1137results about "Ammunition testing" patented technology

A process for manufacturing an ammunition article, including: (a) providing a cartridge including a projectile disposed in a casing and presenting a joint between the projectile and the casing; (b) applying to the joint a sealingly effective amount of a light-curable sealant composition; and (c) exposing the applied sealant composition to curingly effective light. The resulting ammunition article is sealed at the projectile / casing joint against moisture incursion, and such article is amenable to high-speed, high-volume production by the method of the invention.

Imprinting an identification indicia on a cartridge in a difficult context, such as on a coated cartridge or on a high power cartridge. A marking indicia is formed on a base surface located in the interior surface of a cartridge chamber containing the cartridge and includes marking lands raised with respect to the base surface and a maximum marking indicia elevation above the base surface that is coplanar with the interior surface. The marking indicia is thereby recessed with respect to the interior surface and the identification indicia is thereby recessed with respect to the imprint surface.

In accordance with the invention, there is a decision support method comprising collecting data about a set of components of an asset, wherein the data comprises information about the status of each component in the set of components. The method also comprises comparing the data to a set of requirements for a use of the asset and estimating a remaining life for each of the components in the set of components based on the status of each of the components and the set of requirements for an intended use of the asset.

Systematic use of infrared imaging characterizes marks made on items and identifies the particular marking tool with better accuracy than use of visual imaging. Infrared imaging performed in total darkness eliminates shadows, glint, and other lighting variations and artifacts associated with visible imaging. Although normally used to obtain temperature measurements, details in IR imagery result from emissivity variations as well as thermal variations. Disturbing an item's surface texture creates an emissivity difference producing local changes in the infrared image. Identification is most accurate when IR images of unknown marks are compared to IR images of marks made by known tools. However, infrared analysis offers improvements even when only visual reference images are available. Comparing simultaneous infrared and visual images of an unknown item, such as bullet or shell casing, can detect illumination-induced artifacts in the visual image prior to searching the visual database, thereby reducing potential erroneous matches. Computer numerically controlled positioning of the toolmark relative to imaging sensors which use fixed focus optics with shallow depth of focus, varying focus distance and orientation systematically to construct a sequence of images, maximizes reliability of resulting images and their comparisons.

The present invention includes a device for determining the force necessary for the separation of a bullet from an ammunition cartridge comprising a chamber housing having central bore extending from a lower housing end to an upper housing end and terminating at a upper aperture, wherein the central bore comprises a chamber diameter adapted to accept an ammunition cartridge and that the bullet partially extends from the upper aperture; a frustaconical shape shoulder in the central bore at the upper housing end to reduce the chamber diameter to mate to an ammunition cartridge shoulder; a neck that connects the upper aperture to the frustaconical shape shoulder adapted to accept an ammunition cartridge neck; a cartridge retention lip within the upper aperture adapted to contact an ammunition cartridge bullet aperture; a chamber mount adapted to connect the chamber housing and a testing device; a bullet securing device comprising a bullet securing end to secure the bullet and a bullet securing device mount adapted to connect to the testing device; a moving mechanism to move the bullet securing device away from the chamber housing; a sensor in communication with the moving mechanism to measure a force exerted by the moving mechanism; and a display in communication with the sensor to display and or record the force.

The invention relates to an ammunition overload detection device, and in particular relates to an overload test and detection device of a gas gun, wherein the device provided by the invention can be used for solving the technical problems such as inconvenience in operation and use and the like of the existing air gun penetration test device. The overload test and detection device of the gas gun comprises a frame body which is provided with an overload test air gun launching device, a charging overload test bomb, an overload test protective box and an overload test target plate replacement device. Comprehensively, compared with the prior art, in the technical scheme provided by the invention, the target plate replacement device for an overload test, the overload test protective box and a small-size penetration test bomb are designed specially for the small-size charging and priming system air gun overload performance test, principles and methods relevant to the mechanical design are utilized, the design scheme has the characteristics of being vigorous, practicable, convenient and the like, and the overload test and detection device has the advantages of favorable practical value, reliable operability and accurate experiment result.

The invention relates to a method for measuring space attitude of an aircraft or a missile body, in particular to an attitude estimation method based on magnetic survey roll angle rate information for a high-speed rotary missile. According to the attitude estimation method, a three-axis geomagnetic sensor, a two-axis gyroscope and a satellite receiver are adopted to form a missile-borne attitude sensing system, a fast attitude estimation method with the assistance of magnetic survey for the rotary missile is adopted, and therefore the rapid aerial on-line acquisition of the missile body attitude under the unknown initial parameter can be realized; a fast attitude estimation algorithm for the rotary missile uses the missile speed information which is measured and obtained by the satellite receiver to estimate the yaw angle attitude and the pitch angle attitude of the missile body, and the yaw angle attitude and the pitch angle attitude of the missile body are used as observation information of the fast estimation algorithm; and by means of the fast attitude estimation method for the rotary missile, attitude estimation of the missile body can be completed, and meanwhile, on-line estimation and compensation of the error parameters of the missile-borne three-axis geomagnetic sensor and the two-axis gyroscope sensor can be realized. The attitude estimation method has the advantages that the design is reasonable, the flying attitude of the rotary missile can be quickly estimated online, and the good popularization and application values can be achieved.

The invention relates to a system for testing isolation of a guide head, which is used for testing the isolation of the guide head of a laser terminal guided projectile and comprises a signal simulation part, a motion simulation part and a testing main control part, wherein the signal simulation part comprises a laser target simulator, a two-dimensional swing mirror and a reflection screen and is used for generating laser capable of being received by the guide head; the motion simulation part comprises a three-axis turntable capable of loading the guide head and is used for simulating the posture motion of a projectile body; the testing main control part is used for controlling a turntable body to simulate the posture motion of the projectile body according to a predetermined mathematical model, and receiving test data returned from the guide head, so that isolation performance analysis is carried out, wherein laser generated by the laser target simulator is projected on the reflection screen through the two-dimensional swing mirror; furthermore, the guide head receives laser reflected by the reflection screen. Because laser is prevented from being directly projected on the guide head, accurate and effective experimental data about the isolation test of the guide head can be obtained by operators; simultaneously, a real weapon system campaign mode can be well simulated.

The invention discloses a movement simulation system for infrared targets, which relates to the technical field of semi-physical simulation devices and comprises a control system, a target simulator (1), a movement device and a positioning fixture. The target simulator (1) provides different target energy for a seeker at the front end of a guidance cabin (3), the movement device drives the target simulator to move independently or in a compound manner on a horizontal plane and a pitching plane, and the positioning fixture supports the guidance cabin. The control system comprises an industrial personal computer and a movement control system, wherein the industrial personal computer is used for completing human-computer interaction and transmitting processed control signals to the movement control system, and the movement control system is used for receiving the control signals transmitted by the upper computer, further processing the control signals and then transmitting the control signals to an execution unit. The simulation system is particularly implemented by various simulation devices and can be reused, the simulation equipment has universality and is convenient in use and maintenance, and test cost is far lower than the cost of physical experiment.

The invention discloses a light screen device with sending and receiving functions and a test method of the light screen. A light source and a receiving light device are installed on a circuit board to form a detection device main body with sending and receiving functions, and the light is reflected by an illuminator to form a detection screen. The detection device and the reflecting device are both provided with angle regulatory mechanisms with the same structure, the angle regulatory mechanism can adjust the angle of an incidence screen and a reflecting screen to ensure the angle between two screens by cooperating with the light screen. The main light axis of the light-emitting device is ensured to be at the same plane with the main light axis of the receiving device. The light screen device has the advantages of simple structure, fewer links, small cumulative error, high measurement precision, and convenient assembling; the light screen device not only can be used for measuring the speed of a pellet, but also used for carrying out the denseness degree test and the measurement of pellet flying angle and direction; and the light screen device broadens the measurement scope of the pellet.

The invention discloses a system for evaluating the disturbance rejection rate parasitical loop of a strap down infrared seeker. The system comprises a target simulator, a three-axis rotary table, the seeker and an emulation computer, wherein the target simulator simulates the movement relation of a target; the strap down infrared seeker detects the infrared signal source of the target simulator, and outputs a missile-target LOS (Line of Sight) rate obtained after decoupling filtering to the emulation computer, the emulation computer calculates the attitude and position information of a missile according to a practical kinetic model of the missile and transmits the attitude angle of a missile body to the three-axis rotary table to simulate the movement of the missile body; the emulation computer figures out a theoretical missile-target LOS rate and transmits the theoretical missile-target LOS rate to the target simulator to simulate the movement of the missile-target to form an entire closed-loop testing system. In the whole process, the emulation computer stores test data for final disturbance rejection rate calculation. The system eliminates the problem of singular point in the traditional disturbance rejection rate testing method, and enables that the disturbance rejection rate test is more accurate and a testing system is closer to the practical combat mode of the missile.

The invention provides a guided missile ground comprehensive test device and method based on a wireless network, and relates to the field of guided missile ground tests. The problems that full-automatic tests cannot be achieved through an existing guided missile test system and the test system is large in size, poor in portability, complex in test process, low in efficiency and the like are solved. The device is composed of a remote ground monitoring device and a ground automatic test device, wherein the two devices can be in communication through radios, and the communication distance can reach several kilometers. The remote ground monitoring device is used for sending a test instruction to the ground automatic test device and receiving test process data fed back by the ground automatic test device, and is used for data storage. The ground automatic test device automatically completes communication tests, self-inspection tests and the like according to the test instruction sent by the remote ground monitoring device. Compared with a traditional guided missile ground test system, the device has the beneficial effects of being small in size, small in weight, simple in test process, high in efficiency, short in guided missile test and launch time interval, safe to use, and the like.

Systematic use of infrared imaging characterizes marks made on items and identifies the particular marking tool with better accuracy than use of visual imaging. Infrared imaging performed in total darkness eliminates shadows, glint, and other lighting variations and artifacts associated with visible imaging. Although normally used to obtain temperature measurements, details in IR imagery result from emissivity variations as well as thermal variations. Disturbing an item's surface texture creates an emissivity difference producing local changes in the infrared image. Identification is most accurate when IR images of unknown marks are compared to IR images of marks made by known tools. However, infrared analysis offers improvements even when only visual reference images are available. Comparing simultaneous infrared and visual images of an unknown item, such as bullet or shell casing, can detect illumination-induced artifacts in the visual image prior to searching the visual database, thereby reducing potential erroneous matches.

An assembly for determining speed of a supercavitating underwater vehicle during underwater travel includes a fin mounted on the vehicle aft of a cavitator portion of the vehicle and adapted to be extended outwardly beyond a hull of the vehicle and through a boundary of a gas-filled cavity around the vehicle to form a disturbance in the cavity boundary, which disturbance propagates along the boundary. An acoustic transmitter is mounted on the vehicle and directs acoustic energy toward the boundary and the disturbance. An acoustic receiver is mounted on the vehicle and receives acoustic energy reflected off the disturbance. An autopilot is mounted on the vehicle and clocks times of projection of the fin and acoustic transmission receptions of reflected acoustic energy to determine the speed of the vehicle through the water.

Various implementations are disclosed for self-contained, non-intrusive data collection in ammunition. In some implementations, a gun is loaded with a non-explosive, non-firing round of ammunition containing a data acquisition system. Such a data-collecting round of ammunition may be loaded into the gun according to the same procedures as live rounds of ammunition, and, in particular, may be loaded into a firing position immediately after a preceding live round has been fired. In this way, the data-collecting round of ammunition is able to experience temperature or other conditions that are experienced essentially identically by live rounds. After collecting related data while in the firing position, the data-collecting round may be removed from the gun, for analysis of the data for, for example, development of hot gun misfire safety procedures.

An indicia for marking on an object, such as a cartridge case, for representing selected information, such as identification indicia identifying the firearm that discharged the cartridge, and methods and apparatus for generating, imprinting and reading the identification indicia. An indicia includes a multi-dimensional array of encoded marks, including encoded marks determined by spectral encoding variables representing the selected information wherein each spectral variable is spectrally distinguishable from others of the spectral variables representing variables, and an encoded pattern of the encoded marks is determined by algorithmic transformation of the selected information. An indicia may also include hologram related artwork. An indicia may be an encoded hologram multi-dimensional barcode, an encoded hologram or an encoded concentric circular barcode and may be formed of a single indicia or as an array of indicia.

Disclosed is tagged ammunition, methods for making it, using it and detecting it to reduce gun violence. When implemented together with a smart phone coupled readers, standalone readers, or at a security center, software is included to allow integration of signals detected by multiple readers in the vicinity to map detectable ammunition detected by readers designed to detect tagged ammunition as a proxy for loaded firearms. This makes possible securing an area of interest, when combined with placing of at least one networkable reader in the vicinity of the area of interest; and connecting the one or more readers to a monitoring center. Such monitoring centers may be associated with schools, shopping malls, streets, public meetings, public events, housing complexes, an area being swept for loaded guns, an area being monitored for gang activity, or even a residence.

The present invention is directed to identifying ammunition. In one embodiment, an identifiable ammunition cartridge includes a bullet having a first identification surface, a casing having a second identification surface, and an identifying code positioned on at least one of the first and the second identification surfaces. In another embodiment, a method for identifying ammunition includes selecting a first code portion and a second code portion, and combining the first code portion with the second code portion to form an identifier that may be applied to the ammunition. In still another embodiment, a method for tracking ammunition having an identifier includes storing the identifier and a corresponding identity of a first custodian in a data storage system, transferring the ammunition to a second custodian, associating the ammunition identifier with an identity of the second custodian, and storing the identity corresponding to the second custodian in the data storage system.

The invention discloses a propellant powder variable capacity burning rate testing device, belonging to the explosive property test field. The technical characteristics include that a pressure sensor is respectively arranged on the wall of a combustion chamber and a piston, the piston and a piston cavity are in slide fit, a piston rod fixedly connected with the piston is used for leading the connecting wire of the sensor in the piston to the outside of the piston cavity, and ignition cartridge bag and propellant powder to be tested are placed in the combustion chamber; when in test, the propellant powder to be tested is burned in the combustion chamber and the piston is pushed to move, the two pressure sensors respectively record pressure curves of combustion chamber fixed position and piston bottom, namely curve p1-t and curve p2-t, and a high speed camera record piston rod moving stroke-time curve, namely L-t curve; and computing and processing are carried out by virtue of a data acquisition and processing system, thus finally obtaining the burning rate pressure coefficient and burning rate pressure index of propellant powder to be tested. The invention not only solves the problem of measuring propellant powder variable capacity burning rate but also solves the technical problem that cartridge bottom pressure measurement is simulated.

The invention relates to a technique for measuring an initial attitude of a high-speed rotating projectile body at a muzzle, in particular to a method for measuring the initial attitude of the high-speed rotating projectile body at the muzzle based on a three-axis micro electro mechanical system (MEMS) accelerator and two nonorthogonal distributed MEMS gyroscopes to solve the problem of accurately measuring the high-speed rotating projectile body with high axial overload and high angular speed. The method for measuring the initial attitude of the high-speed rotating projectile body at the muzzle comprises the following steps: (I) establishing a cannon emission coordinate system as a reference coordinate system, setting an emission point of the projectile body in a barrel as an original point of the reference coordinate system, and arranging the barrel in an XnOYn plane of the reference coordinate system; establishing a projectile body coordinate system, setting a projectile body core as an original point of the projectile body coordinate system, and enabling an axis to be along the axial direction of the projectile body; and in the whole process of emitting the projectile body to the muzzle, ensuring that the yaw angle of the projectile body is zero and the pitch angle is not changed. The design is reasonable, and the measurement problem that the range and the accuracy are conflicted when the axis angular rate of the projectile body is measured is solved through the two high-precision small-range gyroscopes.

The invention relates to an intiative reclaim control method of the air to air missile experiment missile. The method is added with an intiative reclaim control module and a built-in ballute in the inner of the missile, when the experiment occurs with fault or completes the flying test, the intiative reclaim control module is automatically started. The Control missile adopts the high dropping trajectory to reach the set deceleratatoin attitude-adjusting, then gives the parachute opening control signals, opens the deceleratatoin drag-parachute, completes the ntiative reclaim of the missile reclaim. After the missile reclaim control technology is adopted, the test personnel on the ground obtains the precious software working state and the flying test data in the flying, which realizes the effective utilization of the flying test missile. The technology advances the failure analysis and the zero adjustment work, which is of evident importance to accelerate the development speed of the missile.

An explosive blast overpressure space-time field reconstruction method adopts an overpressure sensor array in a blast test system to acquire blast signals, and utilizes a blast overpressure space-time field reconstruction module to reconstruct an explosive blast overpressure space-time field; during reconstruction, a tested area is first meshed, sensor array elements are arranged, an explosion point is then located, a blast velocity field and a blast peak overpressure field are reconstructed, and thereby therefore a blast peak overpressure field reconstruction result is obtained; in combination with the blast peak overpressure field reconstruction result of the point, each parameter of a 'modified Friedlander equation' is solved, so that blast overpressure space-time data are obtained; finally, the reconstructed data are converted into an image file, and thereby therefore the blast overpressure space-time field is visualized. The method provides a basis for the evaluation of the damage effectiveness of blast and the structure and performance of explosive; and meanwhile, the method also is an important means for evaluating the safety of personnel, the shock resistance of equipment and the affection of blast on the surrounding environment.

The invention relates to a controllable infrared photoelectric detection target device. The controllable infrared photoelectric detection target device comprises a round bottom seat and a target housing which is fixed on the round bottom seat, wherein a laser emission unit, an energy collection unit, a control circuit unit and a signal trigger unit are arranged in the target housing. Additionally, the controllable infrared photoelectric detection target device further comprises a horizontal adjustment unit. According to the controllable infrared photoelectric detection target device, a double high power infrared emission laser device is used to form a fan-shaped detection light curtain, the detection light curtain is controlled by using an external triggering mode, measurement of speed and position coordinates of all-weather large target area pellets of a field trajectory can be achieved, and simultaneously energy consumption is reduced, and work efficiency of equipment is improved.

A firearm comprising a gun barrel for accommodating a desired round of ammunition having a bullet, a shell casing and a primer. The gun barrel has a firing pin associated with a chamber of the gun barrel and the firing pin is activated by a trigger assembly. When the firing pin is activated by the trigger assembly, a striking surface of the firing pin strikes the primer and discharges the round of ammunition to propel the bullet out of the opposite end of the gun barrel. The firing pin, the interior surface of the barrel, or some other surface which contacts the shell casing carries a unique identifying indicia. Upon discharge of the round of ammunition, the component of the firearm carrying the unique identifying indicia transfers an impression of the unique identifying indicia to an exterior surface of the shell casing to identify that the shell casing was discharged by that firearm.

A lightweight ballistic armor system comprising at least one metal strike face plate, a laminate composite backing material secured to the at least one metal strike face plate and an optional air space provided between the metal strike face plate and the laminate composite backing material. The metal strike face plate or plates has a predetermined defined thickness and has a plurality of slotted holes set at an angle relative to the vertical orientation or axis of the metal strike face plate, or which are straight. The plurality of slotted holes is sufficiently small to prevent the passage of a projectile or fragment therethrough. The laminate composite backing material comprises at least one material selected from an aramid fiber material, S-glass, E-glass, polypropylene and UHMWPE, and is provided in combination with a polymer-based resin material. The optional air space provided between the metal strike face plate and the composite backing material has a depth in the range between 0-12 inches.

The invention discloses a method and a device for realizing measurement of a flying speed and a landing coordinate of a projectile of a double-tube volley weapon for outdoor target lanes. The method comprises the following steps that: eight test light curtain arrays are arranged along a trajectory direction; when the projectile flies through the light curtain arrays, a detecting device generates corresponding electric signals so that eight paths of data acquisition devices acquire curtain-passing signals accurately, and transmit the signals to an upper computer through wireless digital transmission equipment; and the upper computer recognizes the flying projectile through a speed and landing coordinate calculation algorithm, stores and displays the flying speed of the projectile and the position coordinate on the surface of the target. The method is simple in theory and easy to realize. The measurement device provided by the invention comprises the detecting device, the data acquisition devices, the wireless digital transmission equipment, the upper computer, a memory and a display; and the detecting device consists of two four-light-curtain detecting devices. The device has a simple structure and low cost, and can realize quick and precise measurement of trajectory parameters of double-tube or single-tube volley weapons under the large-scattering condition of the trajectory at the end point.