10 results about "Electromagnetic launch" patented technology

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.

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 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 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 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 an online speed measurement feedback control method and system for an electromagnetic launching aircraft. The method comprises the following steps: acquiring electromagnetic launcher parameters and aircraft parameters, constructing an output speed equation of the electromagnetic launcher, constructing an output speed equation of the aircraft, and constructing a speed state equation of the electromagnetic launching aircraft; obtaining a speed observation vector according to the output speed equation of the electromagnetic launcher and the output speed equation of the aircraft; obtaining a speed fusion equation according to the speed observation vector and the speed state equation of the electromagnetic launching aircraft, constructing a Kalman filter, taking the speed observation vector as a filter observation, estimating a speed error of the electromagnetic launching aircraft, and performing speed feedback according to the estimation result. The method can meet the needs of different launching speeds of various aircrafts and improve the control precision.

This invention discloses a method for optimizing the trajectory of an electromagnetic launch rocket, comprising: S100 determining multiple initial trajectory inclination angles; S102 trajectory calculation; S104 checking if the orbital insertion conditions are met (if yes, proceed to S106; otherwise, proceed to S118); S106 checking if the overload constraint conditions are met (if yes, proceed to S108; otherwise, proceed to S118); S108 calculating multiple objective function output values; S110 determining if the difference between two adjacent calculated objective function output values ​​is less than a predetermined difference (if yes, proceed to S112); S112 optimizing the trajectory of the rocket corresponding to the maximum orbital payload mass. Initially, determine the initial trajectory inclination angle. Check if the maximum dynamic pressure is not greater than the predetermined dynamic pressure and if the product of the maximum dynamic pressure and the angle of attack is not greater than the predetermined product. If yes, proceed to S114; otherwise, proceed to S116. In S114, determine the initial trajectory inclination angle corresponding to the maximum orbital payload mass as the optimal initial launch inclination angle. In S116, for the remaining initial trajectory inclination angles, perform the same checks as in S112 until the check result is yes, and determine the initial trajectory inclination angle corresponding to the check result as the optimal initial launch inclination angle. In S118, adjust other rocket-related parameters and return to S102.

The application discloses an electromagnetic launching device and a launching method based on a three-rail symmetrical layout and a regular hexagonal armature. The device comprises a launching rail composed of three rails symmetrically distributed in a regular triangle around a center axis of the launching channel, and an armature in sliding cooperation with the three rails. The outer periphery of the armature is composed of three planes and three circular arc surfaces alternately distributed to form a regular hexagonal structure, and the three planes of the outer periphery are in sliding contact with the inner sides of the three rails respectively. Two of the rails are excitation rails used for connecting a pulse power supply, and the third rail is a passive conductive rail which forms a conductive loop with the armature and the excitation rails. The eddy current induced in the passive conductive rail and the current in the excitation rails interact with each other to form a magnetic field distribution which is mutually offset in the center area of the launching path. The sum of the cross-sectional areas of the two excitation rails is greater than the cross-sectional area of the passive conductive rail. The application forms a magnetic field distribution which is mutually offset in the center area of the launching channel, thereby reducing the electromagnetic interference on the electronic equipment carried by the projectile.