-pressure gas provided by the driving source enables a carbon body loaded on the emitter to be released at a certain initial speed; the rectification structure is used for reducing interference generated by gas turbulence in the radial direction of the launcher when the projectile body leaves the launcher. According to the invention, a stable wave page is generated through the cooperation of the motion phases of the two wave generators, the process that a projectile body enters water under a real sea condition is simulated, and more accurate experimental data is provided for the design and optimization of a cross-medium motion body.

The invention relates to the technical field of military data processing, in particular to a light weapon live ammunition efficiency data acquisition method and system, and the method comprises the following steps: obtaining bullet center coordinates in continuous frames, calculating a motion vector, predicting the position of a hit region, extracting the overlapping information of a brightness sudden change region and the hit region, and recognizing an effective hit region. Contact point arrangement and tearing characteristics are analyzed, a structure response chain segment is generated, a mapping path is constructed according to bullet types, and a live bullet response data structure mapping set is formed. According to the method, through dynamic extraction and motion vector construction of the bullet center point in the continuous image and judgment in combination with prediction of the overlapping proportion of the hit area and the abrupt change boundary, the spatial distribution information of the hit position can be rapidly identified, the contact point group and crack characteristics can be analyzed, and accurate extraction of the geometric response of the bullet area can be realized; according to the bullet type number classification and mapping, a complete response path is formed, and the recognition efficiency, the space precision and the processing continuity of multi-dimensional data in a shooting test are effectively improved.

The invention provides a carrier rocket ground test system and method supporting visual process configuration. The system mainly comprises: (1) a visual process configuration module, which configures a test process file through a graphical interface; (2) a process analysis and scheduling module for analyzing a process file and converting the process file into a task sequence; the test execution engine module (3) is used for driving bottom hardware and executing a test instruction sequence; (4) the test resource library module is used for storing and managing various information of test elements and various information of test equipment; the execution monitoring and data management module (5) is used for displaying a test execution state in real time and recording whole-process data; according to the method, the test logic and the execution program are separated, and a user can quickly construct, modify and reuse an automatic test process in a graphical mode, so that the test flexibility is greatly improved, and the test adaptability and efficiency are remarkably improved.

The invention discloses an artificial influence weather rocket projectile three-explosion self-destruction body assembly detection system, and relates to the technical field of multivariable comprehensive measurement, and the system comprises a multi-dimensional positioning measurement module which is used for measuring the coaxiality and fitting pressure of a self-destruction body and an engine housing; the multi-parameter measuring module is filled with the medicament to measure the weight, density and internal defects of the medicament; the connection strength dynamic measurement module is used for measuring torque, tensile strength and vibration displacement; the igniter performance parameter measuring module is used for measuring resistance, time delay and safety reliability; the measurement data integration analysis module is used for integrating a data generation report and an encryption log; and the system control and exception handling module is used for coordinating module time sequences, monitoring data and handling exceptions. According to the system, multi-parameter integrated measurement of the three-explosion self-destruction body is realized, the measurement precision of positioning, medicament filling, connection strength and igniter performance is improved, the remain after self-destruction is ensured to be compliant, and the data is traceable.

The invention discloses a calculation method for reversely deducing an initial speed based on mass and position information of a fragment behind a target. The method comprises the following steps: firstly, manufacturing an after-target fragment recovery device, carrying out armor piercing test, and collecting and recording the material, quality and position information of each after-target fragment; then, typical fragments behind the target are selected, a trajectory test is conducted on the fragment recovery device, and the speed attenuation rule of the fragments behind the target when the fragments penetrate through the fragment recovery device is obtained; and finally, reversely deducing the initial speed of the fragment after target based on the obtained fragment speed attenuation rule. According to the method, the problems of stacking of the fragments behind the target, fuzzy boundary and the like during X-ray shooting are effectively solved, the initial speed of each fragment behind the target can be obtained, and data support can be provided for damage ability evaluation of secondary killing behind the target.

The invention provides a power measurement and control system and method for a liquid carrier rocket, and relates to the field. Comprising a to-be-tested real equipment system used for completing a rocket body test; the simulator is used for installing a simulation equipment system, and simulation equipment in the simulation equipment system is in one-to-one correspondence with real equipment in the real equipment system; the control machine is in communication connection with the real equipment system and / or the simulator and is used for issuing a target instruction to the real equipment system and / or the simulator in the rocket body testing process; the front-end machine is in communication connection with the control machine and the simulator and is used for forwarding first feedback information after the simulator executes the target instruction to generate the first feedback information; the monitoring machine is in communication connection with the front-end machine, the real equipment system and the simulator and is used for receiving first feedback information and / or second feedback information in the rocket body testing process and monitoring the first feedback information and / or the second feedback information; the second feedback information is feedback information generated after the real equipment system executes the target instruction.

The invention discloses a missile-borne integrated navigation method and a missile-borne integrated navigation device for adaptive switching and sequential updating. The method comprises the following steps: acquiring angular velocity data and specific force data of an IMU (Inertial Measurement Unit), and performing inertial navigation state prediction based on the angular velocity data and the specific force data to obtain a prediction error state vector and a prediction error covariance matrix at the current moment; based on the prediction error state vector and the prediction error covariance matrix, navigation mode adaptive discrimination is carried out, a navigation mode discrimination result at the current moment is obtained, and first measurement information is determined based on the discrimination result; performing sequential measurement updating based on the first measurement information to obtain a posterior error state vector and a posterior error covariance matrix at the current moment; and performing error compensation correction based on the posterior error state vector and the posterior error covariance matrix to obtain navigation information. According to the invention, the technical problems of navigation interruption of a high-dynamic missile-borne platform in a GPS denial environment and large calculated amount and poor robustness of traditional fusion filtering are solved.

The invention relates to a rocket sled aerodynamic characteristic evaluation method based on a meteorological environment multi-factor coupling effect, and solves the problem of deviation between a simulation evaluation result and an actual test result due to the fact that factors are not effectively combined in an existing evaluation technology. The method comprises the following steps: step 1, acquiring multi-dimensional meteorological data; 2, adjusting the air density; step 3, adjusting a viscosity coefficient; 4, determining the mass fraction of water vapor in the air; and 5, establishing a wet air material. 6, the relative running speed of the rocket sled and the air is determined; 7, solving the steady state of the aerodynamic characteristics of the whole trajectory of the rocket sled; and 8, verifying and correcting the model. The method has the advantages that the aerodynamic characteristics of the rocket sled can be accurately reproduced; two factors, namely air density and dynamic viscosity coefficient, which have great influence on the aerodynamic characteristics of the rocket sled are comprehensively considered; a wet air material model is established, and compared with a previous dry air model, the evaluation precision is higher.

The application discloses an embedded over-the-horizon anti-armor simulation terminal, which comprises a visual display and control device, a direction-finding and angle-measuring device, a laser receiving device and an effect simulation device.The visual display and control device is used for simulating a video of a camera on a shell to realize flight control of the simulated shell; the direction-finding and angle-measuring device is used for obtaining the position, orientation and inclination angle of the shell; the laser receiving device is used for receiving laser information to simulate the situation that the equipment is hit; the effect simulation device is used for generating sound, light and smoke effects when the terminal is launched or damaged; the main control machine is used for data interaction with the visual display and control device, the direction-finding and angle-measuring device, a data acquisition terminal, the laser receiving device and the effect simulation device, and provides a positioning function; the data acquisition terminal is used for data interaction with the main control machine, collecting data of striking events, hitting events, position states, damage states and remaining shell quantity of the embedded over-the-horizon anti-armor simulation terminal, and realizing display, storage and query of the data.The application realizes simulation of over-the-horizon striking operation and data acquisition in a field environment.

The present application relates to trajectory analysis technical field, specifically to a kind of ballistic sighting trajectory analysis method, comprising the following steps, obtain wind speed time-varying data and centroid parameter, calculate wind disturbance stress and screen maximum value, determine the trend of rotation direction, execute pitch angle consistency judgment, calculate angle adjustment rate and generate boundary parameter, analyze target speed trend and determine delay, calculate deviation trend difference, extract wind disturbance mutation mark high sensitive section, judge offset and high sensitive section overlap, generate dynamic correction instruction group, in the present application, wind speed time-varying data is refined to different structural section of projectile body, and wind disturbance stress intensity is calculated by combining respective surface stress, target delay trend is modeled and analyzed by combining direction angle and modulus difference change in target speed trend sequence, trajectory correction amount mapping relationship is constructed by combining flight parameter and time stamp, and the adjustability and strike accuracy of overall hit path are effectively improved.

The application discloses a launching projectile support for irregular projectile body self-defined rolling angle and an assembling method thereof, which comprises a support body, the support body comprising an upper shell, a lower shell, positioning columns and a lever rod, the upper shell and the lower shell being coaxially and threadedly connected at the ends, a cavity with a closed end and an open end being formed between the upper shell and the lower shell, a projectile body being arranged in the middle of the cavity, the positioning columns filling the remaining space of the cavity and supporting the projectile body, the lever rod comprising a lifting rod, a flat plate lever and a supporting column, the flat plate lever being horizontally arranged on the end face of the lower shell, the lifting rod being arranged in the upper shell along the axial direction, one end of the lifting rod being in contact with one end of the flat plate lever, and the supporting column being arranged in the lower shell along the axial direction, one end of the supporting column being in contact with the other end of the flat plate lever. The application can well position various irregular projectile bodies, thereby meeting the demand for various specifications of projectile bodies in experiments, and the application is convenient for experiments, saves manpower and material resources, and guarantees the accuracy of experimental results and the effectiveness of data.

- Method and device for determining and using a diagnostic tool comprising a temperature aging spectrum. - The method (P) comprises a step (E1) for receiving at least one temperature curve relating to a given geographical location, a processing step (E2) comprising a series of successive substeps (E2A, E2B, E2C, E2D, E2E), implemented iteratively for different values ​​of a characteristic time associated with a type of material, comprising a substep (E2A) for filtering the temperature curve using a first-order filter having said characteristic time as its time constant, a substep (E2B) for applying an aging law, a substep (E2C) for performing an accumulation over a given sliding period, a substep (E2D) for extracting a value corresponding to an aging criterion, and a substep (E2E) for associating this extracted value with the characteristic time.The pairs of values ​​obtained at the end of the iterations allow the formation of a temperature aging spectrum, and a step (E3) to perform comparisons, at least from this spectrum, to carry out a diagnosis. Figure for the abstract: Fig. 4.

This application proposes a small-scale universal modal testing device for rockets, comprising a suspension mechanism for suspending the rocket body and a testing mechanism with an impact end, wherein the impact end can impact the rocket body around a first axis. It also includes a drive mechanism for driving the impact end to impact the rocket body, and a testing platform for mounting the suspension mechanism and the testing mechanism. In use, the impact end is rotated around the rocket body with the first axis as the center and stopped at a suitable position. At this point, the drive mechanism drives the impact end to impact the rocket body. Compared to existing technologies that only include four impact points (left, right, top, and bottom), the impact end that can surround the rocket body has more impact positions, allowing for more flexible adjustment and facilitating the simulation of multi-position impact tests.

A method for calibrating artillery shells is proposed. During metalworking of the body of an artillery shell (1), grooves (2) with appropriate geometric dimensions are cut on the lateral surface or end surface (4) of the body. The shells (1) are placed on a balancing stand, where the value and angular coordinates of their existing unbalance are determined. The unbalance vector is corrected either on the lateral surface of the projectile body (1) or on the end surface (4) by one of two methods: either by installing balancing weights (5) in pre-punched grooves (2) or by drilling or milling balancing holes (6). After completing the correction of the unbalance vector, the artillery shells (1) are calibrated with respect to their mass by weights and corresponding markings on the body of each shell (1).The stabilization of the ballistic properties of artillery shells and the resulting increase in firing accuracy lead to a reduction in standardized consumption.

The application discloses a kind of melt-cast explosive solidification forming monitoring device and method, device includes temperature control oven, the temperature control oven includes the temperature control oven main body being provided with mounting cavity, and the box door being provided at the front end of the temperature control oven main body, rotating base is provided in the mounting cavity, multiple charging sites are spaced apart and arranged on the rotating base, an explosive body mold is provided on each charging site, and the top end of the explosive body mold is connected with a riser hopper;Vacuum tube and injection tube are provided on the top plate of the temperature control oven main body, and the bottom of the injection tube is provided with injection port;X-ray detector, infrared thermal imager and multiple temperature acquisition devices are further provided in the temperature control oven main body.The device realizes the coupling of charging, solidification nursing and process monitoring, multiple charging sites can be independent of each other, can also be combined with each other, effectively improves the monitoring efficiency, and can provide dynamic parameters for process optimization.

The utility model discloses a simulation test device of an initial velocity measuring device. The simulation test device comprises a main control module, a muzzle flame simulation module and a projectile initial velocity simulation module. A main control module; the system comprises a microprocessor unit MCU, a power supply management unit, a light-emitting tube LED driving unit and a communication interface unit. The MCU comprises a memory and an input unit, the memory stores an operation instruction for the light-emitting tube driving unit, and the MCU initializes the light-emitting tube LED driving unit and the communication interface unit after being powered on; the MCU controls an output signal of the LED driving unit according to the parameter setting of the input unit; the muzzle flame simulation module comprises at least one first light-emitting tube LED display screen; the projectile initial velocity simulation module comprises a plurality of second luminous tube LED display screens; and the display screen receives an output signal of the light-emitting tube LED driving unit and generates a predetermined light-emitting pattern. The simulation test device provided by the utility model is used for performance test during debugging, manufacturing and acceptance in the development process of ammunition training guarantee monitoring equipment.

The invention relates to the technical field of ammunition cook-off tests, and particularly discloses a rapid cook-off test device and method.The device comprises a supporting frame, an oil pool, a lifting appliance, a thermocouple, a speed measuring target, a verification plate, a pressure sensor, a video recording device, a temperature recorder and the like. The oil pool is arranged below the supporting frame, the hanger hangs the test bomb above the oil pool, the thermocouple surrounds the test bomb, the speed measuring target and the verification plate are arranged in front of and behind the test bomb respectively, and the pressure sensor is arranged on the side face. The method comprises the steps of inspection before test, equipment installation, verification plate arrangement, sensor installation, equipment debugging, test bomb fixing, water injection and oil injection, remote ignition, observation and recording, field investigation, photographing and recording, unreacted test bomb destroying and the like. The rapid cook-off environment can be accurately simulated, the temperature change of the test bomb can be comprehensively monitored, key parameters can be comprehensively and accurately measured, reliable data can be provided for test bomb performance evaluation, and the test is safe and reliable.

The application is an array type electrostatic sensor, a projectile velocity measuring device and method based on the sensor. The array type electrostatic sensor is in the shape of a tube coaxially arranged behind the projectile outlet and the barrel or bore body, and a plurality of circumferentially arrayed graphite electrodes in a pleated triangle structure are arranged at the upstream and downstream cross sections along the axis of the tube. The measuring device comprises an induction unit, a signal conditioning unit and an analysis and calculation unit, obtains the electrostatic induction signal component belonging to the projectile, then according to the velocity range of different projectile models, selects the electrostatic induction signals of the electrodes at different positions in different cross sections to reconstruct the charge distribution and establish the cross correlation sensitivity matrix, and further based on the correlation focusing principle of the electrodes at different cross sections, proposes a data fusion algorithm of multiple sensor electrodes, and finally measures the muzzle projectile velocity. The application proposes to use electrostatic field sensing measurement as a new means for projectile testing in view of the complex environment of high temperature and high pressure at the muzzle.

The invention belongs to a method for testing the rotating speed of a flying projectile in the field of non-sitting force guns, which comprises the following steps of: photographing and capturing the flying projectile by using a high-speed camera at a specified station on one side of a ballistic trajectory, recording the starting time and the ending time by using marks on the surface of the projectile, and calculating the average rotating speed of the projectile at a certain point when the projectile flies; the system is composed of an emplacement (1), a flying projectile (3) and a high-speed camera (2). According to the method, after an artillery on a gun position (1) shoots ammunition, a flying projectile (3) appears on a trajectory trajectory, a high-speed camera (2) shoots the movement condition of the projectile in a view field and stores the movement condition, and then the time when a marking line is located on the axis of a projectile shaft after the projectile enters the view field and before the projectile leaves the view field is checked and recorded as T0 and T1 respectively, according to the time interval from T0 to T1 of the projectile, the number of turns of the projectile rotating in the interval can be read, and according to the number of turns of the projectile rotating and the time, the flight rotating speed of the projectile can be obtained through calculation.

The invention relates to a method and a device for determining and using a diagnostic tool comprising a temperature ageing spectrum, the method (P) comprising a step (E1) of receiving at least one temperature curve relating to a given geographical location, a processing step (E2) comprising a sequence of consecutive substeps (E2A, E2B, E2C, E2D, E2E), implemented iteratively for different values of a characteristic time associated with a type of material, comprising a substep (E2A) of filtering the temperature curve using a first-order filter having the characteristic time as the time constant, a substep (E2B) of applying an ageing law, a substep (E2C) of performing a cumulative calculation over a given sliding time period, a substep (E2D) of extracting a value corresponding to an ageing criterion and a substep (E2E) of associating this extracted value with the characteristic time, wherein the pairs of values obtained at the end of the iterations form a temperature ageing spectrum, and a step (E3) of performing, from at least this spectrum, comparisons in order to carry out a diagnosis.

The application discloses a weather modification rocket bomb three-explosion self-destruction body assembly detection system, and relates to the technical field of multivariate comprehensive measurement. The system comprises a multidimensional positioning measurement module, which is used for measuring the coaxiality and fitting pressure of the self-destruction body and the engine shell; a medicament loading multi-parameter measurement module, which is used for measuring the weight, density and internal defects of the medicament; a connection strength dynamic measurement module, which is used for measuring the torque, tensile strength and vibration displacement; an igniter performance parameter measurement module, which is used for measuring the resistance, delay and safety reliability; a measurement data integration analysis module, which is used for integrating data to generate a report and an encrypted log; and a system control and abnormality processing module, which is used for coordinating the module time sequence, monitoring data and processing abnormalities. The system realizes integrated measurement of multiple parameters of the three-explosion self-destruction body, improves the positioning, medicament loading, connection strength and igniter performance measurement accuracy, guarantees that the wreckage is in compliance after self-destruction, and data is traceable.

The application discloses a comprehensive electronic equipment detonator impedance detection compensation method, and aims at solving the technical problems that the existing comprehensive electronic equipment does not have a detonator impedance detection function, and the impedance detection precision is poor, the expected performance cannot be reached, and the detection difficulty is great. The application improves the detonator impedance test precision and the automation level, and realizes the engineering application of the detonator impedance detection function on the comprehensive electronic equipment. The method can also be popularized and applied to other occasions needing to detect the detonator impedance, and has certain guiding significance for engineering practice.

The application provides a high-velocity gun zero-flying error detection method, device, equipment and storage medium, and relates to the technical field of weapon equipment test error correction. The method comprises the following steps: acquiring a target image collected by a camera fixed on a high-velocity gun barrel during a zero-flying test in an ideal environment as a reference image; acquiring a muzzle blast intensity, optical visibility, illumination mutation rate, camera posture data and an actual image collected by the camera during an actual zero-flying test of the high-velocity gun; performing error prediction on the reference image according to the muzzle blast intensity, optical visibility, illumination mutation rate and camera posture data, and obtaining a prediction error of the actual image relative to the reference image; performing error correction on the actual image according to the prediction error, and performing zero-flying error detection according to the corrected actual image. The application can realize accurate detection of zero-flying errors in different zero-flying test environments and improve environmental adaptability.

The application provides a stage separation test system, a force-thermal environment identification level test method and a device.The test method comprises the following steps: arranging a stage separation push rod on a vibration test table, performing vibration test on the stage separation push rod by using the stage separation working condition in rocket flight, and checking whether the stage separation push rod can meet the mechanical environment in the rocket flight process; when the mechanical environment in the rocket flight process is met, continuously heating the stage separation push rod to a first preset temperature and keeping the first preset temperature for a first preset time; verifying whether the stage separation push rod meets the stage separation standard at the first preset temperature; continuously cooling the stage separation push rod to a second preset temperature and keeping the second preset temperature for a second preset time; and verifying again whether the stage separation push rod meets the stage separation standard at the first preset temperature. The embodiment of the application can completely simulate the force and thermal environment on the rocket, and can complete the stage separation test under the condition of simulating the force and thermal environment on the rocket.

There are described methods and system for determining a similarity or distance measure between a first ballistic specimen and a second ballistic specimen. The method comprises acquiring topographic data from the first ballistic specimen and the second ballistic specimen of at least one region of interest; computing from the topographic data at least one similarity score s for the first ballistic specimen and the second ballistic specimen; determining a non-match probability measure of the similarity score for at least one parameter characterizing a macroscopic and / or microscopic feature of the topographic data, the non-match probability measure associating the first ballistic specimen and the second ballistic specimen to a different source; and correcting the similarity score by determining a corrected similarity score that yields a same value of the non-match probability measure as the similarity score for a reference value of the at least one parameter.

The invention discloses a liquid oxygen rock breaking shock wave front edge form testing device which comprises a test bed, a cartridge bag fixing seat is fixedly connected to the middle of the test bed, a test cartridge bag is placed on the cartridge bag fixing seat, a first closed box body is fixedly connected to one side of the test bed, and a second closed box body is symmetrically and fixedly connected to the other side of the test bed. Optical guide rails are arranged in the first closed box body and the second closed box body, the optical guide rail in the first closed box body is in sliding connection with a first optical element arranged along an optical path, and the optical guide rail in the second closed box body is in sliding connection with a second optical element; a high-speed camera is arranged at the end, away from the medicine bag fixing base, in the second closed box. The invention further discloses a liquid oxygen rock breaking shock wave front edge form testing method. According to the testing device and the testing method disclosed by the invention, the problems that the physical and chemical change mechanism of the existing liquid oxygen expansion rock breaking is not clear and the comparative research on the aspects of the rock breaking effect and the dynamic response characteristic compared with the traditional explosive blasting is relatively deficient are solved.

The invention discloses a power device, an aircraft and a test system, the power device comprises a phase change power unit, an excitation device, a pressure relief device, a pipeline and spray pipes arranged in pairs, the power device is installed on the aircraft, the test system comprises a test device and a power device, the test device comprises a rack, a bearing, a bearing seat and the power device, and the power device is installed on the rack. Two ends of the power device are rotatably mounted on the frame through a bearing and a bearing seat, the phase change medium is liquid CO2 with certain pressure, and the liquid CO2 can be safely stored in an environment of-50 DEG C to 70 DEG C. When the power device is started, a liquid CO2 medium in the phase change chamber absorbs heat to be subjected to phase change and expansion boosting, and when the pressure reaches a pressure threshold value of the pressure relief device, high-pressure CO2 gas is released to the primary containing chamber and forms a stable and uniform high-pressure gas source after being subjected to pressure reduction and pressure equalization through the primary containing chamber, and meanwhile the high-pressure gas source is released outwards from the symmetrically-arranged spray pipes; thrust generated by gas injection enables the aircraft to rotate at a high speed.

The ammunition passing device comprises a base, an upper cover and a separated counter, two surrounding plates are vertically arranged at the front end and the rear end of the base in parallel, a first boss and a second boss are arranged on the portions, located on the upper surface of the base, of the inner sides of the surrounding plates at the front end and the rear end, and an ammunition belt channel is formed between the first boss and the second boss. The width of the ammunition belt channel is consistent with the length of a standard ammunition belt, when the ammunition belt of ammunition to be counted passes through the ammunition belt channel, the head and the tail of the ammunition pass through the upper surfaces of the first boss and the second boss respectively, the ammunition belt passes through the portion between the ammunition belt channels, an upper cover is detachably and horizontally arranged on the upper surfaces of the two surrounding plates, and a separated counter is arranged on the upper cover. According to the utility model, whether the ammunition meets the installation standard can be detected, so that the unqualified ammunition is prevented from entering the subsequent use link, and the safety and reliability of the ammunition are ensured.