63 results about "Electromagnetic launch" patented technology

The present invention relates to a method for reconstructing the surface of an electromagnetic launch track, belonging to the technical field of electromagnetic track launch. The present invention uses the electromagnetic launch armature material and the track material as a friction pair, adopts a pin-on-disk friction device, and introduces an electric current to the friction pair in the pin-on-disk friction device; by changing at least one parameter among the magnitude of the electric current, the contact pressure of the friction pair, the friction speed, the friction time, and the arcing distance, the surface microstructure of the track material under the corresponding conditions is obtained; based on the surface microstructure obtained from the experiment, the surface structure of the electromagnetic launch track is reconstructed. The present invention realizes for the first time the accumulation of original data of topography reconstruction such as friction and wear on the surface of the track material, material transfer on the surface, and arc ablation on the surface, providing necessary conditions for the subsequent systematic reconstruction of the surface of the electromagnetic launch track. The method of the present invention is reasonable, the process is simple and controllable, the obtained data is true and reliable, and it is convenient for large-scale application.

The invention provides a low-altitude target netting system and method based on an electromagnetic ejection technology, and belongs to the field of aircraft control. The low-altitude target netting system comprises at least one aiming device, at least one electromagnetic launching device, at least one net bomb device and a control device, wherein each aiming device, each electromagnetic launching device and each net bomb device are respectively in communication connection with the control device; the control device is used for generating a control instruction for capturing a low-altitude target; the aiming device is used for identifying and tracking a low-altitude target to obtain position information of the low-altitude target, performing trajectory calculation in real time according to the position information, adjusting the posture of the electromagnetic launching device, and controlling launching of the electromagnetic launching device based on a control instruction; the electromagnetic launching device is used for launching the net bomb device through electromagnetic ejection; the net bomb device is used for capturing a low-altitude target. The capturing net is launched through the electromagnetic launching technology, the capturing range of the system can be effectively expanded, launching parameters can be adjusted in real time, and therefore the launching speed and the capturing rate can be effectively increased.

The invention belongs to the field of electromagnetic emission, and discloses an electromagnetic track emission system and method for friction coefficient full-period measurement. The electromagnetic track launching system comprises an electromagnetic track launching device, a pulse power system, a diagnosis system and a control system. According to the electromagnetic track launching system, full-launching-period measurement of the friction coefficient in an extreme electromagnetic environment can be achieved, and the system is used for monitoring the contact state between central tracks in each launching process and predicting the service life of a device; the full-emission period measurement of the local temperature of the guide rail can be realized; and full emission period measurement of contact pressure and contact resistance between the pivot rails is realized. According to the contact state between the guide rails in the launching process, the pretightening force of the guide rails or the size of the armature is adjusted, so that the service life of the guide rails is prolonged. The local temperature of the guide rail and the contact pressure between the pivot rails are monitored by utilizing the intrinsic physical characteristics of the Bragg grating, the reliability is high, the wavelength self-reference characteristic is realized, the absolute measurement can be realized, the temporal-spatial resolution is high, and the structure is compact.

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.

A tail-finned projectile for an electromagnetic launching device, the projectile being launchable by the electromagnetic launching device and comprising a projectile body (1) and a tail fin (2), wherein the projectile body (1) comprises a ferromagnetic material; and the tail fin (2) is connected to the projectile body (1), and the tail fin (2) comprises fin blades (21) and a fixing structure (22), the fixing structure (22) being located circumferentially outside the fin blades (21) and being connected to the fin blades (21), and the fixing structure (22) being engageable with the electromagnetic launching device before the projectile is launched by the electromagnetic launching device. The projectile allows the tail fin (2) to be held by a snap to prevent disengagement, such that the flight is more stable, and the projectile body (1) is less prone to rust, reducing energy consumption during firing.

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 present invention discloses a sensorless control method for a permanent magnet linear motor for launching in the full speed range, including: taking a double-three-phase permanent magnet linear synchronous motor for launching as the control object, establishing a control model in a three-phase stationary coordinate system and a control model in a VSD coordinate system; when the mover acceleration command a meets the conditions, the motor is started statically and operates in a low-speed open-loop manner; when the motor runs to a predetermined speed, it switches to an adaptive sensorless closed-loop control strategy, and the position and speed of the motor are estimated through an adaptive LQR-KF observer, ensuring that the motor system operates reliably and stably up to the maximum launch speed; when the motor runs to the maximum launch speed, it quickly enters a deceleration state, and a control strategy of position open-loop and current closed-loop is adopted to ensure that the motor brakes quickly and stably; it not only ensures the estimation accuracy of the position observer, but also provides guidance for the sensorless closed-loop control of the electromagnetic launch motor.

The invention belongs to the field of ultrahigh-speed electromagnetic launch design analysis, and particularly discloses a winding type launcher re-connected cannon structure and an electromagnetic performance analysis method of the winding type launcher re-connected cannon structure. The excitation source drives the coil structure and the emitter; the driving coil structure is connected with the excitation source and is used for generating electromagnetic force under the excitation of the excitation source so as to drive the emitter to emit; the emitter is a self-closing multilayer metal coil panel. According to the reconnection gun structure, the through-current capability of the emitter can be greatly enhanced, the electromagnetic thrust peak value generated by the reconnection gun structure and the emitting speed of the emitter are further improved, and the overall performance of the reconnection gun is improved.

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 present invention discloses a coil-type electromagnetic propulsion device, which relates to the field of electromagnetic launch technology. Compared with previous electromagnetic launch devices, the present invention solves the problem that the existing method of transferring the residual current of the drive coil does not consider the rational utilization and recycling of the residual energy of the coil; the conventional circuit shutdown method of the existing magnetic gun has a slow shutdown speed, which easily causes the projectile to be pulled back; and the residual energy in the coil is consumed as heat energy during shutdown, resulting in energy waste. The present invention achieves precise control of the coil through a multi-stage launch circuit, and replaces the thyristor with a high-power switch IGBT tube to achieve the shutdown of the launch circuit at any time. The resistor and diode of the original freewheeling circuit are replaced with a capacitor and a voltage-stabilizing diode, which realizes the recovery and utilization of the residual energy of the coil, avoiding the pull back of the projectile due to the untimely shutdown of the drive circuit and the waste of residual energy in the coil. The high-speed optocoupler is used to improve the anti-interference ability of the electrical signal, thereby achieving stable propulsion of the device.

The invention discloses an anesthesia bomb body structure for an electromagnetic launcher. The anesthesia bomb body structure can better achieve a short-time multi-target anesthesia function. Comprising a cylindrical bomb body (1), materials of the bomb body (1) can be electromagnetically launched, cavities are formed in the front end and the rear end of the bomb body (1) respectively, a partition plate is arranged between the cavities, a rubber cover (2) is fixed in the cavity in the front end of the bomb body (1) in a sealed mode, a liquid pushing device (6) is arranged in the cavity in the rear end of the bomb body (1) in a sliding fit mode, and an anesthetic storage bin is arranged between the partition plate and the liquid pushing device (6). An injection needle body (4) is fixed to the axis position of the liquid pusher (6) in the axial direction, the injection needle body (4) is of a hollow pipe structure, a plurality of liquid injection holes are formed in the surface of the injection needle body (4), a needle head is arranged at the front end of the injection needle body (4), a limiting ring (7) is installed in a cavity in the rear end of the elastic body (1) in the circumferential direction, the material of the limiting ring (7) can be compressed, and a ring groove is correspondingly formed in the surface of the liquid pusher (6).

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.

The utility model discloses a multifunctional anti-riot fork which comprises a main body and a U-shaped rejection piece connected to the head of the main body, and further comprises an electromagnetic net capturing module arranged on the head of the main body. The electromagnetic net capturing module comprises an electromagnetic launch canister, an induction coil, a net bomb module, a capacitor unit, a power supply and a high-voltage unit; and the electromagnetic launch canister is mounted at the end part of the main body. On the basis of the anti-explosion forks, the electromagnetic net capturing function is further achieved, capturing personnel can launch the capturing net through the anti-explosion forks, it is helpful for moving chasing in the escape process and controlling in the confrontation process, the successfully launched capturing net can limit the activity of a target, the capturing difficulty of the capturing personnel is reduced, and the capturing efficiency is improved. And the injury possibility of capturing personnel is reduced. In addition, the arresting net is further provided with the accent light, the target can be dazzled through the accent light to stop moving, and the arresting net can be conveniently and accurately launched and the target can be conveniently and accurately controlled.

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 present invention provides a combined superconducting vacuum high-speed electromagnetic launch device, which relates to the technical field of electromagnetic launch; it comprises a combined launch part, wherein the combined launch part is provided in a row, and the combined launch parts in the row are connected by bolts; a vacuum suction part is installed on the bottom of the combined launch part; a launch mover part is placed in the vacuum suction part; a drag reduction limiter is installed on the launch mover part; a switch control part is installed on the top of the combined launch part, and a compressed air release part is used in conjunction with the switch control part. The compressed air release part can quickly release high-pressure gas, compensate for the air pressure suction caused by negative pressure, reduce the resistance of vacuum launch, and increase the magnetic launch speed; it solves the problem that the current electromagnetic launch device is inconvenient to assemble and use, and when the door is opened for vacuum launch, external air pressure rushes into the launch tube, affecting the speed and stability of the projectile.

The invention discloses an electromagnetic emission system, which comprises a control module, an acquisition module and a multi-stage electromagnetic emission module, the control module is electrically connected with the acquisition module and each electromagnetic emission module; the acquisition module is used for acquiring a feature signal of a feature target in real time; and the control module is used for receiving the characteristic signal and determining the starting stage number of the electromagnetic emission module according to the characteristic signal so as to control the started electromagnetic emission module to execute the emission action. According to the system, the control module is utilized to accurately determine the starting stage number of the electromagnetic emission module according to the characteristic signal, it is guaranteed that the electromagnetic emission module can accurately emit the characteristic target, accurate shooting is achieved, and the hit rate is increased.

The utility model discloses a vehicle-mounted multi-type electromagnetic ejection device, which relates to the technical field of vehicle-mounted unmanned aerial vehicles and comprises a vehicle head and a carriage, an energy storage unit is arranged at the bottom of one end of the carriage, and a charger is arranged at the top of the energy storage unit; a driving system is arranged on one side of the energy storage unit, a control unit is arranged in the driving system, and a switching unit is arranged on one side of the driving system; a hangar is arranged at the other end of the compartment, and an adjustable electromagnetic ejection unit is arranged on one side of the hangar. According to the vehicle-mounted multi-type electromagnetic catapult, only one set of power supply equipment and one set of driving system need to be adopted, catapulting tasks of unmanned aerial vehicles of various types can be adapted at the same time, high-frequency continuous launching of the unmanned aerial vehicles of different types is achieved, the adaptive capacity of the vehicle-mounted multi-type electromagnetic catapulting device is wider, and the launching flexibility and efficiency of the multi-type unmanned aerial vehicles are improved; compared with multiple sets of electromagnetic launching units launched by a single unmanned aerial vehicle, the continuous launching capability of multiple types of unmanned aerial vehicles is improved, and the manufacturing and maintenance cost of the device is saved.

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 discloses an anchor type emission type surface sediment sampling device, and relates to the technical field of sediment sampling, the anchor type emission type surface sediment sampling device comprises an anchor type sediment collecting device, a remote electromagnetic emission device, a portable telescopic recovery device and an intelligent sampling control system, the anchor type sediment collecting device comprises an anchor rod as a main body supporting structure, a camera and a motor module are fixedly installed on the top of the base. The anchor type device adopts the design of a hinge type anchor fluke and a permeable collecting net, the stress angle is optimized through the front end of a shovel-shaped sheet, the shovel-shaped sheet is accurately embedded into surface sediment (the depth is smaller than or equal to 20 cm), and low-disturbance sampling and safe recycling are achieved in combination with a sliding type air cylinder and an inflation floating module; the remote electromagnetic launching device improves the projection speed (greater than or equal to 25m / s) and the sub-meter precision through a multi-stage acceleration electromagnetic coil and intelligent angle adjustment; the intelligent system integrates a water sensor, a fuzzy-PID algorithm and a buoy sonar module, dynamically regulates and controls the sampling process and feeds back data in real time.

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.

This invention provides an electromagnetic launching device and method based on zero-crossing commutation of superconducting constant magnetic flux induced current. The device includes a drive coil wound with superconducting wire or strip, with multiple drive coils forming a launching channel; a projectile coil wound with superconducting bulk or wire; a superconducting DC power supply providing initial current to the drive coil and projectile coil; and an energy-releasing commutation circuit that utilizes an intermediate capacitor to recover and store the magnetic energy of the superconducting drive coil. Based on this device, by injecting currents of a preset ratio into the superconducting drive coil and the superconducting projectile coil respectively, the current in the superconducting drive coil automatically decays to zero when the superconducting projectile coil moves to the axial center of the superconducting drive coil. This avoids the superconducting drive coil exerting a reverse pulling force on the superconducting projectile coil, ensuring continuous acceleration and launching of the projectile coil. This invention solves the problem of rapid, synchronous, and precise commutation of the launching current in traditional coils.