38 results about "Electromagnetic launch" patented technology

The application relates to the field of aerospace superconducting electromagnetic launching technology and discloses a magnet lateral damping anti-collision device for aerospace superconducting electromagnetic launching. The device comprises a first lateral sliding plate, a second lateral sliding plate and a damping anti-collision mechanism. The first lateral sliding plate is arranged on the surface of a first ground module, the second lateral sliding plate is arranged on the surface of a second ground module, the damping anti-collision mechanism is fixed on the two sides of a superconducting magnet in a symmetrical mode to be connected with the superconducting magnet as a whole, and the damping anti-collision mechanism cooperates with the first lateral sliding plate and the second lateral sliding plate to realize lateral damping anti-collision during the movement of the superconducting magnet. Therefore, not only can the rigid body collision between the superconducting magnet and the ground module be prevented when the superconducting magnet is horizontally deviated, but also the lateral impact load during the occurrence process can be mitigated and attenuated, and the success rate of single launching can be improved.

The invention discloses an airborne fire extinguishing device. The airborne fire extinguishing device comprises a power assembly and a fire extinguishing bomb launching assembly, the fire extinguishing bomb launching assembly comprises a launching tube, the launching tube comprises a launching guide rail, the launching guide rail is an electromagnetic guide rail, and the power assembly can provide instantaneous current for the launching guide rail through a cable; the launching tube is connected to the launching seat and is used for launching a guide rail; the fire extinguishing bomb launching assembly comprises a launching seat and a supporting seat, the supporting seat can rotate, the launching seat is connected to the supporting seat and can rotate along with rotation of the supporting seat, and therefore the launching direction of the fire extinguishing bomb launching assembly can be adjusted. The airborne fire extinguishing device can be installed on an airplane, the electromagnetic launching mechanism is adopted to remotely launch the fire extinguishing bomb, so that the airplane does not need to fly over a fire center during fire extinguishing, the safety in the fire extinguishing process is improved, the throwing range of the fire extinguishing bomb is larger, and throwing is more accurate.

The motorized launch system includes a vehicle having at least one electrically conductive coil arranged to interact with at least one ultra-high conductivity material track in the guide rail when the vehicle is moved through the guide rail. The drive device drives the vehicle at a speed at which a current is induced in the track, the current being sufficient to suspend the vehicle and to inhibit the vehicle from colliding with the guide rail and the track by electric suspension when the vehicle is moving along the track, and drives the vehicle at a firing speed to launch the vehicle from the guide rail. The firing speed is at least as high as the first speed. The controller controls the release mechanism to release the payload from the vehicle to launch the vehicle from the rail while the at least one drive device drives the vehicle at the launch speed.

The invention provides an armature structure of a coil type electromagnetic launching flying net capturing unmanned aerial vehicle, and belongs to the technical field of electromagnetic launching and unmanned aerial vehicle prevention and control. The armature adopts a cylindrical high-strength engineering plastic shell, grooves which are uniformly distributed in the circumferential direction are formed in the end face, corresponding axial long grooves are formed in the side face and used for containing iron steel columns, high-strength compression springs are symmetrically arranged in the armature and provide power for bouncing off of the steel columns, and the steel columns are connected with a light high-strength fiber flying net through connecting ropes. When the armature is in the gun barrel, the inner wall of the gun barrel forms natural radial constraint on the steel column, the spring drives the steel column to pop off synchronously after the armature is ejected out of the gun barrel, and the flying net is pulled to be uniformly unfolded to form a circular catching net surface. The technical problems that an existing armature cannot be matched with a coil gun, a flying net is unevenly unfolded, an all-metal structure is prone to electromagnetic short circuit and large in weight, and a limiting structure is tedious and prone to clamping stagnation are solved. The electromagnetic armature has the advantages of being matched with the coil gun, efficient in acceleration, even in flying net unfolding, simple in structure, light, insulated and stable in launching.

A multifunctional electromagnetic deployment device and method for wind tunnel model deployment tests belongs to the field of dynamic testing technology for model wind tunnels. It solves the problems of slow deployment speed and poor repeatability in existing technologies. Key technical points: The top surface of the bracket is fixedly connected to the test model. Two openings are made at the bottom of the bracket, each containing an electromagnet. Two electromagnet cover plates are installed at the bottom of the bracket corresponding to the two electromagnets. A limiter track is provided between the two openings. The model head section, front magnetic section, middle section, rear magnetic section, and tail section are sequentially spliced ​​and fixed. Mounting grooves are provided on both the front and rear magnetic sections. A neodymium magnet with a countersunk hole is placed in the mounting groove closest to the bracket at the top. This invention realizes the connection of the test model before separation, free deployment of the deployed object, and deployment of the object with initial velocity, ensuring close contact between the deployed objects and simulating the real separation process.

The invention relates to a superconducting electromagnetic launching platform safety braking system, a launching platform comprises a track and a test skid car, a sliding rail is fixed on the track, the test skid car is provided with a sliding shoe matched with the sliding rail, and the braking system comprises a sliding shoe friction device, a sliding rail friction device and a clamping plate friction device. The sliding shoe friction device comprises an inner friction block fixed to the inner wall of the sliding shoe and an outer friction block fixed to the outer side wall of the sliding shoe, the sliding rail friction device and the clamping plate friction device are arranged at the ends of the sliding rail, and notches matched with the sliding rail friction device are formed in the two sides of the sliding rail. The sliding rail friction device comprises inner friction plates fixed to the two sides of the sliding rail and matched with the inner friction blocks, inner elastic buffering pieces are arranged between the inner friction plates and the sliding rail, the clamping plate friction device comprises L-shaped supports fixed to the two sides of the sliding rail, and outer friction plates matched with the outer friction blocks are fixed to the inner sides of the L-shaped supports. And an outer elastic buffer piece is arranged between the outer friction plate and the L-shaped bracket. The device has the advantages of being simple in structure, safe, reliable and high in practicability.

This invention discloses a modular pulse-magnetized double-sided high-temperature superconducting linear synchronous motor. The motor uses high-temperature superconducting bulk material as the excitation magnet for the mover and utilizes a pulse magnetization device integrated into the magnetization section of the linear motor to achieve in-situ high remanence magnetization of the mover. The system consists of a pulse power supply system, a modular superconducting mover system, and a double-sided stator system. The pulse power supply system uses a large-capacity capacitor bank and, in conjunction with the split magnet coils in the motor's magnetization section, generates a millisecond-level strong pulsed magnetic field to achieve rapid high remanence magnetization of the high-temperature superconducting bulk material. The modular superconducting mover maintains the required low temperature for superconductivity through a Dewar structure, and the number of superconducting mover modules can be increased or decreased as needed to meet different thrust requirements. Simultaneously, the impact of local quenching is limited to a single module, preventing quenching from affecting other movers and improving system reliability. The double-sided stator structure reduces normal electromagnetic force, improves high-speed operation stability, and fully utilizes the double-sided high magnetic field advantage of the high-temperature superconducting mover to enhance the motor's thrust performance. This structure achieves a high degree of integration between the magnetization device and the motor stator, significantly improving the power density, operational stability, and maintenance convenience of the linear motor. It is suitable for applications with high requirements for the thrust performance and reliability of linear motors, such as electromagnetic launch and ultra-high-speed rail transit.

This invention discloses a portable electromagnetic pine cone harvesting gun, relating to the fields of agricultural machinery and electromagnetic launch technology. It includes: an aiming module that locks onto the harvesting target; a controller module that receives the bullet's position signal and generates a discharge signal or a stop-discharge signal based on the position signal; an energy module that stores preset energy, discharges the firing module according to the discharge signal, and stops discharging the firing module according to the stop-discharge signal; the firing module automatically fills the bullet to the firing position, and when the bullet reaches a first preset position, sends a first position signal to the controller module, accelerating the bullet while the energy module discharges; when the bullet reaches a second preset position, sends a second position signal to the controller module, terminating the acceleration of the bullet after the energy module stops discharging, and then fires at the harvesting target according to the firing signal. This invention achieves efficient pine cone harvesting through electromagnetic acceleration technology, reducing safety hazards and damage to trees.

The application discloses a kind of electromagnetic track damage detection method and system of multi-field coupling analysis, it is related to electromagnetic track launcher technical field, including: obtaining simulated armature loop pulse current, armature mechanical parameter and armature kinematics parameter, import electromagnetic heat multi-physics field coupling model, obtain field-circuit coupling model;Obtain the distribution of current density and temperature along the boundary of armature slot inside boundary and pivot rail contact interface boundary in the simulation process under multi-physics field coupling;According to the change of current density and temperature under different armature placement initial position, determine the optimal initial position of armature placement, and according to the change of current density and temperature under the different electromagnetic transmitter track material set, determine optimal track material;Build electromagnetic track launch system simulation experiment platform, test the surface damage of track at different positions under different pulse current peak and launch times, clarify the characteristics of track surface cumulative wear and ablation damage under different working conditions.

This invention discloses an armature coating with ablation resistance and conductive lubrication properties, and its preparation method. A refractory metal is deposited on the armature surface using cold spraying technology. The surface of the refractory metal coating is then processed into an array of pits of a certain depth. Next, a low-melting-point alloy powder is sprayed onto the textured pits using a cold spraying process to fill the pits. Finally, the low-melting-point alloy coating above the pit surface is removed, resulting in a morphology of a dotted textured array of low-melting-point alloy distributed on the refractory metal surface. The refractory metal coating significantly improves the armature's ablation resistance, while the low-melting-point alloy provides continuous conductive lubrication at the friction interface. This invention combines the high-melting-point ablation resistance of the refractory metal coating with the conductive lubrication properties of the low-melting-point metal, overcoming the limitation of traditional single-function protective coatings for armature surfaces. It enables the preparation of a novel protective coating for electromagnetic launch armature surfaces that possesses excellent conductivity, lubrication, and ablation resistance.

This invention relates to the field of building material structural testing technology, specifically a system and method for testing the impact resistance performance of railings and handrails. The system includes: launching a standard test impactor at a preset impact point using a controllable electromagnetic launcher; acquiring a sequence of transient deformation images from multiple perspectives using a high-speed camera; extracting the spatial coordinates of structural feature points through image enhancement and feature point calibration; and calculating the dynamic displacement field and dynamic strain field. An elastoplastic dynamics inversion algorithm is used to calculate the stress distribution time history and local plastic deformation within the impact contact area, identifying stress concentration areas and determining the stress peak and stress cycle number. Combined with the degree of residual deformation, the impact resistance performance level of the railing and handrail is quantitatively assessed, achieving standardization of the testing process and quantification of the results. This method enables controllable impact process and multi-dimensional deformation acquisition, accurately obtaining the internal mechanical response parameters of the component.

This application belongs to the field of ultra-high-speed electromagnetic launch design analysis, specifically disclosing a design method for a wound-type electromagnetic launch system. The method includes: analyzing the electromagnetic performance of the wound-type electromagnetic launch system based on its thrust model to determine a first selection strategy for the capacitor in the system's excitation source; analyzing the system thrust, capacitor discharge in the system's excitation source, and changes in the pulse power device current to determine a second selection strategy for the number of turns in the drive coil and the number of turns in the launcher's armature coil; performing parameter selection analysis on the repetitive peak voltage, pulse peak current, critical rate of rise of the on-state current, and current pulse width of the system's excitation source to determine a third selection strategy for the pulse power device in the system's excitation source; and designing the wound-type electromagnetic launch system based on the first, second, and third selection strategies. This application enables the efficient and high-precision rapid design of wound-type electromagnetic launch systems.

The invention discloses a phase change energy storage rolling driving system for a high-speed dynamic platform, which comprises a high-speed dynamic test platform, an intermediate mechanical transmission device, a blade oscillating cylinder, a phase change energy storage assembly, a hydraulic servo system and an electrical control system, the high-speed dynamic test platform is a supporting mechanism of a tested piece, a phase change energy storage assembly, an intermediate mechanical transmission device, a blade swing cylinder, a hydraulic servo system and an electrical system, and a sub-supersonic speed dynamic environment is achieved through electromagnetic launching, gunpowder propelling and high-pressure gas driving modes. The intermediate mechanical transmission device is a connecting mechanism between the driving device of the blade swinging cylinder and a tested piece, and realizes rolling movement through the blade swinging cylinder; the phase change energy storage assembly generates high-pressure gas through carbon dioxide phase change and breaks through a rupture disk to drive a piston type energy accumulator to generate a high-pressure oil source to drive a blade swing cylinder. The blade oscillating cylinder is controlled by a hydraulic servo system, and any attitude angle and angular velocity control rule of the tested piece is realized by adopting a waveform iterative algorithm.

The invention discloses a semi-physical simulation system and method for ground separation control of an electromagnetic launch rocket, and the system comprises a launch control module, an electromagnetic propulsion simulation module, a booster simulation module and a communication module, and the electromagnetic propulsion simulation module and the booster simulation module are connected with the launch control module through the communication module. The emission control module adopts real equipment and is used for issuing control instructions to the electromagnetic propulsion simulation module and the booster simulation module through the communication module, and the electromagnetic propulsion simulation module and the booster simulation module generate feedback data according to the control instructions. The emission control module receives feedback data generated by the electromagnetic propulsion simulation module and the booster simulation module through the communication module to form a simulation test process closed loop. By combining the real control module and the simulation module, the vehicle and carrier rocket separation control scene is simulated, the effectiveness of the separation control strategy can be verified, design vulnerabilities can be found as soon as possible, and therefore the research and development period is shortened.

The invention relates to a test system and method for a space deployable and retractable penetration flying spear. Comprising a foldable main body structure, a low-interference test module, a motor rope collecting and recovering module, an electromagnetic transmitting module and a control module, the foldable main body structure comprises a bottom plate, an electric multi-stage cylinder, a target plate and an electromagnetic transmitting device; the electric multi-stage cylinder is used for driving and placing a target plate at a preset position, and the low-interference test module is used for testing and collecting impact force of a flying spear, attitude information of the flying spear, axial acceleration of the flying spear at the moment of penetration, real-time tension of a tether and an included angle between the tether and a penetration axis; the motor rope collecting and recycling module is used for recycling the flying spear after penetration; on one hand, the control module comprehensively coordinates unfolding and folding of the electric multi-stage cylinder, adjustment of electromagnetic emission parameters, synchronous acquisition of sensors and start and stop of a recovery motor to realize automation of a test process; and on the other hand, synchronous analysis and error correction are carried out on the collected data to generate a performance evaluation result. The technical blank is filled, and the development of the fragment removal technology is promoted.

A multifunctional electromagnetic launching device and method for wind tunnel model launching test belong to the technical field of model wind tunnel dynamic test. The problems of slow launching speed and poor repeatability in the prior art are solved. The technical points are as follows: the top surface of the hanger is fixedly connected with the test model, two orifices are opened at the bottom of the hanger, two electromagnets are installed in the two orifices, two electromagnet covers are installed at the bottom of the hanger corresponding to the two electromagnets, and a limit stop rail is arranged between the two orifices; a model head section, a model front magnetic section, a model middle section, a model rear magnetic section and a model tail section are sequentially spliced and fixed, installation grooves are arranged on the model front magnetic section and the model rear magnetic section, and a neodymium magnet with a counterbore is placed in the installation groove closest to the hanger at the top. The connection of the separated test model, the free launching of the launched object and the launching of the launched object with an initial speed are realized, the close contact between the launched objects is ensured, and the real separation process is simulated.

The application discloses a method for rotating propulsion of a propulsion body by alternately combining different-shaped coils, and relates to the technical field of electromagnetic launching. Compared with the previous rotating propulsion method of a magnetic resistance type propulsion body, the application solves the problems of the low efficiency of the existing magnetic resistance type coil propulsion system, the high heat generated by the coil during electrification, the complex design of the multi-stage magnetic resistance type coil, the need of a complex control system for accurately controlling the rotating torque and the propulsion speed generated by the coil, and the high cost of the research, manufacture and maintenance of the magnetic resistance type coil propulsion system; the alternately combined elliptical and circular coils provide smoother rotating motion, reduce energy loss, and improve the overall propulsion efficiency; meanwhile, the optimization of the coil design reduces the heat generated by the coil, and improves the stability and reliability of the system. The alternately combined elliptical and circular coils realize the rotating propulsion of the propulsion body, and provide possibility and reference value for the upgrading and optimization of the magnetic resistance type coil launching.

The application relates to a long-distance fire extinguishing vehicle, belonging to the technical field of fire fighting, and solves the problems that long-distance fire extinguishing is difficult to realize in the prior art and the flight distance of fire extinguishing bombs is difficult to control when the fire extinguishing bombs are launched. The long-distance fire extinguishing vehicle comprises a vehicle body, balance supporting legs, an electromagnetic launching system and fire extinguishing bombs. The electromagnetic launching system is fixedly arranged on the vehicle body. The electromagnetic launching system is used for launching the fire extinguishing bombs, and the fire extinguishing bombs are used for spraying fire extinguishing agents. The balance supporting legs are arranged below the vehicle body, and the lengths of the balance supporting legs are adjustable. The application realizes long-distance launching of the fire extinguishing bombs, and further realizes long-distance fire extinguishing.

The invention, which relates to the technical field of spaceflight electromagnetic emission, discloses a commercial spaceflight electromagnetic emission combined test verification platform comprising an emission track area and a storage and transformation center. The launching track area comprises a launching track subsystem, an electromagnetic propulsion subsystem and a comprehensive guarantee subsystem; the storage and transformation center comprises a superconducting zero-level booster subsystem and a control center. Aiming at the low-cost, high-frequency and customized launching requirements of a large-scale near-earth orbit constellation, the method fully considers the existing technical levels of a spaceflight electromagnetic launching system and a carrier rocket, and aims at improving the carrying capacity, shortening the launching period, reducing the launching cost and the like.

The utility model relates to rescue equipment technical field especially rescue electromagnet throws and throws the bullet, including the bullet body with the accommodation cavity, the rear part screw thread connection of bullet body has the tail cone with the taper contraction section, the outside of tail cone is provided with a plurality of tail vane, the rear end surface of tail vane and the rear end surface of tail cone between reserve the distance for avoiding electromagnetic transmitter coil end plate, still include: rescue assembly, set up in the front of bullet body, the taper contraction section is configured as when throwing and throwing the bullet flight and push rescue assembly acceleration, buffer assembly, set up in the inside of the accommodation cavity of bullet body, be configured as absorbing the launch impact, through this technical scheme, can through rescue assembly in the flight acceleration, while buffer assembly can effectively absorb the launch impact, protect inside rescue assembly, improve the rescue success rate.

The present invention relates to an interorbital launch assembly (1) for transporting cargo in outer space, comprising at least two electromagnetic launchers (2) for launching a cargo pod (3) and further comprising: - an electromagnetic gun (4) which in turn comprises a hollow launch tube (5) and a system of electromagnets (6) that are attached along the outside of the hollow launch tube, - an energy storage system (7), - a navigation and / or control system (8), - a communications system (9), - a docking system (10) for docking the cargo pod (3) to the electromagnetic gun (4), - a propulsion system (11), and - a launch calculation system (12).

The application provides a design method of a small electromagnetic railgun launcher system, and aims at solving the technical problems of electromagnetic rail launching technology, such as that the power supply is too large to be moved and installed at will, the working current is too large to cause serious rail ablation and affect the service life, and the speed of the armature out of the barrel is too large to require harsh material performance of the guide rail and the armature. The method is that the Ohm's law of the loop is written, the force analysis of the armature is carried out, the derivative of the expression of the electromotive force to the magnetic induction intensity is obtained, the derivative is equal to zero, and the minimum value of the electromotive force of the power supply is found through MATLAB drawing. The method discloses two specific modes of the electromagnetic rail launching system, and the specific configuration of the small electromagnetic rail weapon launching system is given by taking a light weapon as an example. The application enables people to configure the small electromagnetic rail launching system according to the demand, has higher dynamic efficiency, has lower requirement for the electromagnetic launching technology, has better realizability, and can avoid the rail ablation and improve the service life of the rail.

The electromagnetic launcher bullet supply mechanism comprises a base frame, a magazine and a bullet feeding mechanism, the base frame is of a hollow structure, the bottom of the base frame is open downwards, a notch is formed in the side wall of the rear end of the top of the base frame, a gun barrel hole is formed in the side wall of the front end of the top of the base frame, and guide rails are arranged on the two sides of an opening of the rear section of the top; the bullet feeding mechanism is arranged on the upper portion of the base frame and can move relative to the base frame and the magazine generating mechanism. The magazine is at least partially located in the base frame and comprises a magazine shell, a magazine base, a magazine support and a telescopic supporting piece. The magazine shell is of a hollow structure, the bottom is open downwards, the top is open upwards, notches are formed in the side walls of the two ends, and the opening edge of the front section with the top open upwards is provided with a blocking edge for preventing the rotor from disengaging. The magazine base is connected to the bottom of the magazine shell; the telescopic supporting piece is located on the lower portion of the sabot and used for driving the sabot and the rotor to ascend and descend. Smooth continuous ammunition feeding can be achieved, and the pre-firing position of the rotor at the starting end of the gun barrel can be flexibly adjusted according to needs.

The application belongs to the technical field of electromagnetic launching aircraft, and relates to a speed acquisition control method and system of an electromagnetic launching aircraft. The method comprises the following steps: acquiring a separation time and a separation speed of an aircraft in the process of accelerating from a launching platform of the electromagnetic launching aircraft to separation; analyzing an acting force of the moving aircraft, and establishing a dynamic equation of the aircraft; obtaining a real-time speed equation of the aircraft according to the separation time, the separation speed and the dynamic equation of the aircraft; acquiring real-time motion parameters of the aircraft, and calculating a real-time real speed of the aircraft according to the real-time speed equation of the aircraft; and starting an inertial navigation module and outputting the real-time motion parameters of the aircraft by a guidance module of the aircraft after receiving the separation time. The method can obtain the real-time real speed of the aircraft after separation.

The invention provides a modular power supply system for an ultra-high-speed long-primary bilateral linear induction motor, which belongs to the technical field of electromagnetic emission and comprises the ultra-high-speed long-primary bilateral linear induction motor, a traction converter and a connecting bus. The ultra-high-speed long-primary bilateral linear induction motor comprises a rotor and a long-primary track composed of a plurality of motor modules, and the motor modules are formed by series-parallel connection of different pole pairs according to the moving track of the rotor. The total primary voltage and the primary current of a pair of poles of each motor module are respectively equal to the working voltage and the working current of a switching device in the traction converter, and the number of parallel pole pairs of the motor modules corresponds to the number of parallel groups of the traction converter; the traction converters are arranged nearby the motor modules, and the motor modules and the traction converters are connected through connecting buses in a one-to-one correspondence mode. The method solves the problems that the bus voltage drop is large, a switching device in a traction converter is not matched and the efficiency of an overall electromagnetic emission system is low due to the fact that centralized power supply and segmented power supply are adopted in a traditional method.

The utility model discloses an electromagnetic transmitting device which comprises a track support, a coil assembly and a coil support, a transmitting track is arranged on the track support, the coil assembly at least comprises a pair of exciting coils which are connected in series or in parallel, the coil assembly is symmetrically distributed on the left side and the right side of the transmitting track, and the axis direction of the exciting coils is perpendicular to the direction of the transmitting track. An opening is formed in the launching track, one end of the opening at least extends to the position between the symmetrically-distributed coil sets, and a launcher can penetrate through the opening to reach the launching position on the launching track. The coil support is made of magnetic conductive materials, the two ends of the coil support penetrate into the axes of the exciting coils on the two sides of the launching track respectively, and the launcher is triggered from the launching position under the action of the coil assembly and the coil support.

The application discloses a mountain electromagnetic electromagnetic launching exploration seismic source device and an accelerating method thereof, which comprises a crawler walking device and a seismic source device, the crawler walking device comprises a crawler chassis, a hydraulic oil pump and an engine, a workbench is installed on the crawler chassis, the hydraulic oil pump for providing power for the crawler chassis and the engine for providing power for the hydraulic oil pump are installed at one end of the workbench, and the seismic source device for controlling impact speed by using an electromagnetic launching device is installed at the other end of the workbench. The application can generate high-energy seismic waves, the energy of the seismic waves can be adjusted, the operation efficiency is high, and the application is suitable for the mountain operation environment.

This invention belongs to the field of electromagnetic transmitters, and specifically relates to a launching method, armature assembly, and launching system. To address the technical problem in existing technologies that cannot deliver cylindrical or non-cylindrical loads with an outer diameter larger than the inner diameter of the coil, this invention proposes a launching method. When the load or launching chamber has a small mass and an irregular shape, such as a cylinder or a tube with an outer diameter larger than the inner diameter of the coil, an adapter is used to fix the load or launching chamber to an outer armature fitted outside the electromagnetic tube. When the load or launching chamber has a large mass, an inner-outer combined armature, consisting of the front ends of an inner armature and an outer armature fixedly connected, is used, and an adapter is used to fix the load or launching chamber to the outer armature. This invention also provides a corresponding launching system and armature assembly. By placing the load outside the electromagnetic tube, the shape and size of the load are not limited by the coil, thereby enabling the launching of loads of various shapes and sizes.

The present application relates to the technical field of protecting slag, in particular to a kind of electromagnetic catapulting dual-phase stainless steel special protecting slag, comprising the following raw materials: red mud, wollastonite, modified fluorite, borax, spodumene and blast furnace slag.The present application handles fluorite by yttrium oxide modification and forsterite coating process, effectively inhibits the release of harmful fluorine ion at high temperature, substantially reduces the erosion to refractory material;At the same time, forsterite coating enhances the stability of particles, improves the comprehensive use effect of protecting slag;In addition, modified fluorite helps to form a better lubricity slag film, reduces the slag and casting blank surface defects.

The application discloses a loading armature for electromagnetically launching a nonmetallic projectile and an electromagnetic launching device. The loading armature comprises a metal shell, and has an open loading chamber for loading the nonmetallic projectile. A through hole is formed in the closed end of the metal shell and is in communication with the loading chamber. The loading armature can be used for electromagnetically launching different types of nonmetallic projectiles. During the process of loading the nonmetallic projectile into the loading chamber through the open end of the metal shell, the through hole keeps the loading chamber in communication with the external environment, so that the loading chamber is not a closed chamber due to the nonmetallic projectile, and the internal air pressure of the closed chamber does not affect the loading of the nonmetallic projectile.