15 results about "Muzzle velocity" patented technology

The invention discloses a method for rapidly predicting the shape stability of a bird body emitted by a multistage electromagnetic coil, and the method comprises the steps: 1, inputting a structural parameter and an electrical parameter according to a bore-out speed requirement; 2, establishing a prediction model of the multistage electromagnetic coil transmitting device according to the parameters in the step 1; step 3, carrying out iterative calculation by adopting a forward difference method to obtain bird jerk after the cartridge case armature passes through the current-stage driving coil; 4, the bird body deformation stability in the current-level launching process is judged; 5, judging whether the armature displacement of the cartridge case meets the requirement or not, and if not, performing iteration at the current stage; if yes, executing the step 6; 6, setting the current, the mutual inductance and the mutual inductance gradient to be 0, and repeating the step 3 to carry out emission iterative calculation of the next-stage electromagnetic coil; 7, repeating the steps 4-6 until the prediction model reaches a preset out-of-bore speed; and step 8, outputting the final acceleration, displacement, speed and bird jerk curve of the cartridge case armature.

The utility model discloses a simulation test device of an initial velocity measuring device. The simulation test device comprises a main control module, a muzzle flame simulation module and a projectile initial velocity simulation module. A main control module; the system comprises a microprocessor unit MCU, a power supply management unit, a light-emitting tube LED driving unit and a communication interface unit. The MCU comprises a memory and an input unit, the memory stores an operation instruction for the light-emitting tube driving unit, and the MCU initializes the light-emitting tube LED driving unit and the communication interface unit after being powered on; the MCU controls an output signal of the LED driving unit according to the parameter setting of the input unit; the muzzle flame simulation module comprises at least one first light-emitting tube LED display screen; the projectile initial velocity simulation module comprises a plurality of second luminous tube LED display screens; and the display screen receives an output signal of the light-emitting tube LED driving unit and generates a predetermined light-emitting pattern. The simulation test device provided by the utility model is used for performance test during debugging, manufacturing and acceptance in the development process of ammunition training guarantee monitoring equipment.

The invention discloses a muzzle arc energy and mass center spatio-temporal evolution analysis method and system, and relates to the technical field of muzzle arc analysis, and the method comprises the steps: building an electromagnetic track launch muzzle arc simulation experiment platform, and obtaining a muzzle arc image through a high-speed photographing system; an arc contour image is obtained based on a local adaptive threshold segmentation and morphological gradient extraction algorithm, and the integrity and robustness of arc contour extraction are improved; based on a robust centroid tracking algorithm of multi-connected domain energy fusion and time sequence consistency constraint, a final arc centroid is obtained, and stable positioning and tracking of the arc energy centroid in the full evolution stage are achieved; and quantitatively analyzing the time-domain evolution characteristics of the highlighted area of the muzzle arc and the law of the spatial motion trail of the mass center of the highlighted area based on the muzzle arc images at different muzzle speed. An effective means is provided for quantitative characterization of a bore port arc, and an experimental basis and a theoretical reference are provided for optimization of a bore port structure, anti-ablation design, regulation and control of emission working conditions and the like of an electromagnetic emission system.

The present application provides an open reluctance cruise missile launcher, comprising a mounting frame, an electromagnet group disposed in the mounting frame, and a reluctance mover disposed in the electromagnet group. The launcher adopts the principle of electromagnetic induction for launch, and the cruise missile is pushed by the reluctance mover, which is disposed in the electromagnet group, which is disposed in the mounting frame. The mounting frame is an open structure, and is provided with multiple external air channels. The electromagnet group is an open structure, and is composed of multiple electromagnets and a number of guide rods. Internal air channels are formed between adjacent electromagnets. The air inside and outside the launcher can be quickly circulated through the multiple internal air channels and the multiple external air channels, which can effectively reduce the air resistance encountered by the cruise missile during launch, and can obtain the required muzzle velocity in a very short time. In addition, the noise during launch is greatly reduced, and the concealment is improved.

Perforation devices including gas supply structures and methods of utilizing the same. The perforation devices include a magazine, a barrel, an action, and the gas supply structure. The magazine is configured to contain a plurality of cartridges. The barrel extends between a breech, which is configured to receive a selected cartridge of the plurality of cartridges that includes a selected projectile, and a muzzle, which is configured, upon firing of the selected cartridge, to permit the selected projectile to exit the barrel at a muzzle velocity and with a muzzle trajectory. The action is configured to transfer the selected cartridge from the magazine to the breech of the barrel and to fire the selected cartridge. The gas supply structure is configured to provide a gas stream to the barrel and includes a surface gas source and a gas supply conduit extending between the surface gas source and the barrel.

The utility model discloses an initial speed measuring device which comprises a front-end acquisition device and a rear-end processing device. The front-end acquisition equipment comprises an acquisition chip, and a signal transmitting unit, a signal receiving unit and a zero-time signal triggering unit which are connected with the acquisition chip, and the acquisition chip is connected with the rear-end processing equipment through a photoelectric hybrid cable; the signal transmitting unit is used for transmitting a single-frequency continuous wave signal, the signal receiving unit is used for receiving a Doppler echo signal of the single-frequency continuous wave signal, the zero-time signal triggering unit is used for generating a triggering signal when a projectile is launched, and when the triggering signal is generated, a signal path is formed between the acquisition chip and the signal receiving unit; and the signal collection unit is used for collecting the Doppler echo signals received by the signal receiving unit and transmitting the Doppler echo signals to the rear-end processing equipment through the photoelectric hybrid cable. The device is high in integration level, reliable in data transmission, high in anti-interference capability and convenient to unfold and fold.

The application discloses a time-space evolution analysis method and system for muzzle electric arc energy and centroid, relates to the technical field of muzzle electric arc analysis, and comprises the following steps: building an electromagnetic track launching muzzle electric arc simulation experiment platform, acquiring a muzzle electric arc image by using a high-speed photography system, obtaining an electric arc contour image based on a local adaptive threshold segmentation and a morphological gradient extraction algorithm, and improving the integrity and robustness of electric arc contour extraction; based on a robust centroid tracking algorithm of multi-connected energy fusion and time sequence consistency constraint, obtaining a final electric arc centroid, realizing stable positioning and tracking of the electric arc energy centroid in the whole evolution stage; and based on the muzzle electric arc images under different muzzle velocities, quantitatively analyzing the time-domain evolution characteristics of the high-light area of the muzzle electric arc and the law of the spatial motion trajectory of the centroid. The application provides an effective means for quantitative characterization of the muzzle electric arc, and provides experimental basis and theoretical reference for muzzle structure optimization, anti-ablation design and launch working condition regulation of an electromagnetic launching system.

The application discloses a multi-sensor weighting trigger system for a gun muzzle velocity measuring radar and belongs to the technical field of gun muzzle velocity measurement; through infrared triggering, acceleration and other sensing triggering, Doppler triggering, electric shock triggering and other external triggering instruction signals, and then through the weighting judgment of a trigger decision device, reliable trigger information is obtained. The system utilizes the physical phenomena generated during the launching of weapons and ammunition, such as vibration, sound, fire, target movement and instruction information, simultaneously measures through the combination of multiple sensors, comprehensively judges the physical time, speed, intensity and other information according to logic, and finally outputs the trigger time and trigger signal, so that the false triggering and missed measurement caused by impact vibration resistance, gun interference, sunlight influence and electric noise interference are reduced, and the task reliability of the system is improved.

The invention belongs to the technical field of impact dynamics experiments, and discloses a fuse reverse overload test device and method, and the device comprises an impact generation device, a test projectile body, and a target body device. The impact generating device adopts an air cannon; the air cannon is used for launching a test projectile body, so that the test projectile body impacts the target body device at a preset out-of-chamber speed; the test projectile body is arranged in a gun barrel of the air cannon, and the test projectile body comprises a projectile body, a to-be-detected fuse and an acceleration sensor; the fuse to be detected and the acceleration sensor are symmetrically arranged at the tail part of the bomb body; wherein the acceleration sensor is used for collecting acceleration data of a fuse to be detected; the target body device is located on an exit path of the test projectile body; the air cannon is adopted as an impact generating device to launch the test projectile body with the fuze to be detected and impact the target body device, based on the principle of penetration overload, an impact response spectrum is obtained through the transient process that the test projectile body impacts the target body, and the accuracy and repeatability of test data are remarkably improved.

The utility model discloses a rear sliding type game gun which comprises an outer shell a, an outer shell b, a flame arrester, a traction shaft, a fishbone guide rail, a tail support fixing pipe and a tail support, an air cylinder shell is correspondingly arranged on a rod body of the middle portion of a piston rod in a sleeved mode, and an air pipe connector is installed at the bottom of the air cylinder shell in a communicating mode. A reset spring is arranged between the piston fixing piece and the air cylinder shell and corresponds to a rod body of the piston rod in a sleeved mode, a microswitch, a trigger, a trigger shaft and a trigger spring are correspondingly arranged in a cavity of the lower right portion of the outer shell a and a cavity of the lower right portion of the outer shell b, the wire harness steel wire fixing position corresponds to the bottom position of the grip, and the corrugated pipe fixing position corresponds to the bottom wall face. The rear-mounted sliding type game gun does not launch any objects with mass (including water, gas, water bullets, lead bullets, stones and the like), so that no muzzle initial velocity exists, only a toy for simulating shooting recoil force is provided, and the rear-mounted sliding type game gun is safer, more environmentally friendly and vivid in experience feeling.

The application discloses a method for inversely calculating parameters of a propellant combustion model based on a time sequence of bore pressure, and relates to the technical field of material constitutive parameter identification. The method comprises the following steps: obtaining sample values of parameters to be solved in a propellant combustion model; inputting the sample values into a two-dimensional axisymmetric finite element simulation model to obtain output results; establishing a mapping relationship between the parameters to be solved and the output results; obtaining actual bore pressure values and actual muzzle velocities in shooting tests; establishing an inverse calculation target function according to the actual bore pressure values, the actual muzzle velocities and the mapping relationship; and obtaining optimal values of the parameters to be solved according to the inverse calculation target function. The method can greatly reduce the number of tests and costs and ensure the accuracy of the data of the parameters to be solved by only a few actual shooting tests, a two-dimensional axisymmetric finite element simulation model and a calculation inverse calculation method, and finally obtaining the optimal values of the parameters to be solved.

1. The name of the design product: the target of the sky screen. 2. The use of the design product: for the collection of the muzzle velocity of the gun interior ballistic parameter. 3. The design points of the design product: in shape. 4. The picture or photo that can best show the design points: the perspective view.

The present application provides an open magnetic induction cruise missile launcher, comprising a mounting frame, an electromagnet group arranged in the mounting frame, and a magnetic induction type mover arranged in the electromagnet group. The launcher adopts the principle of electromagnetic induction for launch, and the cruise missile is pushed by the magnetic induction type mover, which is arranged in the electromagnet group, and the electromagnet group is arranged in the mounting frame. The mounting frame is an open structure, and a plurality of external air channels are provided on the mounting frame. The electromagnet group is an open structure, and the electromagnet group consists of a plurality of electromagnets and a plurality of guide rods, and an internal air channel is formed between adjacent electromagnets. The air inside and outside the launcher can be quickly circulated by the plurality of internal air channels and the plurality of external air channels, which can effectively reduce the air resistance encountered by the cruise missile during launch, and can obtain the required muzzle velocity in a very short time. In addition, the noise during launch is greatly reduced, and the concealment is improved.

The application belongs to the technical field of electromagnetic track launching, and specifically discloses an electromagnetic projectile injection device for Tokamak device disruption mitigation. The application realizes the first acceleration and then deceleration of the armature through four contact rails, four acceleration section reinforcing rails and four deceleration section reinforcing rails, the acceleration section reinforcing rails and the contact rails are isolated through an insulating plate, and the deceleration section reinforcing rails and the contact rails are isolated through an insulating plate. The four-rail scheme can increase the inductance gradient of the system, reduce the required current under the premise of meeting the muzzle velocity of the projectile, reduce the joule heat generated by the armature, and inhibit ablation. If the current of the reinforcing rail is increased, the magnetic field intensity can be increased, so as to further improve the equivalent inductance gradient, reduce the contact rail current, and reduce the ablation of the armature. In addition, the four contact rails are in interference contact with the tail wing of the armature, which can better limit the movement state of the armature, make the spatial magnetic field distribution more uniform, inhibit the deflection of the armature, ensure good electrical contact, and inhibit arc ablation.

The method for calculating the muzzle velocity of an armature comprises the following steps: calculating the force F(t)=m(u(t),x(t))I of the armature 2 , wherein m(u(t),x(t)) is a thrust factor, and I is the amplitude of the exciting current of the power supply of the electromagnetic launching device; obtaining the motion state of the armature, including the real-time position of the armature at time t, the real-time velocity of the armature, and the real-time acceleration of the armature; updating the motion state of the armature; judging whether the armature has been launched according to the updated motion state of the armature, if yes, taking the real-time velocity of the armature at this time as the muzzle velocity of the armature, completing the calculation, otherwise, executing step S5; determining the instantaneous frequency of the exciting current of the power supply according to the real-time position of the armature, and returning to step S1. The skin depth is introduced when the force of the armature is calculated, so that the calculation is more in line with the actual situation, the change from the force of the armature changing with the position to the force of the armature changing with time is realized, the solution of the force of the armature is more accurate, and the accuracy of the muzzle velocity of the armature calculated based on the force is also higher.