1207 results about "Shock wave" patented technology

An exemplary catheter for use in a body lumen comprises: a catheter body; and a plurality of shock wave emitters disposed at a distal end of the catheter body, each shock wave emitter configured to generate a shock wave that propagates distally of the catheter body, wherein the plurality of shock wave emitters are arrayed about a longitudinal axis of the catheter body such that shock waves emitted from the plurality of shock wave emitters can constructively interfere distally of the catheter body, and wherein each shock wave emitter comprises electrodes separated by a spark gap and at least one electrical connector that connects at least one of the electrodes to an electrode of another shock wave emitter of the plurality of shock wave emitters.

Described herein are shock wave catheters having discontinuous emitter bands. The catheters may be used for treating occlusions in a body lumen. In some examples, the catheters include an elongated tube, a shock wave electrode assembly at least partially embedded within the elongated tube, and an enclosure surrounding the shock wave electrode assembly. In some examples, the electrode assembly includes an emitter band at least partially encircling the elongated tube, the emitter band forming a first electrode of an electrode pair, and one wire having a distal end forming a second electrode of the electrode pair. The shock wave electrode assembly is configured to emit a shock wave when a voltage pulse is applied across the electrode pair. In some examples, the at least one emitter band is compressible to reduce a diameter of the emitter band.

The invention discloses a damage effect evaluation system and method based on a large model, and relates to the technical field of nuclear explosion damage, computational grids adapting to different complexities are generated based on a self-adaptive grid technology, a computational domain is determined and the grids of a complex terrain area are refined by introducing a high-precision three-dimensional terrain model, and the damage effect evaluation method based on the large model is obtained. The local simulation precision is improved; meanwhile, a thicker grid is used in a simpler area, so that computing resources are saved, and the fineness of the model and the simulation accuracy are remarkably improved; through multi-scale coupling and multi-physics field coupling technologies, macroscale CFD simulation and microscale DEM simulation are combined, and thermal effect, radiation effect and structural mechanics coupling simulation are introduced; comprehensively analyzing shock waves, heat conduction, radiation propagation and comprehensive influences thereof on buildings and terrains; and the comprehensiveness and accuracy of evaluation are improved, so that the evaluation result has more practical significance.

The invention discloses a heat exchanger descaling and anti-corrosion system and device based on intelligent control, and relates to the technical field of system regulation, the heat exchanger descaling and anti-corrosion system based on intelligent control monitors key parameters of a heat exchanger through a real-time monitoring module so as to effectively prevent faults and performance reduction; the anomaly identification module detects anomaly based on key parameters, constructs a model through historical anomaly image data, judges real-time anomaly types and scaling thickness, and realizes rapid fault identification; the regulation and control module dynamically regulates the pulse width and the period of the power shock wave according to the fluid viscosity data so as to carry out automatic descaling and corrosion prevention on the heat exchanger; the corrosion prediction module predicts the corrosion rate and time based on the data of the corrosion prevention module, provides reference for maintenance, optimizes equipment management, reduces the maintenance cost, and guarantees the continuity and safety of the system. The system integrates real-time monitoring, intelligent identification, automatic corrosion prevention and descaling and prediction regulation and control, and the operation efficiency and reliability of the device are improved.

The invention discloses a high-pressure soft water medium treatment and supply system, which belongs to the technical field of seawater desalination treatment, and comprises a multi-dimensional ion detection module for detecting the concentration distribution characteristics of target inhibition ions in original seawater to generate a corresponding coating material selection instruction; the electric field dynamic coupling module captures a termination signal according to the coating material selection instruction; the shock wave generation module starts a main pump to generate fluid shock waves to execute sediment breaking action according to the termination signal; the monitoring module is used for monitoring the finally output softened water ion concentration and reversely calculating the pollution index of the coating surface; and the heat cycle feedback device is used for starting a self-cleaning mode according to the pollution index and transmitting waste heat in the cleaning process to the pump set. The electric field dynamic coupling adsorption and fluid shock wave cooperative treatment technology is adopted, high-efficiency ion capture, dynamic sediment removal and waste heat recycling can be achieved, energy consumption is remarkably reduced, and continuous and stable operation of the system is guaranteed.

The invention belongs to the field of cross fusion of the technical field of supersonic flow combustion and the field of artificial intelligence, and particularly relates to a knowledge-guided flow field reconstruction and shock train leading edge position detection method and a knowledge-guided flow field reconstruction and shock train leading edge position detection system. According to the method, in dynamic change prediction of the flow field in the isolation section of the combustion chamber of the scramjet engine, flow field reconstruction and a physical mechanism model are combined by adopting a knowledge distillation technology, time, space coordinates and suction parameter data are used as input, and the accuracy of flow field reconstruction is enhanced through generated concentrated knowledge. A deep learning network model for front edge position identification is constructed, and the front edge position of a shock wave string is accurately identified. According to the method, a novel multi-level information processing framework is formed by fusing physical knowledge and a data driving method, and the adaptive capacity and prediction precision of flow characteristics in a complex pneumatic environment are improved. According to the system, a real-time monitoring function is realized on a hardware platform, and powerful technical support is provided for pneumatic design optimization and flight safety.

The invention belongs to the technical field of metal part surface modification, and relates to a composite strengthening method for a carburized surface of a high-bearing gear of an aero-engine. According to the method, high-hardness and high-density ceramic shots are adopted as media for high-energy mechanical shot peening strengthening, the advantage that the subsurface strain hardening effect of the contact strengthening technology is good and the barb-shaped distribution characteristic of mechanical shot peening residual compressive stress are utilized, extremely high residual compressive stress is introduced to the subsurface position, and the contact fatigue performance of the tooth surface of the gear is improved. High-frequency laser shot peening strengthening is used for secondary treatment, so that the surface layer of the material is subjected to plastic deformation, high-amplitude residual compressive stress is introduced into the surface layer of the material within the depth range of more than 500 microns by utilizing the advantage of large influence depth of laser-induced shock waves, and the residual compressive stress can inhibit fatigue crack initiation, has a certain depth and inhibits fatigue crack propagation; and the bending fatigue resistance of the root of the gear can be effectively improved. And an abrasive flow process is adopted, so that the roughness is reduced to be more than 0.4 mu m.

The invention discloses a high-load supersonic compressor blade profile design method coupled with multi-point plasma excitation, which comprises the following steps: generating high-load large-bend blade profile geometric data on the basis of original geometric data by using a blade profile parameterization modeling method; the method comprises the following steps: acquiring compressor blade channel flow field characteristics under a low Reynolds number working condition through numerical simulation, and determining a blade surface flow separation area under the low Reynolds number; determining a multi-point rapid heating plasma excitation layout mode according to the characteristics of the flow separation area; and analyzing the flow control effect of the multi-point rapid heating plasma excitation on the blade type shock wave / boundary layer interference of the supersonic gas compressor. According to the method, the K-H instability of a shear layer is triggered by applying multi-point rapid heating plasma excitation in a flow field, a spanwise vortex array structure is induced to be formed, small-scale vortexes in a flow separation area are promoted to be mixed and evolved into a spanwise large vortex structure so as to accelerate dissipation, and the effect of inhibiting flow separation is achieved.

The invention relates to a closed-loop feedback transcranial alternating current stimulation system and method. The closed-loop feedback transcranial alternating current stimulation system comprises a phase stimulation system used for generating a plurality of electrical stimulation signals and stimulating different brain areas in the brain based on the electrical stimulation signals; a preset phase difference exists between the electrical stimulation signals; the electroencephalogram acquisition system is used for acquiring electroencephalogram signals of the brain after the phase stimulation system stimulates the brain for a preset time; and the evaluation feedback system is connected with the phase stimulation system and the electroencephalogram acquisition system and is used for evaluating the electroencephalogram signals acquired by the electroencephalogram acquisition system and adjusting the electrical stimulation signals based on an evaluation result. According to the closed-loop feedback transcranial alternating current stimulation system, the waveform signal can be flexibly adjusted based on the real-time oscillation signal of the brain, and the problems that in the prior art, the shock wave form is single, individual differences cannot be accurately matched, and dynamic brain network state changes cannot be adapted are solved.

The invention discloses a ducted fan blade and duct matching aerodynamic layout optimization design method and system, and the method comprises the steps: building a blade tip region grid and setting initial load distribution at the same time based on initial design parameters of a ducted fan; optimization is carried out in an alternating iteration mode, and gap distribution updating and duct profile updating are carried out in sequence; the coupling effect between the optimization methods is processed through the comprehensive evaluation function, and optimization parameters are adjusted according to the evaluation result; and when the relative change value of the comprehensive evaluation function is smaller than a preset value and meets the target process requirement, determining a final optimization scheme. According to the scheme, formation of a separation vortex system can be inhibited, and the interference effect of a shock wave boundary layer is improved.

The invention provides a side slope crack passive source seismic wave imaging method, which adopts a multi-wave multi-component seismograph to simultaneously collect a plurality of seismic wave signals on three components, including surface waves, body waves and the like. According to the design, the richness of the data is remarkably improved, so that the physical characteristics of various seismic wave signals can be comprehensively utilized for inversion analysis in data processing. Through combined processing and constraint of different wave types, the problem of multiplicity of solutions in geophysical inversion can be effectively reduced, and the stability and reliability of a result are improved. In addition, due to acquisition of multi-component data, imaging is more comprehensive, and particularly, the method has obvious advantages in description of fracture directivity and geometrical characteristics.

The invention relates to the technical field of action analysis, in particular to a laser targeting training management system which comprises an immersive training environment module, a biological characteristic analysis module group, an intelligent trajectory management module group, a federal learning center module group, a tactical training management module group and a command and control system module group. Compared with the limitation of lack of battlefield dynamic complexity simulation by adopting a static preset scene in the prior art, the scheme deeply integrates multi-physical field environment control, intelligent target dynamic coordination and a cross-sensory feedback technology to construct an immersive battlefield space with temperature and humidity gradient adjustment, explosion shock wave simulation and geographic space accurate reconstruction linkage; therefore, multi-dimensional collaborative transition from single-dimensional visual simulation to tactile sense / auditory sense / olfactory sense / somatosensory is realized, so that soldiers can obtain subversive environment adaptability and tactical decision-making ability exercises in a comprehensive battlefield pressure environment close to reality.

The invention belongs to the technical field of computational fluid dynamics, and discloses a numerical simulation method for supersonic shock wave turbulence interference, comprising the following steps: S100 initializing flow physical quantities in the Reynolds-averaged Navier-Stokes equations and turbulence characteristic quantities in the #imgabs0#SST turbulence model equation; S200 solving the RANS equation to obtain the #imgabs2# at the #imgabs1#th moment; calculating the scale-reduced dimensionless adverse pressure gradient quantity #imgabs3# according to the correlation value obtained in S200; calculating the adjustment function #imgabs5# according to the #imgabs4# value obtained in S300 to obtain an improved turbulent kinetic energy generation term #imgabs6#; solving the improved #imgabs8#SST turbulence model equation according to the #imgabs7# obtained in S400 to obtain #imgabs9#; substituting the #imgabs10# obtained in S500 into S200, and solving it iteratively until the RANS equation residual is Res n Less than a certain value e or reach the maximum number of steps N = N max When , the iterative solution stops. According to the average value of the latest flow physical quantity output by S600 #imgabs11#, the numerical simulation ends.

The invention relates to the technical field of remote execution control, in particular to a blasting operation control system and method based on the Internet of Things, and the system comprises a vibration simulation analysis module, a risk level calculation module, an operation process planning module and a real-time abnormity response module. According to the method, shock wave propagation under various blasting conditions is simulated and analyzed, the safety distance is accurately predicted, blasting safety is improved, risk assessment and adjustment of project planning are achieved by integrating the geological structure, the climate condition and the building position, the sustainability and social responsibility of a project are enhanced, and the method is suitable for popularization and application. The operation condition of a target project is monitored in real time in combination with an Internet of Things sensor, blasting parameters are adjusted in real time or operation is stopped, accurate and dynamic operation control is provided, the personnel safety risk is effectively reduced, the operation efficiency is improved, the safety and economic benefits of blasting operation are enhanced, and the adverse effect on the environment is reduced.

The invention discloses a brick-concrete structure explosion damage reconstruction and visualization method based on deep learning, and the method comprises the steps: obtaining a damage data set of a brick-concrete structure under multi-scene explosion through numerical simulation, and building a training database through data processing and conversion, and building a two-stage brick-concrete structure damage prediction model based on a graph neural network. Error evaluation and parameter optimization are carried out on the model, the prediction capacity of the damage prediction model is improved, and according to node displacement and node stress predicted by the two-stage brick-concrete structure damage prediction model, visualization of the damage effect of the brick-concrete structure under various explosion impacts is achieved. According to the method, the damage results of the shock waves under different equivalents and different explosion positions can be quickly obtained, the explosion damage effect is visualized, and the calculation efficiency is greatly improved while the calculation precision is ensured.

The invention belongs to the field of computational explosion mechanics, and particularly relates to a rapid calculation method for a shock wave and detonation wave propagation process in a non-uniform medium, and the rapid calculation method comprises the following steps: 1, initializing a calculation program; step 2, estimating and calculating step length in each time step; step 3, carrying out integration on the ordinary differential equation by adopting an explicit three-order TVD Runge-Kutta format; 4, solving a Mach number through an A-M relation; 5, data correction is carried out, wherein the data correction comprises regularization and smoothing processing of grids; and step 6, checking whether termination time is reached or not, if so, ending all processes to complete operation, and if not, returning to the step 2 to continue to circularly solve. According to the rapid calculation method, rapid numerical calculation of propagation of shock waves and detonation waves in a non-uniform medium is achieved, wherein the phenomena comprise refraction, transmission, Mach reflection and the like.

The invention discloses an optical test system and method for measuring the total temperature of a supersonic combustion flow field, and relates to the field of combustion flow field measurement. The system comprises supersonic combustion incoming flow, a time sequence synchronizer, a first laser, a first focusing lens, a first total reflection plane mirror, a second laser, a second focusing lens, a sheet light lens, a second total reflection plane mirror, a computer, an ICCD, a tunable laser diode, a laser controller, a photoelectric detector, an industrial personal computer and a signal monitor. On the basis of a non-contact optical testing technology, the local total temperature is obtained by measuring the speed and the static temperature of the combustion flow field at the same time on the premise that the flow structure and the combustion state of the combustion flow field are not damaged, the structure of the supersonic combustion flow field is not obviously affected, unnecessary oblique shock waves are not caused, and the measurement accuracy is high. And the local and downstream flow and combustion states of the tested combustion flow field are not influenced.

The invention discloses a fairing pulsating pressure scaling wind tunnel test method capable of reducing space-ground difference. The method comprises the following steps: determining initial parameters; based on the determined initial parameters, carrying out a transonic speed scaling manual transition pulsating pressure wind tunnel test, arranging pulsating pressure measuring points, and carrying out transonic speed state fairing pulsating pressure environment measurement to obtain a measurement result; performing parameter optimization according to a comparison result of a measurement result and a standard parameter under a real flight test condition to obtain an optimal parameter of manual transition; and based on the optimal parameters, carrying out a transonic speed scaling manual transition pulsating pressure wind tunnel test to obtain test results of the configuration in different free incoming flow Mach number, attack angle and sideslip angle states. According to the method, the free incoming flow local shock wave-boundary layer interference state and the boundary layer separation state of the ground wind tunnel test and the flight test are ensured to be closer through a manual transition mode, and the ground test prediction precision of the carrier rocket fairing pulsating pressure environment is improved.

The invention discloses a high-order nonlinear weighted difference numerical simulation method based on precise dissipation control, and relates to the field of compressible flow numerical simulation, and the method comprises the steps: 1, building a calculation grid based on aircraft profile parameters and calculation conditions; 2, assigning initial values to nodes of the computational grid based on aircraft numerical simulation conditions; 3, setting a time step length based on an aircraft numerical simulation condition and a CFL condition; and 4, cyclically executing the following time propulsion process until the termination time or convergence condition required by the numerical simulation of the aircraft is reached, more accurately controlling the numerical dissipation of the WENO format during the numerical simulation of the aircraft, and improving the flow field simulation capability of a small-scale region on the premise that the shock wave capture stability is basically not reduced.

The invention relates to the technical field of flow field shock wave recognition and visualization methods, in particular to an intelligent flow field shock wave recognition and visualization method, which comprises a data preprocessing module used for preprocessing original flow field data to obtain normalized input data in a multidimensional tensor form; the feature extraction module is used for extracting local gradient features of input data through special matrix mapping so as to generate a preliminary feature matrix; the topological association module constructs a topological structure based on the preliminary feature matrix and generates a topological feature matrix; the attention enhancement module is used for weighting the topological feature matrix through a special function so as to enhance the significant features of the shock wave region; the output module generates a final shock wave characteristic matrix based on the weighted matrix for visual presentation, a special matrix method is introduced for characteristic extraction, and change details of a shock wave area in a flow field can be accurately captured by combining periodicity and gradient characteristics of a trigonometric function.

The invention discloses a supersonic aircraft forebody fast reverse design method considering any three-dimensional bending shock waves, and relates to near space hypersonic aircrafts. According to the supersonic aircraft precursor considering any three-dimensional bending shock wave, transverse flow which cannot be neglected by a complex three-dimensional curved surface supersonic aircraft precursor is theoretically considered by utilizing a three-dimensional bending shock wave theory and a three-dimensional bending characteristic line method, so that the designed supersonic aircraft precursor can reach an ideal lift-drag ratio; and the flow field inverse design of any known three-dimensional bending shock wave is realized. Besides, gradient information can be fully utilized through the three-dimensional bending shock wave theory and the three-dimensional bending characteristic line method, compared with a traditional osculating method, the calculation efficiency is higher, the precision is higher, the obtained basic flow field is not limited to a regular flow field any more, and a wider performance improvement space is provided for aircraft design through more free shock wave selection.

The invention discloses a heat exchanger and method for rare gas preparation, and relates to the technical field of heat exchangers, the heat exchanger comprises a heat exchange mechanism, the outer surface wall of the heat exchange mechanism is sleeved with a cleaning structure, the input end of the heat exchange mechanism communicates with a feeding mechanism, and an aeration mechanism is inserted into the inner surface wall of the heat exchange mechanism. In the cleaning process, the second air pump conveys outside air to the aeration ball, so that a large number of bubbles are formed in cleaning liquid, dirt is cleaned by means of tiny shock waves and high-speed micro jet flow generated during bubble movement and breakage, and the ultrasonic generator can release sound wave energy; the synergistic effect of bubbles and sound waves greatly improves the cleaning efficiency and effect, enhances the stripping capacity of dirt on the inner wall of the heat exchanger, ensures that rare gas is not polluted in the heat exchange process, maintains the high purity of the rare gas, keeps the inner wall of the heat exchanger smooth, and improves the heat transfer efficiency, so that the cooling or heating speed of the rare gas is increased, and the service life of the heat exchanger is prolonged. The efficiency of the whole preparation process is improved.

The invention discloses a hypersonic flow instability multi-field coupling prediction method and system, and relates to the technical field of modern high-speed aircraft design, and the method comprises the steps: obtaining the multi-physical field parameter distribution of a hypersonic flow field; based on a shock wave-boundary layer interaction mechanism, constructing an instability sensitive graph data structure by taking multi-physical field parameters as input, setting graph nodes in a shock wave influence region, a boundary layer region and an intersection region thereof, and calculating connection weights among the nodes; performing multi-scale decomposition on the instability sensitive graph data structure, and extracting instability modes of a shock wave scale, a vortex scale and a molecular scale; screening the instability modes by adopting a hypersonic velocity stability criterion, and determining a dominant instability mode; and constructing an instability evolution prediction model based on the dominant instability mode, and outputting a spatio-temporal evolution rule of hypersonic flow instability. According to the method, the problem that the flow instability phenomenon in the hypersonic velocity complex multi-physical field environment is difficult to accurately predict can be solved.

The invention discloses a goaf overlying strata three-zone identification and division method based on multi-parameter quantitative coupling, and relates to the technical field of coal mines. The method comprises the following steps: acquiring drilling data of an overlying strata of a drill hole drilling goaf through a drill bit which is internally provided with a vibration wave monitoring module, a flushing fluid leakage monitoring module, a drilling speed measuring module and a gas flow monitoring module; determining the parameter weight of each index based on an analytic hierarchy process by means of an index weight calculation module to obtain a comprehensive physical index I value; according to a built-in calculation program of the region division module, grouping of the comprehensive physical property index data total set K is completed, and then three-dimensional partition identification and division of goaf overlying strata three zones are completed. According to the method, the drilling data obtained in real time in engineering drilling is taken as a basic parameter variable, inversion of the fracture distribution characteristics of the overlying strata in the goaf is realized, and the efficiency and the accuracy of three-zone division are effectively improved.

The invention discloses an aerodynamic configuration structure of a precision guidance assembly and a design method, and belongs to the technical field of precision guidance, an assembly precursor adopts continuous three-section curve design: a supersonic speed section adopts a parabola profile, is provided with ribs on the surface, and is used for optimizing shock wave control under a supersonic speed working condition; the transonic speed section adopts a hyper-ellipsoid curved surface, ribs are arranged on the surface of the transonic speed section, and metamaterials are attached to the ribs and used for restraining transonic speed separation; the subsonic speed section adopts arc transition, and ribs are arranged on the surface and used for improving the lift force efficiency of the control surface; wherein the curvatures at the joints of the three sections of curves are continuous. According to the method, supersonic velocity-transonic velocity-subsonic velocity three-section collaborative design is realized, and meanwhile, a boundary layer is improved from a microscopic level by combining a collaborative drag reduction design of a microscopic rib and metamaterial technology, and the performance of a guidance assembly is optimized and improved.

The invention discloses a self-adaptive parameter identification method for an SST turbulence model in shock wave boundary layer interference, and the method comprises the steps: S1, constructing a high-dimensional sample space according to a closed parameter interval range of the SST turbulence model under a determined working condition, carrying out the optimal Latin hypercube sampling, and uniformly obtaining the sample information in the whole space, and enabling the sample information to serve as an input parameter sample; s2, performing numerical simulation based on an input parameter sample and a determined working condition to form a model prior sample set; s3, according to the model prior sample set, constructing a flow field wall surface pressure prediction model under shock wave boundary layer interference based on an improved Bayesian neural network; and S4, based on the flow field wall surface pressure prediction model under the interference of the shock wave boundary layer, performing adaptive parameter identification on the SST turbulence model by adopting a particle swarm optimization algorithm to obtain the optimal closing parameter of the SST turbulence model for realizing the high-precision simulation of the flow field. According to the method, the numerical simulation precision and speed are improved, and technical support is provided for safe and reliable work of the scramjet engine in a complex environment.

The invention discloses a high-voltage direct-current line EM lightning arrester valve plate shunting non-uniformity test system and method, and belongs to the technical field of lightning arrester performance test.The method comprises the steps that S1, a high-voltage direct-current power transmission system simulation model is established, and the discharge current of an EM lightning arrester under the severe working condition of single-pole line short circuit is evaluated based on the high-voltage direct-current power transmission system simulation model; adopting square-wave pulse approximate discharge current, and determining the total amplitude and square-wave pulse width of long-wave discharge current of the EM lightning arrester; s2, applying the square wave pulse to the tested EM lightning arrester resistor discs through a shock wave test platform, and testing the current magnitude and the total current of each resistor disc of the EM lightning arrester under the working condition; the total amplitude and the square wave pulse width of the preset square wave pulse are the same as the total amplitude and the square wave pulse width of the long wave of the discharge current of the EM arrester; and S3, according to the current of each resistor disc and the total current, calculating a current non-uniform coefficient and the current range of the resistor discs. According to the invention, the current distribution non-uniformity of the multi-column parallel lightning arrester can be tested and evaluated more reasonably and comprehensively.

The invention relates to the technical field of medical instruments, in particular to an electromagnetic focusing extracorporeal shock wave pancreatic lithotripsy device and method.The electromagnetic focusing extracorporeal shock wave pancreatic lithotripsy device comprises a device body, a bed body is installed on one side of the device body through a supporting frame, and a lithotripsy notch is formed in the side, close to the device body, of the bed body; a large C-shaped arm and a small C-shaped arm installed on the inner side of the large C-shaped arm are installed at the position of the notch of the device body, an X camera imager is installed at the upper end of the large C-shaped arm, and a shock wave generator and an ultrasonic probe installed on one side of the shock wave generator are installed on the small C-shaped arm. An energy adjusting module used for controlling the shock wave generator and a safety detection module used for detecting the skin temperature are arranged in the device body, and a displayer and a human-computer interaction interface are arranged on one side of the device body. The technical scheme in the prior art has limitations on shock wave generation, positioning precision, energy regulation and control and treatment strategies.

The invention provides a surface treatment method based on laser shock, and relates to the field of laser processing. The surface treatment method based on laser shock comprises the steps that a metal mold with a hollow area is placed between a to-be-treated metal sample and a restraint layer, laser beams irradiate the to-be-treated metal sample in the direction perpendicular to the restraint layer, and patterns are formed on the to-be-treated metal sample under the action of laser shock waves; wherein the energy density of the laser shock waves is smaller than 3.25 GW / cm < 2 >, the thickness of the metal mold is larger than 10 micrometers, and the pulse width of the laser shock waves is smaller than 30 ns. The laser-induced shock wave load is utilized, the surface strengthening effect and the patterning effect are introduced at the same time, the anti-deformation surface with the patterning array can be manufactured, the abrasion resistance and durability of the metal sample to be treated can be enhanced, and the problem that an existing surface patterning technology is poor in durability is effectively solved.

The invention discloses a method and a device for removing gas-liquid inclusion in quartz sand. The method comprises the following steps: S1, roasting quartz raw ore; s2, carrying out water quenching and high-voltage electric pulse treatment on the quartz ore subjected to roasting treatment in S1; and S3, purifying the quartz ore obtained in the step S2 to obtain the high-purity quartz sand. According to the method, when the quartz is treated through high-voltage electric pulse water quenching, plasma explosion, thermal stress expansion and the like are generated on a mineral interface, then shock waves and a destructive power field are formed, cracks are generated and expanded, and expansion cracks are generated on the mineral interface in ores while monomers dissociate the quartz and gangue minerals are removed; a discharge channel is established for gas-liquid inclusions and impurities wrapped by the gas-liquid inclusions, damage to aggregative fluid inclusions on the surface layers of quartz particles is intensified, and a high-purity quartz sand raw material with higher quality is provided for semiconductors and photovoltaic quartz glass products.