83 results about "Shock tube" patented technology

The invention discloses an underwater explosion impact equivalent loading test device and method, and belongs to the technical field of dynamic impact test mechanics, the underwater explosion impact equivalent loading test device comprises a light gas gun system, a combined water shock tube system and a measurement control system, the light gas gun system is a shock wave load loading system of a water shock tube, and the combined water shock tube system is connected with the measurement control system. Comprising a piston, a working table support, a steel pipe, a pressure sensor, a connecting flange, a connecting assembly, a transparent pipe, a double-thread screw assembly, a front panel, a test sample, a rear panel, a working table fixing support and a working table top, and a measurement control system comprises a light gas gun pressurization and emission controller, a high-speed acquisition instrument, a first high-speed camera and a second high-speed camera. The underwater explosion impact equivalent loading test device and the underwater explosion impact equivalent loading test method are compact in structure, convenient to use and suitable for researching underwater dynamic impact protection performance and fluid-solid coupling mechanism of materials or structures in laboratories.

The invention discloses an underwater explosion near-field shock wave indirect measurement device in a limited space, a measurement method and an installation method, belongs to the technical field of explosion shock wave load measurement, and solves the technical problem that near-field shock wave measurement and free-field shock wave decoupling measurement cannot be realized due to direct action of strong shock waves and interference of reflected waves in the prior art. The device is of a shock tube type structure and comprises a measuring structure head round tube, a measuring structure tail round tube, a sensor tail bypass extension round tube, a sensor head bypass extension round tube, an underwater explosion free field sensor, a sensor tail bypass round tube and a sensor head bypass round tube. And the tail part of the underwater explosion free field sensor extends into the sensor tail part bypass extension circular tube, and the head part of the underwater explosion free field sensor extends into the sensor head part bypass extension circular tube. The method is suitable for the field of impact measurement of underwater explosion and can be applied to the field of performance evaluation of underwater explosion sources.

The invention relates to an explosion experiment device, in particular to a shock tube based on a different-material double-diaphragm membrane breaking structure and a design method and an experiment method thereof, and aims to solve the problem that the performance of generated shock waves is affected by a valve structure, a pressure membrane breaking structure and a cutting membrane breaking structure of an existing shock tube. The shock tube is formed by matching the metal diaphragm and the plastic diaphragm, and the diaphragm breaking pressure can be accurately controlled. The design method comprises the steps that firstly, an experiment is conducted to obtain the relation between the plastic diaphragm rupture pressure and the plastic diaphragm thickness and the relation between the metal diaphragm rupture pressure and the metal diaphragm thickness, then the thickness of the plastic diaphragm and the notch depth of the metal diaphragm are determined, and then the length and the inner diameter of a pressure difference control section cylinder and the installation position of the diaphragm are determined; and finally, estimating the gas flow coefficient Kv of the exhaust pipe, and comprehensively designing parameters of the exhaust pipe and the electromagnetic valve. The shock wave performance and parameter precision generated by the experiment method are high.

The application discloses a shock tube experimental device which can realize switching of a high-pressure ignition experimental system and a single-pulse cracking experimental system; when the shock tube experimental device is used as the high-pressure ignition experimental system, the device comprises a shock tube body which comprises a high-pressure section, an intermediate section and a low-pressure section, and further comprises a two-way section, wherein the two-way section is connected with the intermediate section and the low-pressure section through flanges; a pre-gas distribution system which comprises an oxidant gas cylinder, a diluent gas cylinder and a gas mixing cylinder; a vacuum and pressure supply system which comprises a vacuum pump, a gas extraction pump and a driving gas cylinder, wherein the vacuum pump and the gas extraction pump are used for extracting the shock tube body into a vacuum environment; and the driving gas cylinder is connected with the high-pressure section and the intermediate section through a pipeline; when the shock tube experimental device is used as the single-pulse cracking experimental system, a three-way section and a gas exhaust tank are used to replace the two-way section on the basis of the above structure, wherein the three-way section is connected with the intermediate section, the low-pressure section and the gas exhaust tank through flanges.

The invention relates to a shock tube vibration and noise reduction performance improving device for engineering, and belongs to the technical field of engineering anti-explosion tests. A shock tube of the device is coaxially connected with a fragment filtering module, a to-be-tested piece is arranged between the shock tube and the fragment filtering module, and the fragment filtering module is coaxially connected with a vibration and noise reduction performance improving module; high-pressure shock waves are emitted from the shock tube to crush a to-be-tested piece, and fragments of the to-be-tested piece and the decelerated shock waves are attenuated and dispersed after passing through the fragment filtering module and the vibration and noise reduction performance improving module. According to the shock tube vibration and noise reduction performance improving device for the engineering, vibration and noise reduction of the shock tube for the engineering under compressed air explosion are achieved, the shock tube vibration and noise reduction performance improving device can be used for vibration and noise control of a large indoor shock tube test, and operability is high.

The present application relates to a kind of calibration device and calibration method of shock wave overpressure optical measurement system based on shock tube, it is related to the field of shock wave overpressure test, wherein the calibration device includes: standard shock tube, visible measuring unit;Visible measuring unit includes: transparent quartz tube, first piezoelectric sensor, second piezoelectric sensor, third piezoelectric sensor;Transparent quartz tube one end opening, the other end is closed and is arranged;In the direction from the opening end of transparent quartz tube to closed end, first piezoelectric sensor and second piezoelectric sensor have interval and are embedded in the side wall of transparent quartz tube;Third piezoelectric sensor is embedded in the center of the closed end of transparent quartz tube.This scheme can simply, reliably produce theoretical solvable or accurately measured impact wave overpressure of various shock waves propagation process, can accurately and reliably cross-verify and error determination to the impact wave overpressure obtained in optical measurement process, can accurately calibrate the system error of optical observation wave front propagation process.

The present application relates to a kind of adjustable waveform, amplitude and duration of pulse excitation device and method, belong to pulse excitation generator technical field, solve the technical problem that pulse excitation device waveform and duration cannot be adjusted, its pulse excitation device includes supply system and shock tube, supply system includes gas source, pressure reducing valve, third steady pressure sensor, high-pressure gas exported from gas source enters shock tube by pressure reducing valve.Shock tube includes shock tube main body, diaphragm, first dynamic pressure sensor, second dynamic pressure sensor, shock tube can also include piston, baffle.Pulse excitation method is according to the state that shock tube has piston and has no piston, generates pulse excitation, including pulse excitation waveform adjustment, pulse excitation duration adjustment, pulse excitation amplitude adjustment.The present application is used in the situation that combustion chamber pressure is lower, and pulse excitation is generated in combustion chamber.

The application discloses a protective device for the head and chest of a rat, which comprises a supporting frame, a protection mechanism and a binding assembly. The supporting frame comprises a supporting plate, the front surface of the supporting plate is provided with a plurality of arrayed containing grooves, each containing groove is provided with the protection mechanism, the protection mechanism comprises a head protection arc plate, a chest protection arc plate and a plurality of locking assemblies, the bottom side edge of the head protection arc plate is provided with a first protection flat plate, the bottom side edges of the chest protection arc plate are provided with second protection flat plates, the first protection flat plate and the second protection flat plate are detachably installed on the supporting plate through the locking assemblies, and each containing groove is connected with the binding assembly for binding the limbs of the rat. The protective device is used for installing the head protection arc plate or the chest protection arc plate on the supporting plate through the locking assemblies, protecting the head or the chest of the rat separately, and then using a shock tube to perform independent impact injury tests on the head and the chest of the rat, so that the accuracy of experimental data is improved.

The invention relates to a shock tube detonation test visualization device and a test method thereof, and the device comprises a shock tube which is sequentially divided into a premixing section, a detonation section, a development section and a measurement section along the axial direction, and the measurement section is provided with a plurality of optical visualization windows; the gas distribution ignition system is used for filling combustible premixed gas into the shock tube and generating a controllable ignition source at the detonation section; the synchronous signal acquisition system is used for acquiring a flame front position signal in the shock tube in real time; the schlieren system is used for acquiring a two-dimensional transient density gradient field of the shock wave and the flame front; the laser-induced fluorescence system is used for carrying out two-dimensional plane laser-induced fluorescence imaging on the flame reaction area; the high-speed photographing system is used for recording the overall propagation process of the flame in the shock tube; and the smoke grain acquisition unit is used for forming a smoke film on the inner wall of the measurement section to capture and retain the detonation cell structure. Compared with the prior art, the detonation wave three-dimensional structure and array surface change characteristics can be captured and observed at the same time through one detonation test.

A storm shutter system for integration into a window or door frame includes a shutter frame having a vertical aluminum tube frame and one or more shutter tracks configured to guide movement of a storm shutter. An aluminum box is connected to the top of the vertical aluminum tube frame and includes a hood defining an interior space that houses a rod for rolling and storing the storm shutter. A slat anti-shock tube is formed integrally with and positioned beneath the hood, the tube including three edges arranged at right angles and one rounded edge corner that defines a transition region where the storm shutter enters the hood during rolling operation. The rounded edge corner reduces vibration and noise and inhibits entry of debris or water into the hood. A roll-up mechanism within the aluminum box rotates the rod to move the storm shutter between open and closed positions.

The invention discloses a boron-aluminum mixed powder ignition characteristic testing system and method based on a shock tube, and the system comprises the shock tube, a gas distribution unit, a powder dust raising unit, and a signal collection unit. The gas distribution unit comprises a vacuum pump and a driving gas cylinder, and the vacuum pump is connected with the shock tube through an exhaust tube and used for vacuumizing the shock tube; the driving gas cylinder is connected with the shock tube through a gas filling pipeline and is used for filling high-pressure driving gas into the driving section and filling low-pressure test gas into the test section; the powder dust raising unit comprises a high-pressure air tank, and the high-pressure air tank is connected with the spray head through a high-pressure pipeline and used for spraying boron-aluminum mixed powder stored in the spray head into the experiment section to form a boron-aluminum mixture cloud cluster; and the signal acquisition unit is used for acquiring reflected shock wave signals and image data in the experimental section. The non-contact high-response synchronous measurement of the pressure sensor and the photoelectric sensor is realized, the real time interval from shock wave compression to chemical reaction luminescence can be directly obtained, and the test data is accurate and reliable.

The application discloses a large-size free piston driven high-enthalpy pulse device, and relates to the field of wind tunnel test. The device contains four operation modes, i.e. a high-total-pressure high-enthalpy reflection type shock tunnel, a low-dissociation high-enthalpy straight-through type shock tube, an ultra-high-speed expansion tube and an ultra-high-speed expansion wind tunnel. The four operation modes expand the flight envelope simulated by the wind tunnel, so that the flight environment with extremely high dynamic pressure, extremely high temperature, extremely high speed and extremely high brightness can be simulated for a long time. The application not only can simulate the flight environment in a wide area and extremely high speed, but also can provide high-quality wind tunnel test aerodynamic data for aircraft development, and expand the test capacity of the high-enthalpy pulse device.

The application relates to the technical field of fluid mechanics test devices, and provides a shock tube driven pipe tunnel flow pulse direct connection test device and method. The shock tube driven pipe tunnel flow pulse direct connection test device comprises a shock tube main body, a separation assembly, a test section assembly, a vacuum chamber, a parameter measurement assembly and a driving gas control assembly. The shock tube driven pipe tunnel flow pulse direct connection test device can reproduce pipe tunnel through flow and full working condition flow, accurately simulate a wide speed range pipe tunnel aerodynamic environment, generate controllable uniform test airflow through pulse driving of the shock tube, and realize the invention purpose of low-cost and high-fidelity pipe tunnel flow characteristic and vehicle aerodynamic performance test through cooperation of multiple assemblies and a multi-dimensional parameter measurement system. In addition, the application further provides a method applied to the shock tube driven pipe tunnel flow pulse direct connection test device.

A shock wave converging device for a chemical shock tube, and a chemical shock tube. The device comprises at least one shock wave converging tube (100). The shock wave converging tube (100) comprises: a first conversion tube (110), wherein an input end of the first conversion tube (110) is connected to a driven section, the first conversion tube (110) is configured to convert, when an incident shock wave is inputted at the driven section, the incident shock wave into an oblique shock wave, and the projection of an inner wall of the first conversion tube (110) on a target plane is a concave curve; an oblique straight tube (120), wherein an input end of the oblique straight tube (120) is connected to an output end of the first conversion tube (110), the oblique straight tube (120) is configured to perform shock wave enhancement processing on the oblique shock wave to obtain an enhanced shock wave, and the projection of an inner wall of the oblique straight tube (120) on the target plane is an oblique line segment; and a second conversion tube (130), wherein an input end of the second conversion tube (130) is connected to the oblique straight tube (120), the second conversion tube (130) is configured to convert the enhanced shock wave into a parallel shock wave, and the projection of an inner wall of the second conversion tube (130) on the target plane is a convex curve.

The application relates to a portable shock tube device with one-way reflection and a one-way reflection control method. The device comprises a tube structure with a first cavity and a second cavity; a film structure clamped between the first cavity and the second cavity; a film breaking structure capable of connecting the first cavity and the second cavity to form a channel for shock wave propagation; a detection structure for detecting a shock wave; a pressure relief structure comprising a high-speed electromagnetic direct discharge valve and a throttle orifice plate arranged in series along an exhaust direction; the effective flow area of the high-speed electromagnetic direct discharge valve is larger than the opening area of the throttle orifice plate; the film breaking structure is configured to puncture the film structure and trigger communication with the external atmosphere at the same time, so that the pressure of the first cavity and the second cavity tends to be consistent, and the pressure relief rate of the first cavity is determined by the opening area of the throttle orifice plate, thereby avoiding the influence of dynamic errors such as mechanical inertia, hysteresis, valve core shaking and the like on the pressure relief stability during the opening process of the high-speed electromagnetic direct discharge valve, and ensuring the consistency of the pressure relief rate of each test.

Hydraulic damper assembly (100), comprising: a housing (104) with an interior (108), a first end (112) and a second opposite end (116), wherein the first end is configured for attachment to a fixed support and the second end is configured for attachment to a structure under load; a hollow cylindrical shock tube (148) arranged axially inside the housing interior (108); a piston assembly (128) which is axially movable within the interior of the hollow cylinder (148), wherein the piston assembly (128) comprises a piston (136) and a piston rod (132) extending from the second end of the housing (104), wherein the piston (136) defines variably dimensioned adjacent chambers (210, 218) within the hollow shock tube (148), each chamber (210, 218) being filled with a hydraulic fluid; a first end arrangement (156) sealed at the first end (112) of the housing (104) and a second end arrangement sealed at the second end (116) of the housing (104), wherein the second end arrangement comprises a sealed opening through which the piston arrangement (128) is slidably moved; a fluid circuit comprising fluid passages defined in the first end arrangement (156) and the second end arrangement, and a tubular element arranged axially between an outer surface of the hollow cylindrical shock tube (148) and an inner surface of the housing (104), wherein the passage (184) in the end arrangement (156) is further connected to a lateral passage (176) connected to a passage (170) extending into the chamber (218), wherein the fluid circuit connects each of the adjacent chambers (210, 218) to each other and is configured to move the fluid between the chambers (210, 218) in accordance with the movement of the piston arrangement (128) under load; an accumulator (150) arranged in an accumulator surrounding at least a section of the outer surface of the cylindrical tube within a defined space, wherein the end arrangement (156) further comprises an axial passage (190) formed therein, which is fluidically connected to a lateral passage (194) which is connected to the space holding the accumulator (150); and a locking arrangement arranged within the end arrangement (156), wherein the locking arrangement comprises a locking pin (180) and a locking pin (197), the locking pin (180) being arranged in the lateral passage (176) and having a tapered section (182) dimensioned such that the axial passage (170) can be completely closed by the locking pin (180) when the locking pin (180) is adjusted accordingly by a user, and the locking pin (197) being arranged in the lateral passage (194) and having a tapered section (201) dimensioned such that the axial passage (190) can be closed by the locking pin when the locking pin (197) is adjusted accordingly by a user.

The invention relates to an off-line calibration method for the dynamic characteristics of a shock wave pressure sensor, and the method comprises the steps: enabling a standard shock wave pressure sensor and a calibrated shock wave pressure sensor which is verified to be qualified through static metrology to be commonly and symmetrically installed on the end face of a low-pressure region of a calibration shock wave tube, and connecting a correctly-arranged test system; starting a shock tube calibration program to apply a standard step shock wave excitation signal to the two, recording output of the two to obtain discrete time sequence data, and calculating a frequency response function ratio of the two data to obtain a calibration factor frequency response function; and after the test, calibrating original test data obtained by the test of the calibrated shock wave sensor to obtain final test data, preliminarily confirming a shock wave pressure peak value in the final test data, and obtaining final test shock wave pressure peak value data according to the known overshoot of the standard shock wave pressure sensor. The method can effectively improve the accuracy and consistency of shock wave overpressure peak test data in the test.

The utility model belongs to the technical field of high-temperature flow field pressure testing, and discloses a water-cooled wall surface static pressure probe provided with multiple cooling loops and used for measuring a high-temperature flow field of an aero-engine combustion chamber. The device is characterized by comprising a pressure sensing hole, a fixed external thread, an octagonal prism positioning block, a fixed internal thread, a sensor mounting cavity, eight water outlet channels and eight water inlet channels. Compared with an existing water-cooling pressure probe, the probe can measure the wall surface static pressure of a flow field under the condition that the interference on the flow field is as small as possible, and meanwhile, the water-cooling pressure probe can adjust the cooling effect of each area of the probe. When the wall surface static pressure of a high-temperature flow field of a combustion chamber of an aero-engine is actually measured, the water-cooled wall surface static pressure probe is fixed in a static pressure hole which is formed in the wall surface of the combustion chamber in advance, a pressure sensor is mounted in the probe, and the water-cooled wall surface static pressure probe can measure the wall surface static pressure in the combustion chamber in a 2500K high-temperature environment through the calibration of a shock tube. And the frequency response of the probe exceeds 80 kHz.

The present application belongs to the technical field of shock wave test, and relates to a single soldier equipment shock wave test device and method based on equivalent simulation of a shock wave tube. The test device comprises a computer, a dynamic signal test analysis system, an initiator and a dynamic pressure sensor. A bore is arranged at the front end of the initiator, the bore is filled with gunpowder and an electric control firing device is installed, and the rear end of the initiator is connected to a shock wave propagation system. The test method comprises the following steps: assembling the test device, filling the bore with gunpowder after selecting a shock wave driving mode, presetting the initiation mode of the electric control firing device, starting the computer and the dynamic signal test analysis system, controlling the electric control firing device to initiate according to the preset initiation mode, collecting electric signals by the dynamic pressure sensor, analyzing and processing the electric signals by the computer, manually observing the damage condition of the test product, and obtaining the shock wave protection efficiency test result of the single soldier equipment. The present application directly drives by gunpowder explosion, integrates three initiation driving modes, and realizes a small-sized and low-interference test device.

The present invention discloses a double-piston shock tube, which comprises an experimental section, a low-pressure section and a high-pressure section connected in sequence; the high-pressure section includes a high-pressure cylinder and a vacuum cylinder. An anti-high-pressure tube is provided in the high-pressure cylinder, and an anti-low-pressure tube is provided in the vacuum cylinder. One end of the anti-low-pressure tube is communicated with one end of the anti-high-pressure tube, and a solenoid valve is provided at the other end of the anti-low-pressure tube. The anti-low-pressure tube is also connected to a gas driving cylinder outside the vacuum cylinder, and the inner cavity of the vacuum cylinder is also connected to an air pump; a main piston is provided at the other end of the anti-high-pressure tube, and a sub-piston is further provided in the inner cavity of the anti-high-pressure tube to divide the inner cavity of the anti-high-pressure tube into a first cavity and a second cavity. The first cavity and the second cavity are communicated through a pipeline, and the second cavity is provided with a through hole communicated with the inner cavity of the high-pressure cylinder, and the second cavity is also communicated with the inner cavity of the vacuum cylinder; an impact receiving block is provided on the inner wall of the high-pressure cylinder at the end connected to the low-pressure section, the impact receiving block is opposite to the main piston, and the inner cavity of the high-pressure cylinder is also connected to a high-pressure pressure gauge. The shock wave generated by this shock tube is pure, the cooling time is short, and the experimental efficiency is high.

This invention discloses a high-temperature wind tunnel and testing method under shock wave thermal loading, relating to the technical field of high-temperature wind tunnel testing equipment. The method includes: a shock tube, a wind tunnel testing system, a pressure acquisition system, and an intake and exhaust system. It utilizes secondary shock wave reflection heating to obtain a high-temperature, high-pressure gas source, resulting in a higher total temperature of the heated gas source. The high-temperature wind tunnel achieves gas heating and pressurization entirely through shock wave flow, requiring no additional electricity or fuel gas, thus reducing the cost per test. The high-temperature wind tunnel test gas is premixed, enabling precise control of the test gas components and ensuring their purity. This invention can obtain high-temperature, high-pressure subsonic flow fields and even supersonic flow fields covering a wide range of operating conditions. It can be used for visual testing and diagnosis of fuel atomization and auto-ignition processes under high-temperature crosswinds, accurately characterizing physicochemical parameters such as fuel atomization characteristics, auto-ignition characteristics, and flame propagation characteristics, providing experimental data support for the combustion organization of engine combustion chamber atomization.

The invention provides a test system and method for simulating turbulence and sonic boom interference based on a small shock tube, and belongs to the technical field of sonic boom ground simulation tests. The objective of the invention is to solve the problem that a simulation result is deviated from reality due to the fact that an acoustic explosion model does not simulate an atmospheric turbulence environment in the prior art. A high-voltage system, a high-voltage driving section, a double-film section, a low-voltage driven section and a vacuum system are connected in sequence, and a speed measurement piezoelectric sensor is installed on the side wall of the low-voltage driven section; the grid turbulence disturber is arranged on the side wall of the low-pressure driven section; the turbulence control system is connected with the grid turbulence disturber; the hot-wire probe is arranged at the front end of the hot-wire anemometer and is arranged on the side wall of the low-voltage driven section; the test board is provided with a PSP coating, and the test board, the schlieren high-speed camera and the PSP high-speed camera are all mounted on the side wall of the low-voltage driven section; the test board is provided with a high-frequency pressure sensor. The problem that in the prior art, a sound explosion model does not simulate the atmospheric turbulence environment, and consequently the simulation result deviates from the reality is solved.

The utility model relates to an auxiliary device for simulating a shock tube by explosive waves, in particular to a shock tube sparse wave eliminating device capable of weakening self-reflected waves, and aims to solve the problem of inaccurate experimental data caused by the fact that sparse waves generated at the orifice of a shock tube are transmitted back to the upstream during an experiment. The device comprises a circular wave absorbing plate arranged at a tube opening of an explosive wave simulation shock tube; a central wave absorbing hole and at least three edge wave absorbing holes are formed in the wave absorbing plate; the central wave absorbing hole is located in the center of the wave absorbing plate, and the at least three edge wave absorbing holes are evenly distributed around the circumference of the central wave absorbing hole. The utility model can effectively weaken the peak value of the backflow reflection wave of the shock wave in the experiment and improve the experiment precision.

This invention relates to a shock tube gas distribution method and system. During shock tube experimental gas preparation, a gas distribution column and a mixing tank are used in conjunction to actively control the internal pressure of the gas distribution column. An additional pressure-reducing stage is added between the gas cylinder and the mixing cylinder. The gas distribution column buffers large fluctuations in gas flow and pressure, resulting in a more stable gas flow and significantly improving the accuracy of the experimental gas component ratio. Simultaneously, the mixing tank has only one inlet connecting to the gas distribution column and one outlet connecting to the shock tube, improving the tank's strength and pressure-bearing capacity, and enhancing gas distribution safety.

The invention discloses a methane in-situ burning explosion fracturing system and method based on shock wave ignition. A shock wave tube assembly comprises a pressure-bearing tube body; the first clamping device and the second clamping device clamp the first diaphragm and the second diaphragm in the pressure-bearing pipe body. The gas filling assembly comprises a high-pressure gas tank, and a high-pressure gas supply pipeline and a double-membrane gas supply pipeline which are connected with the high-pressure gas tank are respectively communicated with the high-pressure cavity and the double-membrane cavity The exhaust assembly comprises a vacuum pump, a vacuumizing pipeline connected with the vacuum pump communicates with the high-pressure cavity and the double-film cavity through a first communicating pipeline and a second communicating pipeline correspondingly, and a double-film air leakage pipeline communicates with the second communicating pipeline. The methane burning explosion packing unit is a packer arranged on the pressure-bearing pipe body in a sleeving mode. The combustion improver conveying unit comprises an oxygen bottle, and an oxygen conveying pipeline connected with the oxygen bottle is communicated with the combustion explosion chamber; the combustible gas concentration detector is positioned on the oxygen conveying pipeline; the method comprises the following steps: assembling and lowering the shock tube assembly; the high-pressure and double-film cavity is vacuumized; filling gas; the pressure is quickly released; and the generated shock wave is used for igniting and expanding into burning explosion. The device is high in ignition energy and ideal in burning and explosion effect.

The application discloses a two-stage shock tube type device for simulating a far-field large equivalent and large pulse width impact load under deep water, a design method and a simulation method. A first end of an explosion chamber (1) is provided with an explosion chamber hatch cover (2), the explosion chamber (1) is communicated with a model load receiving chamber (7) through a detachable short pipe (5), a first-stage shock tube (3) and a second-stage shock tube (6), a hollow partition plate (4) is arranged in the explosion chamber (1), the hollow partition plate (4) is fixed with the first-stage shock tube (3), and a tail end of the model load receiving chamber (7) is provided with a model load receiving chamber hatch cover (8). The explosion chamber (1) and the model load receiving chamber (7) are provided with a plurality of water injection and pressurization pipes (9) and water drainage and pressure relief pipes (10) for water injection and pressurization and water drainage and pressure relief. The application is used to solve the problem that the existing device cannot effectively, controllably and practically realize the simulation of a large equivalent and large pulse width explosion impact load under deep water through a small equivalent explosion source.

The application discloses a kind of traceable pressure sensor dynamic response calibration method based on absorption spectrum reference pressure input, in shock tube is driven section tail end wall position arrangement to be calibrated pressure sensor, and set optical measurement window in reflected shock action area, synchronous acquisition pressure sensor output signal and absorption spectrum signal;Absorption spectrum signal is preprocessed and spectral line fitting, calculate the gas temperature and collision broadening coefficient after reflected shock wave, and reference pressure amplitude P5 after reflected shock wave is obtained accordingly;Pressure amplitude P1 before incident shock wave is measured using pressure gauge after metrological calibration;According to P1, P5 and pressure mutation time t0 Reference pressure step input signal based on Heaviside step function is constructed;Reference pressure step input signal and pressure sensor output signal are processed, and the ratio of the spectral amplitude of the two is used as the sensitivity of the pressure sensor at the corresponding frequency;Error source in the process of calculating reference pressure amplitude, pressure mutation time and sensitivity is evaluated and calculated, and the sensitivity calibration result of pressure sensor is obtained.The application can obtain the sensitivity characteristics and its uncertainty of pressure sensor.

The utility model provides a kind of multi-channel electric shock tube belongs to biological medical instrument and equipment technical field.It solves the problem of lower efficiency of the existing electric shock tube experiment.This multi-channel electric shock tube, including a plurality of sample containment tube made of insulating material, its multiple sample containment tube is fixed as a row, sample containment tube has first end opening and second end opening, multi-channel electric shock tube further includes first electrically conductive material piece, cover and second electrically conductive material piece, first electrically conductive material piece will sample containment tube first end opening block, cover is covered on sample containment tube when second electrically conductive material piece will sample containment tube second end opening block.This multi-channel electric shock tube is experimented synchronously by multiple sample containment tube, and improves experimental efficiency.

The application discloses a coaxial cylindrical detonation driving device for a shock tube / wind tunnel and a method thereof, which comprises a detonation driving section, one end of the detonation driving section being communicated with a driven section, the other end of the detonation driving section being connected with a blind plate, and a diaphragm being arranged between the detonation driving section and the driven section; the detonation driving section is inserted with a first electrode and a second electrode extending in a radial direction, and an ignition wire extending in an axial direction is electrically connected between the first electrode and the second electrode; the application further comprises a discharge system, the discharge system comprising a high-voltage capacitor, an ignition switch and a unloading switch, an ignition circuit being formed by a positive electrode of the high-voltage capacitor, the ignition switch, the first electrode, the ignition wire, the second electrode and a negative electrode of the high-voltage capacitor, an unloading circuit being formed by the positive electrode of the high-voltage capacitor, the unloading switch and the negative electrode of the high-voltage capacitor, and the ignition circuit and the unloading circuit being connected in parallel. In the application, detonation is replaced by deflagration, and there is no pressure peak in detonation, so that the combustion pressure can be 100% used for compressing test gas, and therefore the pressure of the test gas is improved.

A kind of methane in-situ combustion fracturing system and method based on shock wave ignition, system: shock tube assembly includes pressure-bearing pipe body;Clamp one and two are clamped in diaphragm one and two inside pressure-bearing pipe body;Gas filling assembly includes high-pressure gas tank, high-pressure and double-membrane gas supply pipeline connected with high-pressure gas tank respectively communicate high-pressure and double-membrane chamber;Exhaust assembly includes vacuum pump, vacuum pump connected with the vacuum pumping pipeline is communicated with high-pressure and double-membrane chamber through communication pipeline one and two respectively, double-membrane exhaust pipeline is communicated with communication pipeline two;Methane combustion and explosion packer unit is the packer of being installed on pressure-bearing pipe body;Combustion-supporting agent delivery unit includes oxygen cylinder, oxygen delivery pipeline connected with oxygen cylinder communicates combustion chamber;Combustible gas concentration detector is located on oxygen delivery pipeline;Method: shock tube assembly is assembled and is lowered;High-pressure and double-membrane chamber is vacuumized;Gas is filled;Fast pressure relief;The shock wave generated is ignited and expanded into combustion and explosion.The ignition energy of the present application is high, and the combustion and explosion effect is ideal.