401 results about "Shock wave" patented technology

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 discloses a flow field key structure detection and feature point extraction method based on an optimized YOLO model, and the method comprises the steps: S1, obtaining flow field time sequence schlieren images of an air-breathing aircraft under different working conditions through a high-speed schlieren collection system in a wind tunnel test; s2, preprocessing the flow field time sequence schlieren image to obtain a data set corresponding to the strong shock wave of the isolation section of the air-breathing aircraft, and dividing the data set into a training set, a verification set and a test set in proportion; s3, constructing an optimized YOLO target detection model, and obtaining an optimal weight model after iterative training and verification; and S4, adopting the optimal weight model to complete target detection and feature point extraction of the test set or the schlieren image to be detected. According to the method, the target area is focused through area cutting, meanwhile, a targeted data enhancement strategy of Gaussian noise, brightness adjustment, contrast ratio adjustment and saturation is designed, a high-quality annotation data set is constructed, and the model detection precision is effectively improved.

The application provides a highway charging load prediction method and control system based on traffic flow power. Through a second-by-second specific power model of different electric vehicle types on the highway, factors such as road slope, vehicle load, electric vehicle braking recovery characteristics, instantaneous speed and acceleration can be considered to achieve more accurate energy consumption modeling. By establishing a specific power operation mode distribution library of different vehicle types, using a shock wave model and a cellular transmission model to solve, quantifying the congestion propagation process, dynamically correcting the specific power calculation parameters, only the road section parameters and average speed are needed to calculate the energy consumption under complex road conditions. The driver's range anxiety is quantified as a dynamic variable, and charging decision rules are established for different scenarios. The charging probability is dynamically corrected based on the queue length, weather, and driver type, and an electric vehicle charging time prediction model is established based on different service area charging scenarios.

The invention discloses a shock wave diffusion process testing method based on double cameras and digital schlieren. The method comprises the steps that two high-speed cameras are used for shooting digital schlieren images generated in the shock wave diffusion process; performing image splicing on the acquired images shot by the double cameras; the position of the shock wave is calculated through the spliced image, shock wave position data at different moments are obtained, and the speed of shock wave propagation in the x-axis direction and the y-axis direction is obtained. Based on binocular vision, a digital schlieren system is adopted to collect an air flow field information image containing a shock wave propagation process; splicing of double-camera images is achieved through an improved homography matrix method, the shock wave testing range is expanded, the whole shock wave propagation process is successfully captured, the shock wave diffusion testing accuracy is improved, and visual monitoring of wave types represented by shock waves in various transparent media can be achieved.

The invention discloses a method for predicting shock waves through a multi-region conservation enhanced physical information neural network, and belongs to the field of flow field prediction of shock waves and strong nonlinear physical phenomena in high-speed flow, and the method comprises the steps: S1, carrying out numerical simulation through fluid dynamics software to obtain a reference flow field solution of a to-be-solved N-S control equation, the verification module is used for verifying a model solving result; s2, constructing a neural network comprising an integral layer, a micro-layer and a loss function error layer; s3, constructing a physical information neural network; s4, training is carried out after physical information neural network training parameters are set, and whether a convergence standard is met or not is determined by constructing a joint loss function corresponding to the physical information neural network; and S5, applying the trained neural network model to shock wave prediction of high-speed flow field simulation under different working conditions. Through the multi-region local conservation constraint, the width of the shock wave transition region is effectively compressed, so that the relative error of the physical quantity is obviously reduced compared with the existing method.

The invention belongs to the technical field of hypersonic flight vehicle control, and particularly relates to a hypersonic flight vehicle protection control method considering non-starting of an air inlet channel. The method specifically comprises the steps of establishing a quasi-one-dimensional nominal mechanism model to describe flow field changes of an isolation section and a combustion chamber; adopting a physical information neural network to construct a reduced-order model as a real-time agent of the quasi-one-dimensional model; designing a dual extended Kalman filtering algorithm to realize joint online estimation of model parameters and blind area states, and introducing shock wave position pseudo measurement to form multi-loop feedback; a dual-channel fusion early warning system of a model channel and an intelligent sensor channel is constructed, and robust early warning is realized through adaptive weight; and designing a continuous adaptive model prediction controller, and dynamically adjusting a control strategy according to risk indexes and parameter uncertainty to realize active protection control.

The invention discloses a method for improving the oxidation resistance of nickel-based superalloy, and belongs to the technical field of metal material surface modification. Based on the high-energy transient effect of laser shock waves, the method mainly comprises the key steps of alloy surface pretreatment, laser shock peening process implementation, post-treatment and the like. Specifically, firstly, the surface of the nickel-based single crystal alloy is subjected to pretreatment such as polishing and cleaning, surface defects and pollutants are removed, and the treatment quality is guaranteed; then, according to the material characteristics and performance requirements of the nickel-based single crystal alloy, laser parameters such as laser energy, pulse width and light spot diameter are accurately set, and proper restraint layer and absorption layer materials are selected; then, high-energy pulse laser is utilized to irradiate the absorption layer, high-temperature and high-pressure plasma is induced to be generated, the plasma expands and explodes to generate strong shock waves, the shock waves act on the alloy surface, the surface material is subjected to severe plastic deformation, a residual compressive stress layer with the depth capable of reaching hundreds of micrometers is formed, meanwhile, surface grains are refined, and the microstructure is optimized; and after the strengthening treatment is completed, simple cleaning and performance detection post-treatment are carried out. Through laser shock strengthening, a special organization structure with high density and low defect density is formed on the surface of the nickel-based single crystal alloy, diffusion and invasion of oxygen atoms are effectively hindered, and the oxidation resistance of the alloy is remarkably improved. According to the method, the controllability of technological parameters is high, the strengthening effect can be accurately regulated and controlled, the treatment process is free of pollution and high in efficiency, the obtained strengthened nickel-based single crystal alloy can be widely applied to the fields such as aerospace engine hot end parts and nuclear energy equipment which have strict requirements for high-temperature oxidation resistance, the reliability of related parts is greatly improved, and the service life of the related parts is greatly prolonged.

The invention discloses a multi-sensor fusion target scoring system high-precision positioning method, and relates to the technical field of target scoring positioning, and the method comprises the following steps: building a transient interference recognition channel based on the electromagnetic response of a shock wave sensor, obtaining the electromagnetic disturbance of the bullet hit front edge, and generating an interference time sequence; performing delay triggering on the image sensor according to the interference time sequence, and avoiding an interference peak value to form a safe exposure time period; performing charge pre-release on the image acquisition chain before safe exposure; carrying out synchronous compensation on the shock wave signal based on energy distribution of charge pre-release, so that the shock wave signal and image energy response are symmetrical and mutually stable in a time domain; and dynamic shielding control is carried out on a space coupling path between the two types of sensors by utilizing an energy balance region formed in the mutual stable state. Through energy symmetric compensation and dynamic shielding control of shock waves and image signals, time-space separation and synchronous mutual stability of the signals are achieved, and high precision and stability of target scoring positioning under high-energy shooting are ensured.

The invention discloses a wide-speed-range variant high-speed aircraft aerodynamic layout, and belongs to the technical field of aircrafts, the wide-speed-range variant high-speed aircraft aerodynamic layout comprises a fuselage, the front end of the fuselage is provided with a drag reduction rod, the rear end is provided with a thrust vectoring nozzle, the left and right sides are symmetrically provided with triangular sweepback wings, and the top is provided with a supporting structure; a high-pressure capturing wing is arranged on the top of the supporting structure. The shock wave separation effect of the drag reduction rod is combined with the high-pressure capture and reflection shock wave induction mechanism of the high-pressure capture wings, so that the aircraft can achieve effective drag reduction and lift augmentation effects in different flight states, and the lift-drag ratio and adaptability of the high-speed blunt cone aircraft are remarkably improved.

The invention provides a handheld shock wave generating system which comprises a shock wave balloon and a driving circuit, and the driving circuit comprises a primary power supply circuit, a high-voltage booster circuit, a voltage doubling circuit and a control circuit. After a voltage signal VCCS2 output by the primary power supply circuit is subjected to self-oscillation and boosting of the high-voltage boosting circuit and multiple rounds of voltage multiplication of the voltage doubling circuit, the voltage signal VCCS2 can be increased by hundreds or even thousands of times, a storage battery and a mains supply do not need to be used, miniaturization can be achieved, and carrying is convenient.

The invention discloses a method for producing a carbon source through co-fermentation of sludge and kitchen waste, and relates to the technical field of organic waste recycling, and the method comprises the following steps: collecting a bubble generation time sequence, a liquid phase pressure fluctuation signal and an acoustic scattering signal in a sludge and kitchen waste co-fermentation system, and constructing a coupling distribution model of a bubble size and an oscillation frequency; generating an initial energy evolution spectrum; and under the constraint of the initial energy evolution spectrum, identifying a coherent feature sequence of bubble oscillation, calculating the energy concentration intensity of a multi-scale bubble group, positioning a high-frequency energy concentration area and generating a nonlinear resonance fingerprint. By means of dynamic monitoring and intelligent regulation and control, the energy gathering area is accurately positioned, the resonance process is intervened in real time, suppression of shock wave propagation and predictive control over the structural fatigue risk are achieved, and the fermentation system stability and the carbon source release efficiency are improved.

The invention discloses a multi-information synchronous measurement device and method for a whole space, and belongs to the technical field of spectral measurement and analysis. The device comprises a double-pulse laser excitation module, a multi-angle spectrum acquisition module, a transient imaging module, a backlight shadow imaging module and a synchronous control module. The measurement method comprises the steps of sample positioning pretreatment, double-pulse plasma excitation, multi-angle spectrum synchronous acquisition, plasma transient imaging, shock wave backlight shadow imaging, detection post-treatment and the like, and synchronous acquisition of multi-dimensional data is realized through accurate time sequence control. Omnibearing synchronous measurement of plasma spectrum, form and shock wave propagation is realized, and the device has the advantages of high data time consistency, comprehensive information acquisition, high measurement precision and high experiment efficiency, can be widely applied to the fields of material analysis, environment monitoring, plasma physical research and the like, and has wide application prospect. And the method has good adaptability in LIBS (Laser-induced Breakdown Spectroscopy) technology expansion scenes such as double pulses and magnetic confinement.

The invention discloses a bridge ship impact point positioning method and system based on shock wave time difference analysis, and the method comprises the steps: arranging a vibration sensor array on a plurality of piers in a non-navigable hole region of a bridge, and connecting the vibration sensor array with an edge calculation module; impact characteristics are extracted, and vibration acceleration is calculated; setting a dynamic threshold value, and calculating the coordinates of the impact point when the vibration acceleration peak value exceeds the dynamic threshold value; in the calculation process, double constraint conditions are constructed by using time-frequency joint similarity and time difference of impact characteristics, and correlation of other vibration sensors is carried out; constructing a positioning equation set special for the concrete structure bridge; and resolving a positioning equation set and outputting impact point coordinates. According to the system, a vibration sensor array is used for collecting vibration signals; the edge calculation module is used for extracting impact characteristics and calculating vibration acceleration and impact point coordinates of the vibration sensor; the central processing unit is used for outputting impact point coordinates and damage indexes. According to the method and the system, the impact point in the event that the ship impacts the bridge can be quickly and accurately positioned.

The application provides a rotary impingement oblique flow centrifugal combined compressor and application thereof, and belongs to the technical field of turbine engines, and comprises an outer casing structure, an inner casing structure, a working mechanism and a diffuser mechanism, the outer casing structure and the inner casing structure are rotary bodies, the inner casing structure is located inside the outer casing structure, the inner casing structure and the outer casing structure form a working cavity, the working mechanism is installed in the working cavity and is used for pressurizing airflow. Compared with the compression mode of a conventional combined compressor, the application draws lessons from the pressurization mode of a supersonic inlet, and the Mach number of airflow relative to a rotating impeller reaches 2 or more through high-speed rotation; at this time, a series of weak oblique shock waves are constructed through the contraction of a passage, and a high-efficiency compression system is obtained through the pressurization of the shock wave system, the single-stage pressure ratio of the high-efficiency compression system is much higher than that of a conventional compressor, and the application has the advantages of compact structure, simple processing and long service life.

Embodiments of the present application disclose a river bed load transport characteristic determination method and device, electronic equipment and a computer readable medium, relating to the field of engineering technology. The method performs fast Fourier transform on the sound pressure signals of the microphone array to obtain a sound pressure matrix in the frequency domain; based on the sound pressure matrix, cross-spectrum operation is performed to obtain a cross-spectrum matrix; based on each scanning grid point j on the surface of the monitoring sensor plate as an imaginary sound source point, a sound propagation model is selected according to the aerodynamics theory to determine the sound signal monitored by any microphone; each grid point is scanned, the auto-spectrum of the simulated sound signal is calculated, and the sound source holographic image of the bed load shock wave is determined; the sound source intensity is simulated, the bed load spatial position is obtained, and the bed load particle size component information is obtained through the calibration function relationship. That is, in the present application, the bed load spatial position and the bed load particle size component information are obtained, this method can accurately determine the transport characteristics of the bed load, and becomes an important support for quantifying the disaster prevention and reduction work of mountainous rivers.

This invention discloses a dynamic pressure-based method for testing and analyzing hammer shock waves in aero-engines, belonging to the field of aero-engine testing and structural strength design. The method first uses a surge-induced pressure method to generate hammer shock waves at the engine inlet. Based on the flow field characteristics of the air intake outlet section (AIP section) during surge, dynamic total pressure and static pressure measuring points are arranged in a combination of circumferential and radial directions. Pressure signals are synchronously recorded using a high-speed data acquisition system, and four characteristic parameters—surge overpressure, overpressure ratio, loading time, and pressure rise rate—are defined to quantitatively analyze the intensity, spatial distribution, and dynamic process of the hammer shock waves. This invention achieves rapid, accurate, and comprehensive characterization of the aerodynamic load of hammer shock waves, providing reliable input loads directly for the strength design of complex structures such as S-curve air intakes, thereby improving aircraft safety.

The utility model belongs to the technical field of absorption rods, and particularly relates to a Hopkinson pressure bar absorption rod which comprises a first rod used for being connected with a main rod of a Hopkinson pressure bar. The first bulge is fixed with the edge of the first rod; the second rod is used for being connected with the first rod, a circular groove is formed in the second rod, and a part of the first rod and the first protrusion are arranged in the circular groove. The spring in the pre-compression state is arranged in the circular groove of the second rod, so that the rigidity of the spring is increased, the energy absorption range is widened, meanwhile, certain thrust is applied to the first rod, and the energy absorption effect is improved. When the impact force is smaller than the thrust, the first rods are kept relatively static, when the impact force is larger than the thrust, the first rods extrude the elastic pieces, the elastic pieces reduce reflected waves by absorbing part of impact energy, and therefore the energy absorption efficiency is improved, and the shock wave absorption capacity of the absorption rods is improved.

The utility model discloses a shock wave discrete rotary valve, which relates to the technical field of hydraulic valve banks and comprises a valve body, a valve core, a shock wave buffer and a sensor, the valve body is provided with an oil inlet runner, a recovery channel and an oil outlet runner; the valve element comprises a rotating shaft, a rotary disc and a plurality of rotary cups. The rotary disc is fixedly connected to the middle of the rotating shaft, and the multiple rotating cups are connected to the periphery of the rotary disc at equal intervals. The sensor is arranged on the valve body; the axial leads of the oil inlet flow channel and the oil outlet flow channel are collinear and are tangent to the movement track of the center of the revolving cup; a recovery channel is formed in the tangent position in the radial direction of the valve element. A shock wave buffer is arranged at the bottom of the recovery channel. Oil liquid containing shock waves impacts the revolving cup through the oil inlet flow channel, the shock waves rapidly expand in the revolving cup and are splashed out, the oil liquid enters the recovery channel under the centrifugal effect of revolving of the revolving cup, shock wave energy is absorbed by the shock wave buffer, and part of the remaining oil liquid in the revolving cup is thrown into the oil outlet flow channel under the impact rotation and centrifugal effect of the revolving cup. And one part enters the next impact cycle along with the rotation of the revolving cup.

The invention belongs to the field of transsupersonic wind tunnel design, and discloses a two-dimensional flexible nozzle design method for a variable outlet section of a transsupersonic wind tunnel. The design method comprises determining the length of a model area; determining the aerodynamic theory outlet section position of the transonic nozzle; determining the minimum distance between the aerodynamic theory outlet section of the supersonic nozzle and the aerodynamic theory outlet section of the transonic nozzle; determining the aerodynamic theoretical outlet section position of the supersonic nozzle; determining the aerodynamic theoretical outlet section height of the supersonic nozzle; and determining the expanding angle. According to the design method of the two-dimensional flexible spray pipe for the variable outlet section of the transsupersonic wind tunnel, the problem that shock waves generated by the connection order difference or the gap of the spray pipe section and the supersonic test section interfere with a flow field is solved fundamentally, and the uniformity index of the flow field in the full-speed domain range of the transsupersonic wind tunnel is improved; the supersonic flow field quality is improved and kept stable for a long time, the test data quality is improved, and the method has engineering practical value.

The invention provides a shock wave curvature measurement method and device. The method comprises the following steps: acquiring an original image obtained through a planar laser scattering technology; performing contrast enhancement and noise reduction on the original image to obtain a target image; a window area is selected from the shock wave starting point in the target image; carrying out adaptive image segmentation on the newest window area to obtain a local shock wave curve, and judging whether a shock wave end point exists or not; if not, moving the window area in the target image based on the geometric direction of the latest local shock wave curve, and returning to the step of performing adaptive image segmentation on the latest window area to obtain the local shock wave curve; if yes, the local shock wave curves are spliced, the curvature is calculated, and the shock wave curvature is obtained. According to the scheme, the strategy of combining the moving window and the local adaptive image segmentation is adopted, it is ensured that the optimal segmentation effect can be achieved in each local area, the accuracy of shock wave curve extraction is improved, and therefore the purpose of improving the accuracy of shock wave curvature measurement is achieved.

The application belongs to the field of numerical simulation, and particularly relates to a modeling method of a shock wave light field in a hypersonic flow field, comprising the following steps: adopting an unsupervised learning algorithm to perform gradient clustering on flow field data, and determining the position of a shock wave and the inner and outer boundaries of a shock wave domain in the flow field domain; constructing a hybrid dimension numerical continuous and discrete strategy, determining the main direction of a light ray based on the strategy, performing continuous medium approximation processing on the main direction of the light ray, and performing structured grid discrete processing on the non-main direction of the light ray; based on the analogy of Fermat's principle and Maupertuis' principle, the transmission of the light ray in the refractive index field is analogized to the movement of equivalent real particles in the refractive index potential field, and the dynamic relationship between the equivalent real particles and the refractive index potential field is established; based on the dynamic relationship, the transmission path of the light ray in the shock wave is simulated, and the modeling of the shock wave light field in the hypersonic flow field is realized. The application significantly improves the efficiency and accuracy of the modeling of the shock wave light field in the hypersonic flow field.

The utility model discloses a pipe blocking prevention device for a pump truck, which relates to the technical field of engineering machinery and comprises a bent pipe and a delivery pipe, a mounting hole is arranged at the bend of the bent pipe, a connecting pipe is fixed on the outer side of the mounting hole, a support block is inserted at the upper end of the inner wall of the connecting pipe in a sliding manner, and the lower end face of the support block is connected with an elastic support component. A fixing cylinder is installed on the side wall of the bent pipe, and one end of the fixing cylinder is connected with a pulse valve. In the utility model, the pressure sensor is used for detecting the pressure generated by the material at the outlet of the conveying pipe and transmitting the pressure information to the controller, when the pressure is reduced, the material is blocked at the bent pipe, the controller controls the pulse valve and the electromagnetic vibrator to be intermittently opened and closed, and the electromagnetic vibrator drives the support spring and the electromagnetic vibrator to vibrate; and meanwhile, the high-pressure gas intermittently enters the fixed cylinder, and impact waves generated by the high-pressure gas impact the blocked materials, so that the problem of pipeline blockage can be effectively solved.

The application provides a compressor aerodynamic stability prediction method and device, the method comprising color space conversion on an initial flow field cloud image of the compressor to obtain a target flow field cloud image, wherein the target flow field cloud image comprises at least two color channels; for any pixel point in the target flow field cloud image, the gradient amplitude of the pixel point on different color channels is calculated, and a color gradient map is generated according to the gradient amplitudes of multiple pixel points; based on a preset threshold and the gradient amplitudes, the color attribute of each pixel point in the color gradient map is adjusted to obtain a color mask image; the connected region of a target color in the color mask image is determined as a target region of a shock wave, a main flow and a leakage flow interface; based on the distance between the target interface region and the blade leading edge of the compressor, a stability prediction result is generated, wherein the stability prediction result represents that the compressor is in an unstable or stable state.

This utility model discloses a high-efficiency flame-arresting and explosion-proof valve suitable for dusty gas environments, including a valve body, a valve disc, a counterweight device, and a self-locking device. The valve body includes a valve shell and a top cover plate. Inlet flanges and outlet flanges are provided on the left and right sides of the valve shell. The inner side of the inlet flange extends into the valve body and is equipped with a rubber ring. The upper side of the valve disc is welded to a rotating shaft via a rotating arm. The two ends of the rotating shaft are rotatably connected to the valve body via bearings. The counterweight device includes a counterweight, a slender rod, and a stop rod. The self-locking device is a combination of a spring pin and a locking switch. In the event of an explosion, the high-efficiency flame-arresting and explosion-proof valve provided by this utility model closes the valve disc and is locked by the self-locking device, effectively cutting off the propagation path, achieving flame arrest and explosion isolation, preventing the propagation of shock waves and flames generated by the explosion, effectively preventing secondary and multiple explosions, and effectively protecting the safety of personnel and upstream equipment.

The utility model discloses a kind of automobile A column reinforcing member based on lightweight design, it is related to the technical field of automobile parts, including external steel body, the inside of external steel body is equipped with main body reinforcing component, the inside of main body reinforcing component is equipped with energy-absorbing member, the side of external steel body away from the surface of main body reinforcing component is equipped with sound insulation cotton.The utility model can make the internal structure of automobile A column more stable by main body reinforcing component, reduce the deformation due to collision, protect front compartment safety, by energy-absorbing member, local shock wave can be offset, ensure that front compartment living space is not deformed, while the material density of energy-absorbing member is smaller, the overall weight of A column can be reduced, so as to reduce the weight of entire vehicle body, reach the effect of reducing fuel consumption, while external steel body is fixed together by hinge hole bolt and angle steel bolt, compared with general welding mode, when maintaining, avoid cutting A column, cause stress concentration of A column, affect the safety of overall A column structure.

The utility model relates to the technical field of soot blowing, in particular to a high-cleanliness shock wave soot blower which comprises a soot blower body, a bearing ring is arranged on the inner wall of an exhaust port in the soot blower body, a turning plate is hinged to the bearing ring through a torsional spring hinge, a plurality of buffering holes are formed in the bearing ring in the circumferential direction, and the buffering holes are formed in the blowing direction of airflow. The hole depth of each buffering hole is gradually reduced in the direction away from the hinged position of the turning plate and the bearing ring in the circumferential direction, sealing rings used for sealing the buffering holes are arranged on the bearing ring, a sliding plug slides in each buffering hole, a pressure spring is supported between each sliding plug and the corresponding sealing ring in a jacking mode, and the sliding plugs penetrate out of the buffering holes in a sliding mode and are used for abutting against the turning plate. The soot blower has the advantage that the possibility that impurities in the boiler fly into the soot blower, and then the cleanliness of the interior of the soot blower is affected is reduced.

The application discloses a hypersonic flow instability multi-field coupling prediction method and system, relates to the technical field of modern high-speed aircraft design, and comprises the following steps: acquiring 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 the multi-physical field parameters as input, setting graph nodes in the shock wave influence area, the boundary layer area and the intersection area thereof, and calculating the connection weight between the nodes; performing multi-scale decomposition on the instability sensitive graph data structure, and extracting instability modes of the shock wave scale, the vortex scale and the molecular scale; screening the instability modes by adopting a hypersonic stability criterion, and determining a dominant instability mode; and constructing an instability evolution prediction model based on the dominant instability mode, and outputting the spatiotemporal evolution law of the hypersonic flow instability. The application can solve the problem that the flow instability phenomenon under the complex multi-physical field environment of hypersonic speed is difficult to accurately predict.

The application relates to a Monroe-effect enhanced shock wave generating device, which comprises a tank body, one end of the tank body is provided with an inlet for mixed gas, the other end of the tank body is provided with an outlet and connected with a shock wave output end, an inner cone and an efficiency ring are arranged in the tank body, the inner cone is adjacent to the inlet, the top of the inner cone is towards the inlet and provided with a turbulence passage for the mixed gas, the efficiency ring is spaced opposite to the inner cone along the axial direction of the tank body, and the central hole of the efficiency ring is connected with the shock wave output end. In the application, the turbulence passage of the inner cone can mix the mixed gas again, the mixing degree of the mixed gas is improved, a conical cavity is formed between the inner cone and the tank body, based on the Monroe effect, the inner cone can both concentrate energy and enhance the effect and indicate the direction of the shock wave during the shock wave generating process, energy loss is prevented, and the efficiency ring cooperates with the inner cone and blocks the backflow of smoke and dust.

A supersonic diffuser for use in turbomachinery adapted to impart thermal energy to a process fluid is provided. The diffuser includes a vaned zone configured to define a passageway having a flow area to pass a flow of a process fluid at supersonic velocity. The vaned zone is configured to define a step-change to the flow area of the passageway at a given location, such as where the flow of the process fluid exits the vaned zone. The diffuser further includes a shock zone coupled to the vaned zone to pass the flow of the process fluid that exits the vaned zone. The shock zone is configured to support a system of shock waves that increases static temperature of the process fluid downstream of the system of shock waves. A mixing and subsonic diffusion is configured to decelerate process fluid from the shock zone to a reduced subsonic speed prior to discharge of the process fluid through an exit of the diffuser.

This invention belongs to the field of drilling engineering technology and discloses a continuous shock release device, including a pulse shock unit and a differential pressure unit. The upper valve of the differential pressure unit has a first state and a second state during rotation. In the first state, the upper valve covers the main hole and avoids the secondary hole, so that the mounting sleeve is under high pressure. Under high pressure, the piston assembly hammers the bottom wall of the first chamber to generate vibration. This vibration is transmitted through the cylinder assembly and the mounting sleeve to the release component below, thereby causing vibration of the fish and its stuck position. When the upper valve rotates to the second state, the upper valve covers the secondary hole and avoids the main hole, so that the mounting sleeve is under normal pressure. Under normal pressure, the piston assembly moves in the opposite direction and resets. The upper valve rotates continuously relative to the lower valve, so the piston assembly can transmit high-frequency, pulsed shock waves to the fish through the release component. The high frequency and large shock force effectively improve the success rate of release.