33 results about "Electromagnetic propulsion" patented technology

The utility model discloses a vehicle-mounted electromagnetic propulsion remote fire extinguishing device, which belongs to the technical field of fire fighting equipment and comprises a vehicle body with a chassis, and a plurality of support legs are distributed on the outer edge of the chassis; the supporting leg comprises a horizontal telescopic part and a vertical telescopic part, the horizontal telescopic part comprises an outer sliding barrel and an inner sliding barrel, and the inner sliding barrel is connected with a first driving assembly for driving the inner sliding barrel to move; the vertical telescopic part comprises a bottom foot, a ball head rotationally connected with the bottom foot is arranged on the bottom foot, the ball head is connected with a second driving assembly for driving the ball head to move, and the second driving assembly is fixed to the inner sliding barrel; the electromagnetic emission assembly, the pulse power supply and the generator are all arranged on the chassis; the pulse power supply is connected with the electromagnetic emission assembly. The generator is connected with the pulse power supply and the electromagnetic emission assembly. The chassis can bear the electromagnetic emission assembly, the pulse power supply and the generator, the pulse power supply and the generator guarantee that the electromagnetic emission assembly provides electric energy, the supporting legs can provide supporting force for the chassis, and recoil force can be stably borne.

This invention relates to the field of high-speed magnetic levitation transportation technology and discloses a test device for a ground module of a magnetic levitation electromagnetic propulsion system. The device includes a superconducting magnet, a ground test bench, a frequency converter, a through-core transformer, a high-voltage generator, connecting leads, dry-type terminals, and two power supply cables for the tested module. The tested ground module and the superconducting magnet are arranged opposite each other on the ground test bench. One end of the power supply cable for the tested module is equipped with a dry-type terminal, and the other end is connected to the lead-out end of the propulsion coil of the tested ground module. The dry-type terminal of one power supply cable passes through the through-core transformer and is connected to the dry-type terminal of the other power supply cable through a connector to form a conductive loop. The connection point of the dry-type terminal is connected to the high-voltage generator through connecting leads. The frequency converter is connected to one vertical side of the through-core transformer. The shielding shell of the tested ground module and the shielding layer of the tested power supply cables are grounded. This allows for multi-field coupling durability testing.

This invention provides a weldable, lightweight, long-life arc-initiating electrode and welding method, including an anode head, a cathode head, an anode column, and a cathode column. The anode head and cathode head are made of single or composite metal conductor materials resistant to arc erosion; the anode column and cathode column are also made of single or composite metal conductor materials. The current path is as follows: the arc igniter is connected to both ends of the track in the muzzle region of a high-speed electromagnetic propulsion device, powered by an external power source. Current flows through the track and armature path of the high-speed electromagnetic propulsion device. The armature, under electromagnetic force, accelerates and slides from the muzzle towards the muzzle. When the armature exits the muzzle, it disengages from the track. Simultaneously, the metal or plasma medium in the gap between the bypass electrodes of the arc igniter induces gap breakdown discharge, achieving arc initiation. This invention meets requirements for conductivity and high tensile strength.

The present application relates to the technical field of smelting furnace, and provides a melting and preserving integrated furnace for non-ferrous metal recycling, which is characterized by comprising a furnace body, an electromagnetic rolling stirring device and an electromagnetic propeller, the furnace body has a feeding cavity, a cold chamber and a hot chamber which are sequentially communicated, a spoiler wall is arranged between the feeding cavity and the cold chamber, the lower part of the spoiler wall is provided with a liquid passage, the electromagnetic rolling stirring device is arranged at the lower part outside the feeding cavity, the electromagnetic rolling stirring device is configured to drive part of the molten liquid in the feeding cavity to enter the cold chamber through the liquid passage, and drive part of the molten liquid in the feeding cavity to impact the spoiler wall and roll downward, so as to stir the raw materials by means of the solution, and the electromagnetic propeller is arranged on the outer bottom wall of the furnace body. The melting and preserving integrated furnace provided by the present application realizes the circulation of the molten liquid in the furnace cavity of the smelting furnace through the cooperation of the electromagnetic rolling stirring device and the electromagnetic propeller, and solves the technical problem that the existing technology adopts the graphite rotor to circulate the cold and hot molten liquid, which is easy to mix impurities.

The present subject matter provides an electromagnetic propulsion system comprising: at least one electromagnetic thrustor configured to intake air, ionize the air to produce ionized air, pass the ionized air through at least one electromagnetic field and emit the ionized air in a first direction, to reach acceleration, thereby creating a thrust force in a second direction that is opposite to the first direction, and an electrostatic repulser surrounding the at least one electromagnetic field, configured to pass at least one inducing element therethrough and control a velocity and acceleration rate of the at least one inducing element, wherein a velocity and acceleration rate of the ionized air through the at least one electromagnetic thrustor is induced by the velocity and acceleration rate of the at least one inducing element in the electrostatic repulser. Additional embodiments of the electromagnetic propulsion system are disclosed herein.

This invention discloses a contactless power supply RGV (Automated Guided Vehicle) for unmanned warehousing, relating to the technical field of intelligent warehousing and logistics equipment. The invention includes a cargo-carrying structure and a power supply and energy storage structure. The power supply and energy storage structure is charged using a weakly coupled magnetic resonance wireless power transmission system. The moving power system of the cargo-carrying structure includes an energy storage and release structure and an electromagnetic propulsion structure. The energy storage and release structure is used for braking energy storage and for releasing kinetic energy during startup. The electromagnetic propulsion structure is magnetically connected to an external electromagnetic propulsion component and drives the cargo-carrying structure to move. The power supply and energy storage structure uses a weakly coupled magnetic resonance wireless power transmission system for charging, eliminating the need for traditional plug-in interfaces or contact points, significantly reducing power supply failure rates and maintenance frequency. The power supply and energy storage structure works in conjunction with the cargo-carrying structure to continuously provide stable power during vehicle operation, thereby improving the continuous operation capability of the RGV in unmanned warehousing environments.

This application relates to the field of electromagnetic propulsion technology, specifically disclosing a double-sided long stator linear drive system, including multiple subsystems and a main controller. Each subsystem includes an equal number of linear motor stator segments, six-phase switches, position detection devices, a common AC bus for the subsystem, and a subsystem control bus. The linear motor stator segments are connected to the common AC bus of the subsystem through corresponding six-phase switches, and then connected to the system common AC bus formed by the subsystem bus interfaces, which is connected to a six-phase converter composed of three-phase converters distributed in each subsystem. Each position detection device is connected to the system control bus through the subsystem control bus, and then to the main controller. The main controller controls the switching of each linear motor stator segment according to the installation order of the subsystems and the running position of the linear motor mover measured by the position detection devices. The subsystems can be randomly ordered and assembled without affecting the system operation, exhibiting good mobility.

The application relates to the technical field of aerospace space electromagnetic propulsion, in particular to a high-frequency rotating magnetic field transient magnetic field configuration measuring system and method, the system comprises a high-frequency rotating magnetic field, a three-axis inductive magnetic probe, a signal transmission bus and an oscilloscope, wherein: a plurality of three-axis inductive magnetic probe arrays are uniformly distributed in the high-frequency rotating magnetic field to be measured; one end of the signal transmission bus is fixed at the boundary of the high-frequency rotating magnetic field region to be measured, and the other end is connected with the oscilloscope; the signal transmission line of each three-axis inductive magnetic probe is connected with the signal transmission bus; the oscilloscope is internally provided with a data processing system, which is used for collecting inductive magnetic field signals and processing the same, and displays the configuration and dynamic change of the high-frequency rotating magnetic field to be measured in real time. The application is suitable for transient rotating magnetic field configuration detection with a frequency of 0-1 MHz, and the known inductive magnetic probe, the oscilloscope and other instruments are combined skillfully to have the ability of high-frequency magnetic field measurement.

This invention provides a low-thrust pulsation multi-stage reconnected electromagnetic propulsion device and its power supply control method, including two rows of stator coils, a mover plate embedded with multiple metal plates, a mover mechanism, and a stator power supply device; the two rows of stator coils are fixed in parallel on a stationary base, with each pair of stator coils arranged coaxially facing each other; the metal plates are embedded in the mover plate, which is fixed to the mover mechanism, located between and parallel to the two rows of stator coils, with the center of the metal plate and the axis of the two rows of stator coils on the same plane; the load is connected to the mover mechanism through a connecting mechanism; each row of stator coils is evenly spaced along the propulsion direction; multiple metal plates are evenly spaced along the propulsion direction on the mover plate; a pulse current is supplied to the stator coils through the stator power supply device, and the metal plates are subjected to a controllable and powerful thrust, causing the mover mechanism to move at high speed in the direction of the force. This electromagnetic propulsion device is suitable for propelling high-speed motion of moving bodies within different speed ranges.

The invention relates to a non-contact electromagnetically-driven hydrodynamic noise test system, which comprises a pressure-resistant still water cabin and a non-contact dragging module, the non-contact dragging module comprises a model bearing frame, a magnetic levitation stator unit and an electromagnetic propulsion unit, the magnetic levitation stator unit enables the model bearing frame to suspend on a sinking groove rail, and the electromagnetic propulsion unit enables the model bearing frame to suspend on the sinking groove rail; the electromagnetic propulsion unit pushes the model bearing frame to move through electromagnetic force. The magnetic levitation stator unit is provided with two groups of floater permanent magnet arrays; and a south-north pole connecting line of the floater permanent magnet array is inclined relative to the horizontal plane, so that homopolar repulsive force is decomposed into vertical suspension component force and horizontal guide component force. Non-contact suspension linear motion of a model, transverse disturbance reduction through grooved rail limiting and uniform non-contact electromagnetic propulsion are realized through electromagnetic driving and magnetic suspension in the pressure-resistant still water cabin, mechanical friction noise is thoroughly eliminated, a flow field environment is remarkably optimized, a high-precision condition with extremely low background noise is provided for hydrodynamic force and underwater acoustic performance test of an underwater vehicle, and the test efficiency is improved. And the non-disturbance test in the completely static water body is realized.

The invention provides an aircraft using a Gaussian electromagnetic propulsion device for air compression, the center of a saucer-shaped aircraft is an olive-shaped control center, an oxyhydrogen energy storage tank and an oxyhydrogen battery device are assembled in the olive-shaped aircraft life control center, and an aircraft body provides electric energy as required through an oxyhydrogen energy storage battery; two aircraft compressor blades are annularly stacked together in a big-end-up mode, a pair of electromagnetic propulsion coil sets is distributed on the edge of each of the upper compressor blade and the lower compressor blade of the aircraft, each pair of electromagnetic propulsion coil sets corresponds to a set of annular neodymium magnet guide rail, and the two sides of each guide rail are equally divided according to the sector radian of a circle. An inner arc and an outer arc of each equally-divided radian are each provided with a neodymium magnet, the neodymium magnets and electromagnetic coils matched with the neodymium magnets form an electromagnetic propeller, an electromagnetic propelling coil set on a gas compressor blade wheel enables two gas compressor blades to rotate oppositely after being powered on reversely, and power generation coils are additionally distributed on the outer edge of the large gas compressor blade wheel. Neodymium magnets distributed in an array shape are arranged at the positions, corresponding to the coils on the large compressor blade wheel, outside the aircraft body to form a generator device, and electric energy is generated along with rotation of the large compressor blade wheel. Three exhaust ports perpendicular to the exhaust direction are formed in the bottom of an annular pipe below the gas compressor, substances treated by the high-energy ionization accelerator are exhausted out of the aircraft through the exhaust ports, an exhaust port is also formed in the side face of the aircraft, and a direction adjuster is arranged in the aircraft. The attitude and direction of the aircraft are controlled through an electric hydraulic control valve, a direction regulator and a high-energy ionization acceleration device.

A sensorless velocity measurement and positioning method and system for a linear motor in a suspended electromagnetic propulsion system is disclosed. The positioning method includes: observing unmodeled disturbances in a coordinate system using a designed disturbance observer to obtain the observed disturbance values ​​in the coordinate system; converting the observed disturbance values ​​in the coordinate system into a coordinate system and inputting them into an improved adaptive superspiral sliding mode back EMF observer to obtain the back EMF signal in the coordinate system, which is then input into a third-order orthogonal normalized phase-locked loop to obtain the position and velocity of the superconducting permanent magnet synchronous linear motor; and designing an extended state observer to input the position and velocity of the superconducting permanent magnet synchronous linear motor obtained from the third-order orthogonal normalized phase-locked loop into the extended state observer to obtain the optimized position of the superconducting permanent magnet synchronous linear motor. This invention can operate effectively in a linear motor of a suspended electromagnetic propulsion system and has good sensorless control performance.

The invention discloses an electromagnetic propulsion system for spacecraft, utilizing multiple ring structures with helically arranged pathways containing magnetic ball bearings. These bearings are accelerated by electromagnetic coils, generating thrust via the conservation of momentum. The system comprises dual-function rings, designated for forward and reverse thrust, enabling precise control over spacecraft acceleration and deceleration. This non-chemical propulsion method offers a sustainable alternative by eliminating the need for expendable propellants. The modular and scalable design allows for varying thrust levels, making it adaptable for diverse mission profiles, from small satellites to large exploration vehicles. This innovative approach enhances spacecraft maneuverability, efficiency, and operational lifespan.

The application provides a conversion device for converting lightning electric energy into kinetic energy, and relates to the technical field of electric energy conversion devices.The device comprises an artificial lightning attraction system, which is used for inducing lightning in a thunderstorm environment and leading out the generated lightning current; a pulse energy storage and conversion system, which is connected with the artificial lightning attraction system, is used for receiving the lightning current led out by the artificial lightning attraction system and storing energy, and outputs the energy after pulse shaping and power amplification as pulse electric energy; and an electromagnetic track launching system, which is connected with the pulse energy storage and conversion system, is used for receiving the pulse electric energy for pulse discharge to generate an electromagnetic field to provide electromagnetic propulsion force, so as to launch a load.The application solves the problems that the existing technology causes the loss of artificial lightning attraction energy directly led into the ground, and the electromagnetic track launching device highly depends on a conventional power grid, thereby causing the great power supply pressure of the power grid.

The present application relates to the technical field of spacecraft electromagnetic propulsion, and particularly relates to an electromagnetic propulsion device for polar orbit satellite and a propulsion control method, aiming at solving the technical problem of short service life of artificial satellite in the prior art. The electromagnetic propulsion device comprises a power supply assembly and a propulsion assembly; the power supply assembly is electrically connected with the propulsion assembly, and the two form a circuit loop; the propulsion assembly is used for shielding current passing through itself and is used for connecting with a spacecraft. The electromagnetic propulsion device does not need to use working medium such as liquid, gas and plasma, and obtains propulsive force through cooperation of the earth space magnetic field and the current, thereby reducing the cost of the propulsion device and greatly improving the service life of the on-orbit satellite.

The invention discloses a vehicle-mounted rotor position and suspension gap detection system and method for magnetic suspension electromagnetic propulsion, and belongs to the technical field of magnetic suspension electromagnetic propulsion. The system comprises a triangular or trapezoidal grid hole shading plate, a laser detection device and a controller; the laser detection device comprises a plurality of laser generators and a plurality of laser detectors, and each laser generator and each laser detector pair are symmetrically arranged on the two sides of the triangular or trapezoidal grid hole shading plate with the triangular or trapezoidal grid hole shading plate as the center; in the process that the triangular or trapezoidal grid hole shading plate moves along with the vehicle-mounted rotor of the magnetic suspension electromagnetic propulsion system, the laser generator emits laser, the laser detector converts received laser pulse signals into electric signals, and the number and the duty ratio of the laser pulse signals are calculated and uploaded to the controller. According to the invention, high-reliability real-time position and suspension gap information of the vehicle-mounted rotor can be obtained, and stable electromagnetic thrust generated by the magnetic suspension electromagnetic propulsion system is ensured.

The application discloses a flexible closed-loop transmission electromagnetic propulsion system and a control method, wherein the system forms a flexible closed-loop driving chain with tension self-adaption through front and rear traction ropes and a traction drum, and four actions of acceleration propulsion, rapid braking, return and return braking of a traction vehicle are uniformly controlled by using a traction motor, so that the problems of multi-motor synchronization error and energy internal consumption are avoided. In cooperation with a hydraulic tensioning mechanism and a modular light rail, high-precision position and speed control and equipment safety protection are realized. In the energy storage aspect, a flywheel inertia or a super capacitor energy storage can be selected according to the scene, and five working modes are seamlessly switched and energy is fed back in combination with a four-quadrant converter. The application has the advantages of clear control logic, reliable operation, convenient transportation and installation and small maintenance quantity.

The invention discloses an air-breathing type electromagnetic propulsion device for an ultra-low orbit satellite, and relates to the technical field of electromagnetic acceleration propulsion. In the device, an air-breathing type gas collecting assembly collects and compresses mixed gas of an ultra-low orbit; the radio frequency plasma ionization assembly ionizes the composite working medium gas to form plasma; the plasma heating acceleration assembly injects energy of a high-power radio frequency power supply into plasma through electromagnetic wave coupling, and heating and acceleration of the plasma are achieved. The vector thrust control assembly restrains and controls the heated and accelerated plasma to form a directional ion beam; the electric propulsion main control assembly collects key state parameters of the air suction type gas collection assembly, the radio frequency plasma ionization assembly, the plasma heating acceleration assembly and the vector thrust control assembly through sensors, and closed-loop control is conducted on the four assemblies according to received or preset control instructions and in combination with the key state parameters. Efficient ionization can be achieved under low working medium pressure, and wide-load efficient and stable operation can be achieved.

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 the technical field of smelting furnaces, and provides an electromagnetic rolling type smelting and protection integrated furnace for regenerating non-ferrous metals, which is characterized by comprising a furnace body, an electromagnetic rolling stirrer and an electromagnetic propeller, the furnace body is provided with a feeding cavity, a cold chamber and a hot chamber which are communicated in sequence, a turbulent flow wall is arranged between the feeding cavity and the cold chamber, and a liquid passing opening is formed in the lower part of the turbulent flow wall; the electromagnetic turnup stirrer is arranged on the lower portion of the outer side of the feeding cavity, the electromagnetic turnup stirrer is configured to drive part of melt in the feeding cavity to enter the cold chamber through the liquid passing opening and drive part of melt in the feeding cavity to impact the turbulent flow wall and turn over downwards so as to stir the fed raw materials with the help of the solution, and the electromagnetic propeller is arranged on the outer bottom wall of the furnace body. According to the melting and protection integrated furnace provided by the invention, through the cooperation of the electromagnetic rolling stirrer and the electromagnetic propeller, a large circulation is formed when the melt runs in the furnace cavity of the melting furnace, and the technical problem that in the prior art, a graphite rotor is adopted for conducting cold and hot melt circulation, and materials are easily doped is solved.

The application relates to a magnetic suspension electromagnetic propulsion and air compression propulsion composite carrier system, which comprises a carrier module, a superconducting magnetic suspension electromagnetic propulsion module, an air compression propulsion module, a vacuum pipeline module, an electronic control module, a blocking module and a slide rail; the slide rail is arranged in the vacuum pipeline module; the superconducting magnetic suspension electromagnetic propulsion module is used for floating the carrier module, making the carrier module leave the surface of the slide rail and obtain a certain speed; air internal energy is converted into kinetic energy of the carrier module through the air compression propulsion module; the electronic control module is used for detecting the moving speed of the carrier module, real-time regulating and controlling electromagnetic linear propulsion power, ensuring effective coupling of the air compression propulsion and the electromagnetic linear propulsion, and making the carrier module obtain a predetermined acceleration; the blocking module is arranged at the pipeline outlet of the vacuum pipeline module. The application realizes composite application of the magnetic suspension electromagnetic propulsion and the air compression propulsion.

This invention relates to a non-contact electromagnetically driven hydrodynamic noise testing system, comprising a pressure-resistant still water chamber and a non-contact towing module. The non-contact towing module includes a model carrier, a magnetic levitation stator unit, and an electromagnetic propulsion unit. The magnetic levitation stator unit suspends the model carrier on the trough rail, and the electromagnetic propulsion unit moves the model carrier via electromagnetic force. The magnetic levitation stator unit has two sets of float permanent magnet arrays; the line connecting the north and south poles of the float permanent magnet arrays is inclined relative to the horizontal plane, so that the repulsive force of like poles is decomposed into a vertical levitation component and a horizontal guiding component. This invention achieves non-contact levitation linear motion of the model through a pressure-resistant still water chamber using electromagnetic drive and magnetic levitation. The trough rail limit reduces lateral disturbance, and the electromagnetic propulsion is uniform and non-contact, completely eliminating mechanical friction noise, significantly optimizing the flow field environment, providing high-precision conditions with extremely low background noise for testing the hydrodynamic and underwater acoustic performance of underwater vehicles, and realizing undisturbed testing in completely still water.

The present invention discloses propulsion system operating exclusively in electromagnetic domain. Only electromagnetic field and direct electric current are used to generate propulsion force. In exemplary embodiment two switchable electromagnets, one to generate electromagnetic field, the other to generate electromagnetic force are used. To disable electromagnetic reaction force on electromagnetic field generator, streams of independent but synchronized direct current pulses passing through two electromagnets are organized in the way that first electromagnet is always carrying current when magnetic field generated by second electromagnet reaches it, thus generating Laplace force, whereas, second electromagnet is never carrying current (open circuit) when magnetic field generated by the first electromagnet reaches it, which means, no Laplace reaction force ever occurs on second electromagnet. The system therefore does not depend on the emission of matter. Only electric current is needed.

The invention provides a preparation method of high-fatigue-resistance, high-toughness and high-temperature-resistance dispersion-strengthened aluminum alloy, and relates to the technical field of aluminum alloy preparation. The preparation method comprises the following steps: uniformly mixing aluminum alloy powder with a certain amount of polytetrafluoroethylene-PTFE turbid liquid, drying to obtain PTFE coated aluminum alloy powder, carrying out cold isostatic pressing forming and vacuum or nitrogen sintering densification on the composite powder to prepare an aluminum-based composite material blank, and preparing the high-fatigue-resistance high-toughness high-temperature-resistant aluminum-based composite material by adopting a thermal deformation process. According to the method, an aluminum oxide film on the surface of aluminum powder is effectively broken and removed in the sintering process of aluminum alloy powder by introducing PTFE, meanwhile, a ternary nanometer dispersion strengthening phase is formed in situ, and fine grain strengthening and precipitation strengthening mechanisms are combined, so that the aluminum-based composite material has excellent mechanical performance, fatigue resistance and high-temperature performance. The method is short in technological process and easy for industrial large-scale production, and has wide application prospects in the fields of aerospace, rail transit, electromagnetic propulsion equipment and the like.

The invention relates to a projectile velocity prediction method and system for an electromagnetic thruster, and the method comprises the steps: S1, building a turn number relation of a drive coil corresponding to the projectile velocity by taking the acceleration, obtained on the axis of the drive coil, of a projectile in a solenoid as a reference; s2, correcting the turn number relation of the driving coil corresponding to the projectile velocity; and S3, based on the turn number relation of the drive coil corresponding to the corrected projectile speed, obtaining a relation curve of the projectile speed and time, and predicting the motion speed of the projectile under different matching relations according to the relation curve. The matching relation between the number of turns of the driving coil and the motion speed of the projectile is constructed, so that the projectile can ensure high kinetic energy and high efficiency in the acceleration process of the driving coil of each stage of the solenoid, and the acceleration effect of each stage can be predicted.

The utility model discloses a chemical fuel multi-stage propulsion electromagnetic mixed ejection device which comprises a base, a movable seat, an electromagnetic propulsion assembly and a steam propulsion assembly. The moving seat is slidably connected to the base in the length direction of the base, the electromagnetic propelling assembly comprises a first stator and a second stator which are fixedly installed on the side, in the thickness direction, of the base, and a mover fixedly installed on the side, close to the base, of the moving seat, and the mover is located between the first stator and the second stator; the steam propelling assembly is fixedly installed on the side, away from the base, of the movable base. The mover coil in a power-on state interacts with the multiple first magnetic parts and the multiple second magnetic parts respectively, and the steam propelling assembly jointly drives the movable base to move in the length direction of the base, so that the steam propelling assembly and the electromagnetic propelling assembly can be designed in a miniaturized mode; the chemical fuel multi-stage propulsion electromagnetic mixed ejection device has the advantages of being compact in structure and small in equipment size.

The application discloses a kind of active arc excitation type linear track electromagnetic propulsion device, it is related to electromagnetic propulsion field, and the device mainly includes track pair, armature projectile, pulse power supply and active arc device;By configuring active arc device with sharp contact in the inside of track, and according to the set order, main pulse power supply is turned on, active arc device is excited, so that closed loop is formed between armature projectile and track pair by arc, armature projectile is propelled by electromagnetic force in the magnetic field generated by electrified track, and keeps non-contact suspension state with track in the whole acceleration process.The application replaces traditional physical contact with controllable arc, fundamentally eliminates the friction loss between armature projectile and track, significantly improves track life, propulsion efficiency and motion controllability, realizes efficient, low-loss electric energy-kinetic energy conversion.

Disclosed in the present invention is an electromagnetic propulsion system, comprising: a launch coil assembly and a magazine. A through-going coil cavity is formed at the center of the launch coil assembly; the magazine is used for accommodating projectiles; the projectiles are ferromagnetic; the magazine is adjacent to the launch coil assembly; an opening is formed at the side of the magazine close to the launch coil assembly; one end of the coil cavity is communicated with the interior of the magazine by means of the opening; each projectile has a ready position in the magazine; when the projectile is in the ready position in the magazine, the projectile is coaxial with the coil cavity, and a magnetic field generated by the launch coil assembly imparts an initial velocity to the stationary projectile in the ready position, such that the projectile passes through the opening and enters the coil cavity to be launched.

The present invention relates to a new form of air, land, underwater or space propulsion achieved by the use of suitable electromagnetic interactions. By using capacitors formed by symmetric or asymmetric conductors (1) and (2), surrounded by a dielectric (3), subjected to asymmetric voltage pulses or with asymmetric electric field derivative we obtain directional propulsion forces. This is possible due to a new electromagnetic propulsion mechanism that uses conservation of total momentum where the sum of the mechanical momentum with the electric field momentum should always be conserved resulting in a constant and zero total sum of the two components, where the change in electric field momentum will generate a corresponding change in the mechanical momentum of the capacitor thus generating propulsion forces where the inertia forces are attenuated and can generate force fields.