181results about "Ammunition testing" patented technology

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 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 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 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.

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 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 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.

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.

The application discloses a vertical test platform for rockets and a use method thereof, and belongs to the technical field of rocket body assembly, which comprises support columns, a plurality of support columns are vertically arranged at the positions of four peripheral edges, horizontal platform modules are arranged between the plurality of support columns, a plurality of platform modules are arranged in up-down positions, the platform modules slide on the support columns in the vertical direction of the support columns, working through holes suitable for rocket bodies are formed in the platform modules and are arranged at the middle positions of the platform modules, the platform modules are arranged in a central symmetry mode, the platform modules comprise sliding base plates and sliding plates, the sliding base plates are slidably connected with the support columns, and the sliding plates slide on the sliding base plates in the horizontal direction of the sliding base plates to approach or move away from the support columns. The application has the effect of adjusting height, expands the applicable range of general assembly, parking and testing of rockets with high height, and improves the working efficiency of workers.

The application provides a digital intelligent transportation carrier rocket test method and test system, belonging to the field of carrier rocket test technology. The method constructs a test architecture coordinated by the cloud, test backend and test front end. The cloud is responsible for overall management of test data, operation of digital twin model and artificial intelligence analysis service. The test backend is responsible for coordination of on-site test tasks, real-time data processing and instruction issuance. The test front end connects the tested carrier rocket through a universal interface module and deploys digital and intelligent equivalent modules. The system adopts a three-layer architecture of perception layer, service layer and application layer, integrates a high-fidelity digital twin model to realize a virtual-real combined test closed loop, realizes unified access of multi-source heterogeneous test data through a data bus, and supports heterogeneous adaptive testing of solid, liquid and reusable carrier rockets. The application realizes digital control and intelligent decision support of the carrier rocket test process, and improves test efficiency and reliability.

The invention relates to an on-line self-adaptive health detection system and method for initiating explosive devices of an agile aircraft, and belongs to the technical field of on-line detection of spaceflight electronic systems. Comprising a constant current source, an integrated computing power center, a reusable detection link and an ignition loop, wherein the integrated computing power center comprises a sequential logic control algorithm module and a data estimation module; the reusable detection link comprises an analog switch 1, an isolation optocoupler, a multi-choice analog switch, a voltage following module, an isolation operational amplifier module, a differential operational amplifier module and an AD acquisition module; the ignition loop comprises an initiating explosive device to be detected; according to the invention, the problems of poor precision, complex hardware, low test efficiency and the like of a traditional single-path voltage measurement method are solved, and the test coverage, safety and application reliability of the agile aircraft are improved.

This application discloses a gun-launched test projectile, comprising: a first housing having symmetrically arranged first and second slotted structures; an antenna disposed within the first and second slotted structures for receiving satellite signals; a projectile-borne receiver circuit box disposed within the first housing and connected to the antenna for determining the current position of the test projectile based on the satellite signals; a buffer structure connected to the projectile-borne receiver circuit box for reducing the overload effect on the projectile-borne receiver circuit box during launch; and a base assembly disposed at one end of the first housing, having an abutment portion and a connecting portion, the abutment portion abutting against the projectile-borne receiver circuit box, the connecting portion connecting to the first housing, and a cavity structure between the abutment portion and the connecting portion. This application also discloses a test projectile recovery device and method.

The application provides an underwater explosion shock wave testing device, which comprises a sealed shell and two-way pressure sensors, two-way signal conditioning circuits integrated on a circuit board, a data acquisition and storage module, a communication module and a power module sealed in the shell, wherein: the two-way pressure sensors realize sensing of underwater explosion shock waves and convert the underwater explosion shock waves into electrical signals input to the signal conditioning circuits; the two-way signal conditioning circuits realize adjustment of the sensor output signals and conversion into differential signals; the data acquisition and storage module samples the conditioned shock wave signals, converts the shock wave signals into digital signals and stores the digital signals in real time; the communication module realizes communication and data transmission between the testing device and an upper computer, and the upper computer filters, extracts and analyzes and processes underwater explosion shock wave data; and the power module supplies power for operation of the testing device. The application can more accurately complete measurement and save data, calculate and analyze underwater explosion power, and has a good application prospect.

This invention provides a method for obtaining terminal ballistic parameters by combining ballistic shock wave and explosion wave data. This method solves the technical problem that existing acoustic measurement methods can only obtain the location and time of the explosion, but not the projectile velocity and trajectory direction, thus hindering accurate assessment of projectile performance. The method comprises the following steps: N acoustic measurement points (N≥2) are set up around a predetermined explosion point; the acoustic measurement points sequentially acquire the arrival direction and time of the ballistic shock wave, and the arrival direction and time of the explosion wave; the explosion point location and explosion time are obtained from the acquired explosion wave arrival direction and time; and the trajectory direction and projectile velocity are calculated from the acquired ballistic shock wave arrival direction, time, and explosion point location. This invention enables the acquisition of terminal ballistic parameters such as explosion point location, explosion time, projectile velocity, and trajectory direction, providing crucial data support for accurate projectile performance assessment.

The application discloses a floating device for underwater experiment of an aircraft, which comprises a shell, a connecting plug arranged at the bottom of the shell and connected with a projectile body of a launcher, a core body installed in the shell, a top cover arranged at the top of the shell, a locking device arranged between the core body and the bottom of the shell, a spring release assembly connecting the core body and the shell, an electronic control system installed in the core body, an antenna arranged in the core body, and a communication quick plug arranged in the cavity of the core body. The shell bottom quick connector obtains the data in the projectile body, the shell is internally provided with the core body for obtaining the data in the projectile body through the communication quick connector and internal cable, and the core body realizes autonomous floating through the cooperation of the locking device and the spring release assembly. Only the core body needs to be salvaged, and the problems of difficult positioning and salvaging of the projectile body and difficult recovery of the projectile body data in the underwater experiment of the aircraft are solved.

The invention discloses a test supporting system suitable for multi-point excitation air cannon impact, which comprises a bottom plate, an annular resonance steel plate and a side plate, the annular resonance steel plate is arranged at the upper end of the bottom plate in parallel through a plurality of upright posts, the side plate is connected with the outer sides of two adjacent upright posts, and the plurality of upright posts are uniformly distributed along the circumference of the resonance steel plate. The test supporting system suitable for multi-point excitation air cannon impact adopts a spliced design, is convenient to disassemble and transport, meets the test requirements of test pieces with different sizes, can save the test cost, can adapt to a multi-air cannon impact test stand, and can meet the conditions of non-uniform magnitude distribution and the like during the impact test of high-magnitude and large-size test pieces; and the plurality of vertical columns are uniformly distributed along the periphery of the resonance steel plate, so that the boundary of the resonance steel plate is fixed, the installation is more stable and firmer, and the test risk is reduced.

The invention relates to an experimental device and method for preventing a quadratic type cloud explosive bomb from fire channeling. The device comprises a cloud explosive bomb main body which is a hollow pipe containing central initiating explosive and cloud explosive fuel, an upper end opening is detachable, and a plurality of notch grooves are distributed in the inner side wall of the cloud explosive bomb main body. The central tube is filled with the porous material, the inert explosion suppression dust is uniformly dispersed in pores of the porous material, and explosion flame propagation of the central initiating explosive is inhibited under the combined action of the porous physical structure and the chemical explosion suppressant, so that the fire channeling phenomenon is prevented. The center initiating explosive is tightly connected with the detonator, and the detonator is fixed through a center initiating detonator plug. And the ignition delay system is used for controlling the initiation time sequence of the central primer detonator and the secondary primer detonator. The method can prevent the fire channeling phenomenon of the cloud explosive bomb, so that the damage power of the cloud explosive bomb is improved, and the method has the advantages of being simple in process, easy to operate, low in cost and suitable for batch production.

A case sorter for sorting ammunition cases includes a housing with a case inlet for receiving a feed tube of stacked cases, a first exit for expelling acceptable cases, and a second exit for expelling unacceptable cases. The housing supports a stepper assembly and a slider assembly. The stepper assembly drives the slider assembly, which in turn carries individual cases from the case inlet to a measurement position where the height and diameter of each case is measured with corresponding measurement systems. Depending on their height and diameter measurements, each case is then sorted by a sort program stored on an integrated controller. Each acceptable case is carried by the slider assembly to the first exit, and each unacceptable case is carried by the slider assembly to the second exit. The first exit optionally includes a sensor for detecting when cases have filled a cooperating exit tube.

The application provides a kind of deep penetration test three-dimensional trajectory test method, after the reduction trajectory of foaming material, the coordinates of each point on the deep penetration trajectory are accurately obtained by image processing method;It should be noted that the foaming material prepared by the present application has certain strength and toughness after solidification, even if it is subjected to impact and wear of concrete block / stone block during target sectioning, the structure will not be damaged, and the three-dimensional model of the trajectory formed by the foaming material can ensure the integrity of the trajectory track after being taken out, the model can keep the original crater morphology and three-dimensional state of the trajectory;As can be seen, the trajectory reduction technology of the present application solves the contradiction between target sectioning randomness and retaining the integrity of the trajectory line, greatly reduces the difficulty of target sectioning, and has the advantages of saving labor and time cost, simple and efficient.

The comparator of the present invention allows the competitive shooting handloader to take a number of empty cases, or empty cases with un-spent primers, measure them and sort them in such a way that each case can be segregated and uniformity of sorted cartridges can be achieved. The comparator can also be variably adjustable to measure the depth of primer pockets, the length of primers, the thickness of cartridge rims, and the overall length of bullets.