208 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.

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.

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.

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 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 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.

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 present invention discloses a composite material winged projectile structure forming method, including: S1, pre-fixing the projectile and the wing; pre-assembling the projectile and the wing through a fixing tool, preliminarily determining the relative position of the upper fixing frame and the lower fixing frame; applying structural glue to the wing root surface where the wing and the projectile are in direct contact, determining the final position of the wing, and the wing inclination α must be less than 0.2 degrees; S2, secondary fixing the projectile and the wing; determining the side structural glue application radius R according to the projectile diameter, curing the side structural glue, and secondary fixing the wing and the projectile; S3, forming the projectile and wing reinforcement area; laying fabric prepregs of different sizes and quantities in the reinforcement area in sequence, and then heating and curing. The process controllable and reliable forming method provided by the present invention improves the safety and reliability of the winged projectile structure by controlling the application radius of the structural glue on the wing root surface and the accuracy and consistency of the laying of the reinforcement area, which is conducive to exerting the ultimate performance of the aircraft.

The present invention proposes a simulation method for simulating shot peening strengthening of a structural member with an inclined projectile impact. The number of projectiles at saturation shot peening is calculated based on the crater diameter obtained from the finite element simulation of a single projectile impact and the saturation shot peening coverage rate; a calculation method for residual stress at different projectile incident angles and projectile incident velocities is established, and the residual stress along the depth direction of the projectile impact area when the projectile is obliquely incident is calculated based on the residual stress along the depth direction of the projectile impact area when the projectile is vertically incident; a calculation method for residual stress in the area of multiple projectile impacts is established, and the residual stress along the depth direction of the projectile impact area during multiple projectile impacts is calculated based on the residual stress along the depth direction of the projectile impact area at different projectile incident velocities and projectile incident angles; the residual stress under different shot peening conditions is introduced into the structural member model in the form of initial stress, and thus the finite element simulation of the shot peening strengthening deformation of the structural member with an inclined projectile impact is carried out.

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 disclosure relates to a system for visually detecting projectiles to thereby confirm that the projectiles are not trapped in a conduit. The system includes a housing defining an inlet. A trap is positioned within the housing. The trap is moveable about and between a catching configuration and a releasing configuration. An actuator is configured to move the trap about and between the catching configuration and the releasing configuration. The housing has a window that permits visual detection of the trap from a position outside of the housing.

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.

The present disclosure provides devices, systems, and methods for aligning and securing a projectile. A base defining a receptacle for receiving the projectile comprises a self-centering mechanism for aligning a longitudinal axis of the projectile with a reference axis. An upstanding support projects upwardly from the base. A head member extends from the upstanding support, disposed vertically above the base, and has defined therein an opening aligned with the reference axis. A rod member is slidably mounted in the opening, such that a longitudinal axis of the rod member is aligned with the reference axis. A mounting adapter has a first end configured for adhesively retaining the projectile and a second end defining a coupling mechanism selectively mateable with a distal end of the rod member and with an inspection device used for performing inspection of the projectile.

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.