250 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.

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.

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.

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.

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.

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.

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.

The invention relates to a projectile body penetration icebreaking test device which comprises a rack, a projectile body launching assembly, a positioning clamp, a protection assembly and an image shooting assembly, the rack is provided with a horizontal test surface used for placing a sample, and an opening located below the sample is formed in the horizontal test surface; the bottom of the projectile body launching assembly is a launching end pointing to the horizontal testing face, the projectile body launching assembly is rotationally connected with the rack in the vertical horizontal plane, the positioning clamp is installed on the horizontal testing face of the rack and provided with a positioning end, and the protection assembly is arranged below the horizontal testing face and fixedly connected with the rack. The image shooting assembly is mounted on the rack and is provided with an image acquisition end; the sample can be fixed on the horizontal test surface of the rack through the positioning clamp, the inclination angle of the launching end of the sample can be adjusted by rotating the projectile launching assembly, and the image information of the sample is acquired through the image shooting assembly, so that the impact damage of the projectile to the sample at different penetration angles is researched.

A projectile introduction system includes a central pipe configured to receive and guide a wellbore projectile therethrough, a ball guide mated to a top end of the central pipe, including sloped surfaces for guiding the wellbore projectile into the central pipe, a T-shaped joint including connections on opposing arms and in fluid communication with a bottom end of the central pipe, and at least one high-pressure line extending between a pump and a wellbore frac tree, wherein the connections on the opposing arms of the T-shaped joint are mated with the at least one high-pressure line.

The utility model provides an ammunition loading and unloading lifting appliance which is composed of two semicircular ring-shaped buckles with the same structure and two lifting ring screws, the whole structure of the lifting appliance is designed according to the structure of a projectile and the actual use requirement, the shape of the buckles refers to the head size of the projectile, and the two semicircular ring-shaped buckles with the same structure are adopted and connected through the lifting ring screws. The problem that a projectile loading and unloading lifting appliance is not matched with actual requirements can be solved, and the projectile loading and unloading requirements are met. The lifting appliance is simple in structure, convenient to operate and stable and reliable in performance, operators can be reduced, the loading and unloading efficiency can be improved, on the basis that the projectile is reliably lifted, it can be well guaranteed that the posture of the lifted projectile is kept vertical, the safety during projectile loading and unloading is improved, and the risk that the tail of the projectile is damaged is reduced. The loading and unloading lifting appliance disclosed by the utility model can provide a reference for the same type of problems.

The invention relates to the technical field of air cannons, in particular to a hundred-micron-sized bullet ultra-high-speed launching device and a using method thereof.The hundred-micron-sized bullet ultra-high-speed launching device comprises a high-pressure air chamber, a pump pipe, a conical section, a launching pipe and a target chamber; one end of the pump pipe can communicate with the high-pressure air chamber, and a piston is arranged in the pump pipe. An inlet of the conical section is communicated with the other end of the pump pipe; one end of the launching tube can be communicated with the outlet of the conical section; a throat pipe part is arranged in one end, close to the conical section, of the launching pipe; the throat pipe part is used for containing hundred-micron bullets; when the ultrahigh air pressure flows through the throat pipe part, the air passage is narrowed, so that the pressure and the speed of the air are further increased, and the hundred-micron-sized projectiles are launched out of the launching pipe at an ultrahigh speed. Meanwhile, the trajectory of the projectile is controlled near the axis of the launching tube, and the projectile is not in contact with the inner wall of the launching tube, so that the kinetic energy loss of the projectile is reduced, the ejection speed is favorably guaranteed, and the projectile is relatively completely ejected.

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.

The proposed technique is depending on decreasing the mass of the applicable bullets and its position in the front of the bullet as well as modifying the remaining body of the projectile by a rocket engine and a group of fins during the movability of the projectile toward the target. This technique is working when the projectile exits the pipe of the gun which in turn will increase the ability of the projectile to resist the force of gravity and the air friction. This in turn will resulting in an increasing of the speed of the projectile ongoing to the target and will increase its effective range.

The invention discloses a seeker missile-target connection line geographical system frame angle calculation method, device and equipment, and the method comprises the steps: obtaining a direction cosine matrix from a geographical coordinate system to a missile coordinate system according to an attitude angle provided by a navigation system; obtaining a direction cosine matrix from the projectile body coordinate system to the sight line coordinate system according to a frame angle, measured by the seeker, of the sight line coordinate system relative to the projectile body coordinate system; obtaining a direction cosine matrix from the geographic coordinate system to the sight line coordinate system according to the direction cosine matrix from the geographic coordinate system to the projectile body coordinate system and the direction cosine matrix from the projectile body coordinate system to the sight line coordinate system; and according to the direction cosine matrix from the geographic coordinate system to the line-of-sight coordinate system, calculating to obtain a frame angle of the projection of the missile-target connecting line in the geographic coordinate system. According to the method, platform attitude compensation is performed on the frame angle of the projectile-target connecting line projected in the sight line coordinate system obtained through measurement of the seeker, the frame angle of the projectile-target connecting line projected in the geographic coordinate system is obtained, and more accurate and reliable angle parameter input is provided for a fire control system.

The invention relates to a manufacturing method for an obturating ring (100) for a projectile where the obturating ring (1) is cast onto a projectile body (10) in a mold arranged on the projectile body comprising the following method steps; i.) a mold is arranged on the projectile body (10), ii.) the mold is heated, iii.) material is added to the mold, iv.) the mold cools, v.) the mold is removed. The invention further consists of a projectile body arranged with an obturating ring and a projectile.