361 results about "Projectile" patented technology

The invention discloses a method for measuring an attitude angle of a free throwing object in a wind tunnel test through a binocular system, and belongs to the field of aerodynamics tests based on a photogrammetry technology. Comprising the steps that a binocular system is arranged in a wind tunnel, and internal and external parameters of the binocular system are calibrated through a cross scale; reconstructing the surface mark points of the calibration plate by photogrammetry outside the wind tunnel and establishing a local coordinate system; placing a calibration plate in the wind tunnel, wherein each vector of a local coordinate system is parallel or vertical to an incoming vector, and calibrating a wind tunnel coordinate system by adopting a resection method; carrying out photogrammetry and initial pose installation on mark points on the surface of a thrown object; acquiring each state image of the thrown object and reconstructing the three-dimensional coordinates of the surface mark points; taking the attitude angle of the thrown object as 0 degree as a reference state, and comparing the rigid body transformation relationship between the blowing state point cloud and the reference state point cloud to obtain attitude angle data. Alignment of a wind tunnel coordinate system and a binocular system coordinate system can be achieved, limitation of the appearance of the thrown object is avoided, and attitude angle data of the thrown object are calculated in a non-contact and high-precision mode.

A suppressor baffle includes a cone portion expanding along a central axis from a proximal end defining a projectile opening to an open distal end having an outer rim. The projectile opening is in an entrance plane oriented obliquely to the central axis. A first volume between a first side of the cone portion and a central plane that includes the central axis is smaller than a second volume between an opposite second side of the cone portion and the central plane. At least part of the outer surface of the second side of the cone portion has a convex profile as viewed along the central plane from a side of the suppressor baffle. In another example, a first part of the cone is axially offset from an opposite second part of the cone, resulting in a curved projectile opening profile and a curved outer rim profile.

The invention discloses a material superspeed condition and particle friction electrification ground simulation device and method, and relates to the field of static electricity, the device comprises a projectile ejection device, a projectile flight track, a grounding ring, a first Faraday cup, a projectile friction zone and a second Faraday cup which are arranged in sequence; the projectile flight orbit, the first Faraday cup, the projectile friction area and the second Faraday cup are all arranged on the flight orbit of the measured projectile; one end of the grounding ring is connected with one end, close to the first Faraday cylinder, of the projectile flight orbit; the accelerated to-be-tested projectile passes through the first Faraday cup, the projectile friction area and the second Faraday cup in sequence; the first Faraday cylinder and the second Faraday cylinder are both used for sensing the charge of the measured projectile; and the projectile friction area is used for carrying out a friction experiment on the tested material. According to the invention, the triboelectrification rule of the flying body in the flying process can be accurately simulated.

The invention provides a three-dimensional numerical simulation method and system for supercavitation projectile high-speed inclined water discharge, and the method comprises the steps: building a three-dimensional geometric model of a projectile and a flow field computational domain, and outputting projectile body attribute parameters; estimating the size of a projectile body motion area, performing grid division on the projectile body and a flow field calculation domain, importing fluid solving software, establishing an overlapping calculation domain, and setting projectile attribute parameters and fluid solver boundary conditions; the influence of compressibility of water on the high-speed projectile is considered, a user-defined function is adopted, and the nonlinear relation between the density and the pressure of the compressible liquid under the isothermal condition is established; initial motion parameters of the projectile are defined, numerical solution is carried out, and cavitation evolution, flow field distribution, stress and motion characteristics in the water outlet process of the high-speed inclined projectile are obtained. According to the invention, the high-speed inclined water outlet process of the projectile under different working conditions can be simulated, the cost can be effectively reduced, and a technical basis is provided for a submarine launching test.

Provided is small arms ammunition projectile (24) and manufacturing method having a core (10) with a longitudinal core axis, a forward portion (18), and a rearward end (14). The core (10) has a rear portion (16) with an edge (26) that may be chamfered or radiused, a first portion (28) being frustoconical, and a second portion (30) adjacent the first portion (28) being substantially cylindrical. The jacket (12) has a longitudinal axis (99) and longitudinally extending socket (45) to receive the rear portion (16) of the core (10). The socket (45) has a socket bottom (46), a first socket portion (50) being frustoconical, and a second socket portion (52) adjacent the first socket portion (50) being substantially cylindrical. The core (10) and jacket (12) are shaped such that when assembled, the frustoconical portion (28) of the core (10) is seated in the frustoconical portion (50) of the socket (45) of the jacket (12), respective contact surfaces (31, 41) of the second portions (30, 52) of the core (10) and jacket (12) mate together with the longitudinal core axis (98) and longitudinal jacket axis (99) being coaxial.

The present invention relates to a projectile, in particular deformation and / or partial fragmentation bullet, comprising an essentially cylindrical projectile tail, an adjoining bow sided projectile head with an essentially central opening which opens into a cavity that extends axially from the projectile head in the direction of the projectile tail, preferably into the projectile tail, which has a cavity bottom and is bounded by a wall, and an tear-off groove introduced into the wall and, at least partially surroundings the cavity, which is arranged at a distance of at least 10% of the longitudinal extension of the cavity from the cavity bottom and has a radial depth of at least 10% of a caliber diameter and / or of at least 30% of a radial wall thickness of the wall surrounding the cavity.

A projectile is integrally formed with a high-G shock isolator to isolate a protected device. The isolator includes a pattern of cut-outs formed around a circumference of a metal casing that defines flexures and supports and coupling paths that zigzag therethrough. Symmetry about the longitudinal axis of the projectile defines springs that are colinear with the principal axes of the projectile with a resonant frequency selected to attenuate shock inputs to levels acceptable to the protected device. The isolator is suitably provided with forward and aft stops to ensure isolator survivability. The aft stops are positioned in the cut-outs to prevent the flexures compressing beyond the yield strength of the casing material. The forward stop includes a structure rigidly attached behind the isolator that extends forward to engage a forward-facing surface of the isolator to prevent the flexures from stretching beyond the yield strength of the casing material.

The invention relates to a floating double-powder-chamber balance gun structure which comprises a front body tube, a first powder chamber, a second powder chamber, bullets, a balance body and a rear body tube. The front body tube is a motion section of the projectile; the first powder chamber is used for filling a first main charge; the second powder chamber clings to the balance body and is used for filling a second main charge; the projectile is a main launcher; and the balance body is used for balancing recoil force generated by launching the projectile. Compared with the prior art, through the arrangement of the first powder chamber and the second powder chamber, the initial running speed of the projectile is increased on the premise that the maximum in-chamber pressure of the balance gun is not increased; according to the invention, simple structure and principle are applied, the problem of high bore pressure caused by high initial velocity index of a large-diameter barrel weapon can be solved, safe test launching of the barrel weapon is realized, and the test device provided by the invention is simple in structure, simple to operate, safe, reliable, economical and practical.

Projectiles and methods of making and using same are disclosed herein. A projectile comprises a first portion having a first cylindrical portion having a first flat end surface, a first section extending from the first cylindrical portion at a first acute angle, a second section extending from the first section at a second acute angle, and a tip section extending from the second section and terminating in a pointed tip. The projectile includes a second portion having a second cylindrical portion having a second flat end surface and a trailing portion having a generally frustoconical shape. The trailing portion tapers towards a trailing end of the projectile. A post couples the first cylindrical portion and the second cylindrical portion. The post is in contact with each of the first flat end surface and the second flat end surface.

A projectile system is described, the projectile system includes a projectile body, the projectile body including a front end portion that tapers to a point at the front end and the front end portion of the projectile body is dimensionally smaller than a bore of a firearm system, the projectile body including a driving band portion behind the front end portion of the projectile body, the driving band the driving band portion being dimensionally equal to a caliber of the firearm system and dimensionally greater than a bore diameter of the firearm system, such that the driving band portion comes into contact with the bore of the firearm system when the projectile passes through the bore of the firearm system.

Disclosed are embodiments for determining the position and speed of a projectile in 3D world coordinates using a calibrated camera and radar. In some embodiments, a method comprises: capturing a sequential set of images of a projectile in motion; determining a radial velocity of the projectile; determining a set of two-dimensional (2D) image points representing respective locations of the projectile in the sequential set of images; determining respective depths of the 2D image points in their respective 2D image planes based on the 2D image points, time intervals between the captured 2D images, the radial velocity and a rotational part of a homographic transformation, the homographic transformation configured to project three-dimensional (3D) world coordinates to the 2D image planes; and determining a set of 3D world points of the projectile in the 3D world coordinates based on the 2D image points, the respective depths thereof and the homographic projection.

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.

The invention provides a continuous bomb dropping device and a continuous water entry test device and method for a bomb body in a decompression environment, and belongs to the technical field of cross-medium water entry test devices. In the continuous bomb dropping device, a moving sliding table is fixedly arranged on a support, a bomb body releasing structure comprises a supporting shell, a rotating wheel and a driving piece, the supporting shell is connected with the moving sliding table, the moving sliding table can drive the bomb body releasing structure to move in the vertical direction, the rotating wheel is rotationally arranged on the supporting shell, and the driving piece is fixedly arranged on the supporting shell and connected with the rotating wheel. The driving part can drive the rotating wheel to rotate, the rotating wheel is provided with a plurality of projectile body containing cavities, the multiple projectile body containing cavities are arranged at intervals in the circumferential direction of the rotating wheel, a projectile outlet is formed in the lower portion of the supporting shell, and the projectile outlet is configured in the mode that when the projectile body containing cavities communicate with the projectile outlet, projectile bodies in the projectile body containing cavities are separated from the projectile body containing cavities and penetrate through the projectile outlet. And after one-time pressure reduction is conducted on the pressure reduction tank, continuous controllable release of the multiple projectile bodies entering water is achieved.

Described herein are multi-part projectiles that include a high-friction coating as part of an interface between parts of the projectile body. The high-friction coating reduces the probability that projectile parts coupled at the interface would rotate relative as the projectile is launched, thus enhancing the reliability and accuracy of the projectile. In one example, a multi-part projectile includes a projectile body having first and back sections coupled by an interface. The front section has a front land and the back section has a back land. The threaded interface restrains the rotation of the projectile body first and back sections. A high-friction coating is disposed on at least one of the lands of one or both the front and back sections. The high-friction coating has a co-efficient of friction greater than the parent metals against each other alone, without the high-friction coating disposed therebetween.

The invention belongs to the technical field of launching platforms, and particularly relates to a same-projectile different-shot average trajectory difference evaluation method which comprises the following steps: step 1, establishing a trajectory simulation model; 2, carrying out an average ballistic performance difference check test; 3, identifying a zero resistance coefficient; 4, coincidence calculation is carried out; step 5, determining equivalent distributed source parameter distribution characteristics; 6, equivalent current-day error source parameter distribution characteristics are determined; 7, estimating a system error; 8, evaluating the average ballistic difference of the non-test supporting points; step 9, reconstructing a trajectory; and step 10, evaluating the average ballistic difference of the test supporting points. Compared with the prior art, the method has the advantages that test supporting point average ballistic difference evaluation with low consumption, low false risk and high credibility can be realized; and non-test supporting point average ballistic performance difference evaluation information can be given, and comprehensive evaluation is realized.

The invention discloses a projectile pose measuring and calculating system based on a multilevel feature fusion neural network and visual three-dimensional model fitting, which captures a high-speed projectile flight image on the basis of a deep learning technology, realizes the detection of a target image through a target detection technology based on the multilevel feature fusion of the neural network, and realizes the measurement and calculation of the projectile pose. And on the basis, a posture reconstruction resolving technology based on monocular vision and a projectile model is used for realizing the resolving work of the projectile state, so that the accurate measurement of the projectile muzzle state is realized, the test range is not less than 10 degrees, and the test error is less than 5%. According to the method, the detection precision is improved, the bullet muzzle state parameters can be accurately measured, solid data support is provided for artillery performance evaluation and improvement, and the method has higher anti-interference performance.

The invention discloses a stationary oblique detonation wave cell structure measurement system and method, and the system comprises an experiment module, two ends of the experiment module are respectively provided with an inlet hole and an outlet hole, the inlet hole and the outlet hole are provided with membranes for sealing the experiment module, and the experiment module is pre-filled with combustible gas; the projectile launching device is arranged at one end of the experiment module and used for accelerating a projectile to a target speed and then launching the projectile into the experiment module from the inlet hole, the projectile is ejected from the outlet hole, and the projectile with the target speed makes contact with the combustible gas in the experiment module to be detonated and induces oblique detonation waves to occur; the smoke trace plates are arranged in the experiment module and distributed in the circumferential direction and / or the axial direction of a trajectory where the projectile enters the experiment module, and the surfaces of the smoke trace plates make contact with generated oblique detonation waves and are subjected to flowing strafing to form cells. According to the invention, the smoke trace plate can be adaptively arranged according to the flow field characteristics of oblique waves and bombardment waves, so that the accurate cell form and size can be captured.

The invention herein describes an aerodynamically improved projectile which has less overall mass and achieves higher maximum velocities. The projectile has a jacket with a nose opening and a base opening and a core disposed therein. The core is open-ended and has a channel defined from the open forward end to the open base end. The channel is axially aligned with the nose opening and base opening of the jacket. Removably attached to the base opening is a base cover that is engineered to detach from the projectile during flight. A pressure differential created in the channel during projectile flight causes the base cover to detach from the projectile, thereby fully opening the channel.

The invention discloses an active projectile burst perforation damage behavior prediction method, which comprises the following steps of: constructing a quasi-closed container temperature rise and energy conversion model based on a first law of thermodynamics, and analyzing energy release and global overpressure in an active material quasi-closed container based on the model, and an equivalent TNT equivalent relation reserved for a detonation product by PTFE / AL, so as to predict the burst perforation damage behavior of an active projectile. A method for predicting the shock wave overpressure peak value and the positive pressure area action time in the air is further established, a projectile-target collision behavior is converted into target plate deformation work through specific kinetic energy modeling of a penetration body projectile, a target plate deformation prediction model is established on the basis of impact wave overpressure and positive pressure area action time factors, and meanwhile, the impact wave overpressure peak value in the air and the positive pressure area action time are predicted on the basis of fracture mechanical behavior analysis. Under the condition of considering the crack ultimate strength factor, an aftereffect target ultimate deformation prediction model is established. Based on this, the scheme provides a brand new solution thought for the prediction method of the damage behavior of active projectile energy release-temperature rise-overpressure-bursting perforation of PTFE / AL.

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.

The invention provides a cavity head type navigation body time-delay air cushion buffer load reduction device combined with active ventilation, and belongs to the field of moving object high-speed water entry impact load reduction. The technical problems of a load reduction mechanism and a load reduction effect of the air cushion effect of the navigation body are solved. Through the combined effect of the porous air leakage structure and the active ventilation device, adjustment and control over the load reduction air cushion of the head when the concave cavity head type projectile sails in water are achieved, the load reduction function is achieved, and meanwhile the negative influence of the air cushion effect on the sailing process of the projectile is avoided. A novel porous air leakage method is adopted, the pressure intensity of the air cushion in the concave cavity is kept at a low value through time-delay air leakage, buffering load reduction is achieved in combination with active ventilation, and technical support is provided for high-speed water entry flow control, load reduction design, low-load stable configuration theory development and the like.

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.

Provided is small arms ammunition projectile (24) and manufacturing method having a core (10) with a longitudinal core axis, a forward portion (18), and a rearward end (14). The core (10) has a rear portion (16) with an edge (26) that may be chamfered or radiused, a first portion (28) being frustoconical, and a second portion (30) adjacent the first portion (28) being substantially cylindrical. The jacket (12) has a longitudinal axis (99) and longitudinally extending socket (45) to receive the rear portion (16) of the core (10). The socket (45) has a socket bottom (46), a first socket portion (50) being frustoconical, and a second socket portion (52) adjacent the first socket portion (50) being substantially cylindrical. The core (10) and jacket (12) are shaped such that when assembled, the frustoconical portion (28) of the core (10) is seated in the frustoconical portion (50) of the socket (45) of the jacket (12), respective contact surfaces (31, 41) of the second portions (30, 52) of the core (10) and jacket (12) mate together with the longitudinal core axis (98) and longitudinal jacket axis (99) being coaxial.

The invention relates to the technical field of machining, in particular to a numerical control machine tool for machining a grenade body, which comprises a rack, a clamping piece, a servo tool turret and a tailstock supporting device, a main shaft box and a feeding box are installed on the machine frame. The clamping piece is installed on a main shaft of the main shaft box and used for clamping a projectile body, and the main shaft box is used for driving the clamping piece to rotate. The servo tool turret is mounted on a feeding seat of the feeding box and used for mounting a plurality of tools, and the feeding box is used for driving the servo tool turret to feed a projectile body so as to cut the projectile body; the tailstock supporting device is arranged on the rack and used for supporting the end, away from the clamping piece, of the projectile body. The tailstock supporting device comprises a sliding rail, a sliding base assembly, a driving piece and a positioning ring. The sliding rail is arranged on the rack; the sliding seat assembly is slidably arranged on the sliding rail; the driving piece is used for driving the sliding seat assembly to slide on the sliding rail; the positioning ring is rotationally arranged on the sliding seat assembly, and a positioning hole is formed in the positioning ring. The method has the effects of improving the machining precision of the projectile body and improving the production efficiency and quality of the projectile body.

The invention discloses a method for estimating the penetration UHPC depth of a long-rod projectile based on an empirical formula, which comprises the following steps: firstly, according to a known test, carrying out numerical simulation by utilizing LS-Dyna finite element software, comparing a numerical simulation result with an experimental result, verifying the accuracy and correctness of a numerical simulation method, then designing 27 calculation working conditions according to 5 parameters, and calculating the penetration UHPC depth of the long-rod projectile according to the 27 calculation working conditions. Under the condition that other parameters are controlled to be unchanged, the influences of the parameters M, d, v, fc and phi on the penetration depth are analyzed in detail, and an empirical formula is given, so that the empirical formula is suitable for long-rod projectile penetration UHPC depth prediction. According to the method, a mathematical model is adopted to establish the relationship between the penetration depth and the projectile body speed, the projectile body mass, the bullet shape, the compressive strength and the projectile body diameter. And the penetration depth of the projectile body to the UHPC is predicted by inputting related parameters. The method is mainly used for evaluating the anti-penetration performance of the UHPC structural engineering, and is beneficial to improving the working efficiency and saving the cost.

There is provided a projectile for throwing underwater by hand, the projectile comprising an elongate body having a hemispherical nose and a paraboloid tail portion extending from the hemispherical nose to a flat end, and multiple tail fins extending away from the elongate body and positioned proximate the flat end. There is also provided methods by which the projectile may be filled, emptied, and used for a dodge-the-torpedo game.

The invention discloses a projectile body trajectory posture adjusting device and method, and belongs to the technical field of projectile body posture adjusting.The adjusting device comprises an outer shell, a first torque adjusting assembly and a second torque adjusting assembly, the first torque adjusting assembly and the second torque adjusting assembly are arranged in the outer shell, and the adjusting method comprises the steps that the outer shell is installed at the end, far away from the mass center of a whole projectile, in the projectile body; when the trajectory posture needs to be adjusted, the missile-borne computer firstly starts the first torque adjusting assembly, and the rotating speed of the second torque adjusting assembly is preliminarily increased; when the projectile body is located at a specific trajectory position, the missile-borne computer starts the second torque adjusting assembly, a movable mass block in the second torque adjusting assembly rotates to generate mass eccentricity, and the trajectory posture of the projectile body is adjusted through the eccentricity generated by rotating the mass, so that the aim of dynamically controlling the flight posture of the projectile body is achieved. The structure is simple and compact, the size is small, the adjusting capacity is high, the influence on the mass center and pneumatic parameters of the projectile body is small, and the influence of pneumatic resistance caused by the change of the appearance structure of the projectile body on the range is effectively avoided.

Composite projectiles include various material compositions, diameters, and cavities within the projectiles having a variety of cavity diameters, sidewalls, and bottoms selected and formed to induce different levels of penetration and disintegration of the composite projectiles upon impact with targets.

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.