116 results about "Projectile" patented technology

Disclosed are embodiments for determining the position and speed of a projectile in three-dimensional world coordinates using a single camera and radar. In some embodiments, a method comprises: determining a zero radial speed time of the projectile based on radar measurements of the projectile; determining a radial speed of the projectile at a particular time based on the radar measurements; determining a radial speed slope at the particular time based on the radial speed measurements; determining a two-dimensional image point of the projectile at the particular time; determining a depth scale coefficient at the particular time based on the zero radial speed time, the radial speed, the radial speed slope, the image point, and a homographic transformation; and determining a position of the projectile in space at the particular time based on a three-dimensional position of the camera, the depth scale coefficient, the image point and the homographic transformation.

A projectile includes a shell defining a cavity and one or more retainers. A bolo is disposed within the cavity and a backplate is engaged with the one or more retainers. The backplate is configured to separate from the shell to release the bolo in response to imbalanced forces resulting from deploying the projectile.

This invention discloses a method and apparatus for simulating the motion of a projectile landslide. The method includes: acquiring rock mass parameters of the projectile rock mass; calculating the initial state parameters of the projectile rock mass during the landslide; analyzing the flight process of the projectile rock mass in the air using an aerodynamic analysis model based on the rock mass parameters and the initial state parameters to determine the state parameters of the projectile rock mass before impact with the ground; and analyzing the motion process of the projectile rock mass after impact and after impact using a discrete element method (DEM) model based on the state parameters before impact with the ground to obtain the final shape of the projectile rock mass. This embodiment, by simultaneously utilizing both an aerodynamic analysis model and a DEM model, can more realistically simulate the motion process of a projectile landslide.

The invention provides a method for measuring the dynamic hardness of a material based on bullet impact indentation. The method comprises the following steps: carrying out decontamination and polishing treatment on the surface of a target material; measuring the elastic modulus of the to-be-measured area; the hard spherical projectile is launched to impact the to-be-measured area to form an impact pit, and the springback speed of the projectile is measured in situ; measuring geometric parameters of the impact pit; establishing a contact force model of the elastic unloading section impacted by the projectile; and with the springback speed and the geometric parameters of the pit as input, obtaining the maximum loading force through a contact force model, and finally calculating the dynamic hardness. The dynamic Myer hardness is calculated by measuring the bullet rebound speed and pit parameters through the bullet impact indentation test without depending on real-time data acquisition of a high-frequency force / displacement sensor, so that the problem of strain rate upper limit caused by hardware limitation in the traditional technology is solved, and the blank of dynamic Myer hardness measurement under the high strain rate is filled up.

An electric circuit breaker device includes: an igniter provided to a housing; a projectile disposed in an accommodating space formed in the housing, the projectile being to be projected along the accommodating space by energy received from the igniter; a conductor piece that is provided to the housing, forms a portion of an electric circuit, includes in a portion thereof a cutoff portion to be cut off by the projectile, and is disposed with the cutoff portion crossing the accommodating space; an arc-extinguishing region positioned on a side opposite to the projectile prior to actuation of the igniter with the cutoff portion interposed between the arc-extinguishing region and the projectile, and configured to receive the cutoff portion cut off by the projectile; a first coolant material disposed in the arc-extinguishing region; and a second coolant material disposed between the projectile and the cutoff portion in the accommodating space prior to actuation of the igniter.

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.

Target device (100) for firing with long or short firearms, comprising at least one upright target (110) capable of withstanding firing with conventional hunting or sporting projectiles, characterized in that two targets (110, 120) are provided in pairs, which are coupled via a respective coupling device (111, 121) to a common rotatably mounted shaft (130), and the kinetic energy absorbed upon impact of a projectile on a first target (110) causes the first target (110) to be moved from a vertical position to a horizontal position by means of a rotation of the shaft (130) and simultaneously causes the second target (120) to be moved from a horizontal position to a vertical position by means of a rotation of the shaft (130).

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.

According to one aspect of the present disclosure, a computer-implemented method for determining a configuration of a projectile launching device is provided, wherein the method comprises receiving first data from a passive sensor; determining a first location of a detected object based on the first data; determining a second location based on the first location; and determining a configuration of the projectile launching device to fire a projectile such that it collides with the detected object at the second location.

The invention belongs to the technical field of deep underground target penetration, and particularly relates to an energy gathering / kinetic energy series penetration structural body which comprises a charging shell, the front end of the charging shell is provided with an opening, a shaped charge liner is arranged at the opening of the front end of the charging shell in an adhesive mode, the rear end of the charging shell is fixedly connected with a rear-stage connecting part, and the rear-stage connecting part is fixedly connected with the charging shell. The rear end of the rear-stage connecting part is connected with a rear-stage main projectile body, a charging buffer layer is arranged at the front end of an inner cavity of the rear-stage main projectile body, a rear-stage fuze is installed at the rear end of the rear-stage main projectile body, and the charging shell and the rear-stage main projectile body are both filled with gunpowder. Wide-speed-range penetration is achieved through the series connection structure, the rear-stage connecting part extends into the charging shell to be in threaded connection with the charging shell, the rear-stage connecting part is protected against damage by utilizing three-direction pressure stress generated by explosive detonation, meanwhile, the length of the rear-stage connecting part can be adjusted, the rear-stage connecting part is used for protecting a penetration projectile body structure under the condition of different penetration target-hitting speeds, and the penetration target-hitting speed is improved. And therefore, the purpose of increasing the penetration power is achieved.

A device (1) is provided for measuring imbalance of a projectile (10), comprising a support (2) defining a main axis (2a) and a main plane (2b) orthogonal to the main axis (2b), and including a cavity (20) suitable for housing a projectile (10) centred with respect to the main axis (2a), a tubular body (21 ) bounding the cavity (20) radially to the main axis (2a) so as to surround the projectile (10), a base (22) bounding the cavity (20) parallel to the main plane (2b) so as to face the bottom of the projectile (10); movement means (3) configured to move the projectile (10) in the cavity (20) rotating about the main axis (2a); and measurement means (4) configured to measure at least one vibration of the support (2) in the main plane (2b) and / or parallel to the main axis (2a) with respect to a fixed structure, such as a floor or a frame integral with the floor; and one or more compressed air circuits (5) distributed between the body (21 ) and the base (22), configured respectively to apply at least a second pneumatic force (F2) on the projectile along the main axis (2a), defining a second air bearing (5b) between the projectile (10) and the base (22) to allow the projectile (10) to float in air with respect to the base (22), and to alternatively or simultaneously apply at least a first pneumatic force (F1) normal to the main axis (2a) and / or tangential to the projectile (10) parallel to the main plane (2b), defining at least a first air bearing (5a) around the projectile (10), and apply at least a third pneumatic force (F3) tangential to the projectile (10), realizing at least part of the movement means (3).

The utility model relates to a rescue throwing deceleration projectile body, which comprises a projectile body, a projectile head, a wing seat, a slow descent assembly and a propulsion power assembly, the projectile head, the projectile body and the wing seat are sequentially arranged from left to right, a material cavity is arranged in the projectile body, and a plurality of flying wing surfaces are arranged on the peripheral surface of the wing seat. The propelling power assembly is located in the wing seat and used for providing driving force for flight of the projectile body, the slow descending assembly comprises a plurality of buffering fan blades, extension plates are formed on the back faces of the buffering fan blades, the ends of the extension plates are hinged to the flight wing face, and the slow descending assembly is opened when the projectile body lands. And in the falling process of the projectile body, the multiple buffering fan blades can be opened, the wind resistance of the projectile body is increased, the falling speed of the projectile body is reduced, and the probability of material damage is greatly reduced.

The application discloses a light-weight split type centering structure suitable for a sub-caliber dynamic accelerating device and belongs to the technical field of special launching. The application comprises a front centering part, a rear centering part and an adjusting mechanism; the front centering part is composed of a plurality of annular supports with the same structure according to the length of a projectile body and is sequentially sleeved on the projectile body; the rear centering part is connected with the sleeve through a center blind hole; the bottom surface of the center blind hole of the rear centering part abuts against the tail end surface of the projectile body; the adjusting mechanism is composed of a long screw rod and a plurality of nuts; the position of the annular support of the front centering part is adjusted by adjusting the screwing position; the application reduces the proportion of useless projectile support mass in the launching mass; under the condition of the same launching propellant amount, the projectile body obtains a higher speed, and the design index of reducing the launching mass is realized.

A device for determining a firing position from which a projectile has been fired at a target object is proposed, comprising:at least one sensor unit for detecting an impact of the projectile in the target object,at least one acoustic sensor unit for detecting a muzzle blast when the projectile is fired, anda determination unit which is arranged to determine the firing position on the basis of the detected muzzle blast and the detected impact.

The invention relates to a hollow-point projectile with a one-piece construction, comprising a cylindrical section (1) and an ogive section (2), the projectile tip (3) being located at the end of the ogive section (2) opposite the cylindrical section (1), wherein the ogive section (2) is divided into at least two segments (4.1, 4.2, 4.3, 4.4) and has a channel (7) which has a muzzle (6) in the region of the projectile tip (3). The cylindrical section (1) and the ogive section (2) have a completely closed outer surface.

The application provides a supercavitation projectile cross-medium water entry interference suppression method based on optimization of a cymbal length, comprising the following steps: S1, establishing a projectile-cymbal parameterized model, and demarcating an optimization interval of the cymbal length; S2, coupling a multiphase flow model, a cavitation model and a dynamic grid method to simulate a separation process of the projectile and the cymbal, and obtaining original data of the projectile; S3, performing comparative simulation of multiple groups of different cymbal lengths, and quantitatively extracting three key performance indexes of a supercavity symmetry, a pitch angle deviation and a speed attenuation rate by using the original data of the projectile; and S4, establishing a multi-target optimization criterion based on an interference index, determining a globally optimal cymbal length parameter, and completing the whole optimization process. The application can solve the problem caused by improper design of the cymbal length when the supercavitation projectile and the cymbal cooperatively enter water.

The invention discloses a perforation explosion pressure field calculation method considering a perforating bullet charging structure, and relates to the technical field of perforation well completion, and the method comprises the steps: collecting perforating bullet parameters, wellbore parameters, perforating pipe string parameters and environmental parameters; dividing the shaft annulus into a plurality of shaft annulus nodes; a plurality of charging nodes are divided in the perforating bullet charging area; calculating an initial detonation pressure field of charge explosion of the perforating bullet; and calculating the explosion pressure at each shaft annulus node to obtain a perforation explosion pressure field. The method is used for solving the problems that in the prior art, an accurate quantitative relation between charging structure parameters and an explosion pressure field distribution rule is lacked, and an existing calculation method is insufficient in precision and poor in engineering applicability. The purposes of accurately calculating the perforation explosion pressure field distribution under different charging structure conditions and improving the safety of perforation well completion operation and the predictability of the perforation effect are achieved.

The invention discloses a self-powered emitter structure for emission of an electromagnetic reconnection gun, relates to the technical field of electromagnetic emission, and aims to solve the problems that a solid / winding type emitter of an existing reconnection gun is prone to uneven eddy current, weak in through-flow, insufficient in thrust, speed and emission efficiency and limited in emission range, and a novel self-powered emitter structure is provided. Comprising a battery module, a rectifying circuit module, an energy storage transmitting circuit module, a high-voltage direct-current voltage limiting circuit module, an acquisition module, a control module and a metal shell, the control module is electrically connected with the acquisition module, the battery module, the rectifying circuit module, the energy storage transmitting circuit module and the high-voltage direct-current voltage limiting circuit module respectively to form an integrated circuit module; controllable high shooting speed, high shooting efficiency, ultra-long range and continuous shooting can be better achieved, the structure is simple and more compact, and safety is good.

The invention relates to the weapons industry, in particular to firearms. The firearm comprises a barrel (1) with a muzzle cut (2) and is provided with an external jet engine (9) configured to generate a jet of gases (10) coaxial with the barrel axis beyond the muzzle cut (2) in the direction of firing. The invention also concerns a projectile (6) for a firearm, comprising a cavity (18) containing a flowable substance (19) and one or more channels (20) communicating with the cavity (18) and having outlet openings (22) on an outer surface of the projectile (6). The cavity (18) is provided with a piston (23) capable of rectilinear movement and adapted to receive the impact of gases of the propellant charge (5). According to the invention, the projectile (6) has two alternative configurations. In the first configuration, a surface of the cavity (18) has one or a plurality of spiral -shaped protrusions (24) made along the axis of rotation of the projectile (6) and adapted to interact with the piston (23). In the second configuration, the piston (23) is made as a stepped piston consisting of several cylindrical surfaces of different diameters corresponding to the cylindrical surfaces of the cavity (18).

According to one aspect of the present disclosure, there is provided a computer-implemented method of determining a configuration of a projectile launching device, the method includes receiving first data from a passive sensor; determining a first location of a detected object based on the first data; determining a second location based on the first location; and determining a configuration of the projectile launching device to propel a projectile to collide with the detected object in the second location.

The application discloses a speed measuring device and a measuring method for measuring the speed of a projectile, which comprises a speed measuring device and an optical measuring unit; the speed measuring device comprises a cavity, and a measuring area is arranged in the cavity and used for measuring the speed of the projectile passing through the cavity; the optical measuring unit is used for adjusting a measuring light path, measuring the position information of the projectile in the cavity detection area at different moments, processing the position information data, and obtaining the speed of the projectile passing through the speed measuring device.

The application discloses a soft recovery test method and system for a strong impact test projectile body and a test projectile, and belongs to the field of strong impact test testing; the method is characterized in that: first, a high-speed camera is arranged on the side of the muzzle of a simulated artillery strong impact test device, and the lens of the high-speed camera is directed to the muzzle; an ultra-wide-angle camera is arranged on the rear side of the simulated artillery strong impact test device, and the lens of the ultra-wide-angle camera is directed to the front of the simulated artillery strong impact test device; then, the speed of the test projectile out of the muzzle and the real-time state and posture of the test projectile in the recovery process are acquired; finally, the damage reason and position of the tested sample are judged; the damage reason and position of the tested sample are obtained, that is, the damage is caused by the bore overload or the landing collision. The application solves the problems that, when the test projectile is subjected to strong impact overload test by a simulated artillery or a gas gun, the test projectile lacks a key state detection means and safe and reliable recovery judgment basis.

This invention provides a three-dimensional numerical simulation method and system for high-speed inclined water ejection of a supercavitating projectile. The method includes: establishing a three-dimensional geometric model of the projectile and the flow field computational domain, and outputting the projectile's property parameters; estimating the size of the projectile's motion region, meshing the projectile and flow field computational domains, importing the meshes into fluid dynamics software, establishing an overlapping computational domain, and setting the projectile's property parameters and the fluid dynamics solver's boundary conditions; considering the influence of water compressibility on the high-speed projectile, using a user-defined function to establish the nonlinear relationship between density and pressure of a compressible liquid under isothermal conditions; defining the initial motion parameters of the projectile, performing numerical solutions, and obtaining the cavitation evolution, flow field distribution, force and motion characteristics of the high-speed inclined projectile during water ejection. This invention can simulate the high-speed inclined water ejection process of a projectile under different operating conditions, effectively reducing costs and providing a technical basis for submarine-launched tests.

This invention belongs to the field of energy extraction equipment technology, and relates to a storable shot perforation fracturing device and method, including a tubing, a perforation fracturing tool string, a casing, and a cement sheath; the lower end of the tubing is connected to the upper end of the perforation fracturing tool string, which is installed in a cylindrical casing. A cement sheath is fitted on the outside of the casing, and the cement sheath is formed in the rock containing an oil and gas reservoir. The storable shot perforation fracturing device uses compressible gas for perforation fracturing; the device accelerates the shot through pressure differential and a long acceleration tube, increasing the jet destructive force, and the shot penetration can form a deeper perforation; during the fracturing process, pulse-induced low temperature and turbulence are used, which can increase the apparent viscosity of the fluid and reduce the proppant holding effect under the filtration pressure differential, thereby helping to solve the proppant carrying problem.

Magazine (1) of a cannon with several containers (3) for each receiving a cartridge (15), wherein the containers (3) are connected to each other by a connecting means (2), wherein at least one container (3) has a support tray (4) and at least one retaining flap (5.1, 5.2), wherein the retaining flap (5.1, 5.2) is pivotably held on the support tray (4), wherein the retaining flap (5.1, 5.2) is pivotable back and forth between a release (6) and a holding position (7), wherein the retaining flap (5.1, 5.2) has a cartridge case area (8) and an axially spaced projectile head area (10), wherein in the holding position (7) a radial distance between the cartridge case area (8) and an opposite base of the support tray (4) is greater than a radial distance between the projectile head area (10) and the opposite base of the support tray (4), wherein in the holding position (7) between the Sleeve area (8) of the retaining flap (5.1, 5.2) and a first area (16) of the cartridge (15), wherein in the holding position (7) a second bearing surface is formed between the projectile head area (10) of the retaining flap (5.1, 5.2) and a second area (17) of the cartridge (15), wherein the retaining flap (5.1, 5.2) has a transition area (12) which is formed between the case area (8) and the projectile head area (10), wherein in the holding position (7) a third bearing surface is formed between the transition area (12) of the retaining flap (5.1, 5.2) and a transition area of ​​the cartridge (18), characterized in that a sum of the bearing surfaces of the at least one retaining flap (5.1, 5.2) is at least 35% of the surface area of ​​the cartridge (15), wherein the support shell (4) is cylindrical segment-shaped with an opening angle of less than 180°, wherein two retaining flaps (5.1, 5.2) are arranged symmetrically on the support tray (4), wherein the pivot axes of the two retaining flaps (5.1, 5.2) run parallel to a cartridge axis.

This invention discloses a portable impact sensor calibration device, comprising, from top to bottom, an upper mounting plate, a conical target plate, a small buffer pad, a launching tube, a launching tube base plate, and a winding mechanism. The upper mounting plate is fixed to the upper end of the launching tube via a column, forming a calibration space. The conical target plate is located in the center of the calibration space, with its larger end facing upwards and its smaller end in contact with the small buffer pad. The larger end of the conical target plate has an outer edge. The target plate and the column are fitted with a clearance fit. The small buffer pad is installed at the opening of the launching tube. The launching tube contains a projectile, a compression spring, and a pull wire. The projectile is fitted with the launching tube with a clearance fit. The upper end of the compression spring abuts against the projectile, and the lower end abuts against the launching tube base plate. One end of the pull wire is connected to the projectile, and the other end passes through the compression spring and the launching tube base plate before connecting to the winding mechanism. The winding mechanism is installed at the bottom of the launching tube base plate and is used for winding and unwinding the pull wire. This invention can eliminate the additional errors caused by cable movement and the inconvenience of operation, improve the accuracy of calibration, and is convenient to carry.

The invention relates to a method for manufacturing a projectile (10) with a projectile body (12) and with a guide structure (22) applied to the projectile body (12), comprising: providing the projectile body and applying the guide structure to the projectile body by overlay welding at least one overlay material (26). The invention also relates to a projectile with a guide structure made of an overlay welded material.

The invention relates to a projectile (10) with a projectile casing (12) having a projectile front (14) with a front opening (18), wherein the front opening (18) can be closed by means of a locking screw (20), wherein a filling explosive charge centering tube (42) is attached inside the projectile casing (12), in which at least one filling explosive charge (60, 62) limited by a filling explosive charge cup (64, 66) is arranged, wherein a predetermined breaking point (68) is formed on a bottom (54) of the filling explosive charge centering tube (42) facing away from the projectile front (14), and wherein at least one vent channel (70, 72) is formed on the filling explosive charge cup (64, 66), which provides a flow connection between a first internal section (74) at the bottom (54) of the filling explosive charge centering tube (42) and a second internal section (76) of the filling explosive charge centering tube. (42) is produced, which is located on the side of the filling explosive charge (60, 62) facing the projectile front (14).

The invention provides a material dynamic stress-strain relation measuring method and system for bullet impact indentation, and the method comprises the steps: pre-processing a target material, and executing N times of hard spherical bullet impact target material tests; taking the indentation radius and residual depth of the pit as test data as input, and calculating and obtaining corresponding representative plastic strain according to the geometrical relationship that the spherical indenter of the hard spherical projectile generates the indentation on the target material; the bullet impact speed, the rebound speed and the pit geometric parameters which serve as test data serve as input, and representative stress is obtained through calculation; and performing data fitting on the representative plastic strain and the representative stress to obtain a dynamic stress-strain relationship of the target material. The technical bottleneck of direct measurement of the stress-strain relation under the ultrahigh strain rate is broken through, a representative stress-strain method in a quasi-static scene is innovatively expanded to the dynamic field, dependence on a preset constitutive model is not needed, and the dynamic stress-strain relation of the material is directly derived through test data.