130 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 a high-temperature and high-pressure multifunctional integrated shock tube test system, belongs to the technical field of explosion and impact dynamics tests, and aims at solving the problem that an existing shock tube is usually single in function and is only used for a simulation test of a certain function. The high-pressure section and the low-pressure section of the shock tube are both made of high-temperature-resistant nickel-based alloy, an induction heater is adopted for heating, high-pressure inert gas is filled into the high-pressure section through pressure gradients of diaphragm sets with different layers of diaphragm clamping sections, high temperature and high pressure of the high-pressure section at the temperature of 20-900 DEG C and the pressure of 0.1-50 MPa are obtained, and the high-pressure shock tube has the advantages that the high-pressure shock tube is compact in structure and low in cost. The multifunctional integrated shock tube test system can be used for researching the crushing characteristics of rock materials under the conditions of different pressures, temperatures, water contents and the like, the damage characteristics of explosion shock waves in the air to a target piece and the impact damage characteristics of a high-speed projectile body. Effective methods and means are provided for related research, and the shock tube test technology and engineering application capability are expanded. The test system is easy to implement, low in cost and multipurpose.

The invention discloses a shock wave heat loading high-temperature wind tunnel and a test method, and relates to the technical field of high-temperature wind tunnel test equipment. The shock wave heat loading high-temperature wind tunnel comprises a shock tube, a wind tunnel test system, a pressure acquisition system and an air intake and exhaust system; a high-temperature and high-pressure gas source is obtained in a secondary shock wave reflection heating mode, and the total temperature of the obtained heating gas source is higher; the high-temperature wind tunnel realizes gas heating and pressurization completely through shock wave flow, extra electric power and gas requirements are not needed, and the cost of a single test is lower; the high-temperature wind tunnel test gas is premixed, so that the components of the test gas can be accurately controlled, and the purity of the components of the test gas is ensured; the device can obtain a high-temperature high-pressure subsonic flow field and even a supersonic flow field covering wide-range working conditions, can be used for visualization test diagnosis of spray fuel atomization and spontaneous combustion processes under high-temperature crosswind, accurately characterizes physical and chemical characteristic parameters such as fuel atomization characteristics, self-ignition characteristics, flame propagation characteristics and the like, and has a wide application prospect. And test data support is provided for engine combustion chamber spray atomization combustion organization.

The invention relates to an inter-stage thermal separation equivalent simulation test method based on explosion impact, and belongs to the technical field of tests. According to a mass and energy conservation equation, an initial corresponding relation between # imgabs0 # and flow parameters is established; the advanced corresponding relation between the # imgabs1 # and the flow parameters is obtained; establishing a calculation formula of the # imgabs2 # and the # imgabs3 #; establishing a relation equation for equivalently replacing combustion of the rocket engine with explosion of the explosion shock tube; solving unknown parameters in the relation equation according to the relation equation of equivalently replacing combustion of the rocket engine with explosion of the explosion shock tube, and adjusting the parameters according to a solving result to realize a jet flow effect generated by equivalently replacing combustion of the rocket engine with explosion of the explosion shock tube; according to the invention, by modulating the initial parameters of the explosion shock tube, equivalence of pulsating pressure effects at different positions in the interstage section is realized in the process of simulating the work of the engine.

The invention relates to the technical field of vibration and noise reduction of shock tube testing devices in the engineering anti-explosion industry, in particular to a gradient design type shock tube vibration and noise reduction device for engineering. Comprising a shock tube, an injection silencing module and a vibration and noise reduction module. The shock tube is connected with the injection silencing module; the vibration and noise reduction module is connected with the injection noise elimination module; the shock tube, the injection noise elimination module and the vibration and noise reduction module are coaxially arranged. According to the gradient design type shock tube vibration and noise reduction device for engineering, airflow and sound wave propagation paths are optimized through gradient design, so that noise and vibration generated in the working process of the shock tube are effectively reduced, and meanwhile the aerodynamic performance and operation efficiency of the shock tube are kept. The vibration and noise reduction module formed by periodically arranged functional units forms an acoustic black hole structure, compared with a traditional method, the acoustic black hole structure has better acoustic and elastic wave control physical characteristics, the propagation speed of shock waves can be effectively reduced, and reflection at the tail end of a boundary is reduced.

The invention belongs to the technical field of shock tunnel tests, and discloses a test device for measuring multiple parameters in a high-enthalpy shock tunnel tube. The multi-parameter measurement test device is installed on a driven section of the shock tube and comprises a front high-pressure transition section, a high-pressure visible section and a rear high-pressure transition section which are sequentially connected from front to back through flanges. The multi-parameter measurement test device adopts built-in circular tube thick-wall optical glass to perform non-contact optical measurement, so that the pressure bearing safety is ensured, and the influence of the change of an inner flow channel on a flow field is avoided; the correction lens is arranged on the outer side of the optical glass, so that the problem of imaging distortion of the circular tube is avoided, and more effective test data is further obtained; meanwhile, the device is combined with a reserved surface laser incidence window, a line laser incidence and receiving interface, a pressure sensor interface and a heat flow sensor interface, is used for measuring multiple parameters such as a wave system structure, components, pressure and heat flow flowing in the shock tube, and has engineering practical value.

The invention discloses a strong-impact high-simulation dummy evaluation system and method. The system comprises a dummy model, a mounting base and a dummy evaluation module, the dummy model comprises a head assembly, a neck assembly, an upper trunk assembly, a left arm assembly, a right arm assembly, a hip assembly, a left leg assembly and a right leg assembly. The mounting base comprises an X-direction adjusting handle, a Y-direction adjusting handle, a Z-direction adjusting handle, a 360-degree rotation adjusting handle and a dial; the dummy evaluation module comprises a data acquisition unit (sensor) and a data analysis and processing unit, and is used for carrying out impact evaluation on the dummy model. The device and the method are suitable for test data acquisition and analysis in scenes such as coal mines, chemical environments, free field explosion impact environments and shock tube tests, and evaluation and testing of human injury conditions and protection effects of protection products (such as protection clothing and protection helmets) in strong impact environments are realized; and different types of sensors can be arranged at different parts of the dummy according to requirements so as to research the injury mechanism and the equipment protection performance.

The invention relates to an explosive wave simulation shock tube auxiliary device and a working method, and provides a large explosive wave simulation shock tube opening sparse wave dynamic elimination device and method in order to solve the problem that the accuracy of a test result is reduced due to the fact that an existing shock tube sparse wave elimination device cannot eliminate interference of sparse waves on the test in real time. The eliminating device comprises an eliminating device body (5) and a feedback control system. The eliminating device is arranged at a tube opening of a low-pressure section of the shock tube. The eliminating device comprises a frame, X fan blades arranged on the frame and Y partition plates vertically arranged, X is larger than or equal to 1, and Y is larger than or equal to 0. The fan blades are arranged in rows, the number of the fan blades in each row is equal, fan blade rotating shafts are arranged on the two sides of each fan blade, each fan blade rotating shaft is connected with one transmission structure, and each fan blade is arranged between every two adjacent partition plates or between one partition plate and the inner side wall of the frame. Each transmission structure and the corresponding fan blade rotating shaft are used for controlling the rotating angle of the corresponding fan blade.

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.

Embodiments of the disclosure are directed to a shock initiation system for initiating shock in a shock tube for demolition. In some embodiments, the shock initiation system comprises a reusable discharge unit and a replaceable shock initiation platform. The reusable discharge unit may comprise a power source, a timer, a switch, and user inputs and may function to store a time, countdown the timer, and generate and transmit an electrical energy to the replaceable shock initiation platform. The shock initiation platform may receive the electrical energy from the discharge unit overpowering a resistor disposed on the shock initiation platform. The resistor may then detonate providing an initiation shock to a proximally disposed shock tube, thereby initiating shock in the shock tube.

The invention relates to diaphragm pre-pressing forming equipment for an explosive wave simulation shock tube and blasting experiment equipment thereof, belongs to the technical field of strong dynamic load resistant safety protection engineering, and meets the requirements of diaphragm pre-pressing forming and blasting experiment for the explosive wave simulation shock tube. The diaphragm pre-pressing forming equipment comprises a medium-pressure section, a medium-pressure section support, a main barrel, a main barrel support, a diaphragm pressing ring and a pressure sensor. Two ends of the medium-pressure section are opened, and a diaphragm is mounted at one end and is compressed and mounted through a diaphragm pressing ring; the other end is connected with the main cylinder; in the medium-pressure section, the outer cylinder wall of the main cylinder is provided with a medium injection interface and a sensor interface, and the pressure sensor is connected through the sensor interface. The diaphragm blasting experiment equipment comprises diaphragm pre-pressing forming equipment, a glass light window, a temperature sensor and a camera. The device and the method are used for pre-pressing forming of the diaphragm of the blast wave simulation shock tube and analysis of the blast state of the diaphragm.

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 invention discloses an ignition experiment observation system and a use method thereof, and relates to the technical field of fuel combustion experiments.The ignition experiment observation system comprises a shock tube, one end of the shock tube is closed, the other end of the shock tube is open, and a reaction cavity is formed in the shock tube; the visual structures are arranged on the two sides of the shock tube, and the reaction cavity can be observed through the visual structures; the light source module is arranged on one side of the shock tube, and the light source module is used for emitting light into the reaction cavity; the visual module is arranged on one side of the shock tube, the visual module and the light source module are symmetrically arranged, and the visual module is used for obtaining image information in the reaction cavity. By arranging a visual structure on the side wall of the shock tube and introducing an optical schlieren visual camera technology, image data of the ignition process in the shock tube can be completely recorded, so that the position and homogeneity of the ignition in the shock tube can be accurately judged, and required data can be provided for research on heterogeneous ignition in the shock tube.

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 invention discloses a shock tube test section structure and an ignition observation system, and relates to the technical field of fuel combustion experiments.The shock tube comprises a shock tube test section body, a reaction cavity is formed in the shock tube test section body, and a butt joint structure is arranged at one end of the shock tube test section body; the butt joint structure is used for butt joint of a shock tube high-voltage driving section capable of forming shock waves; the side surface of the shock tube test section body and the other end of the shock tube test section body are both provided with the visual structures, and the visual structure located on the side surface of the shock tube test section body extends from one end of the shock tube test section body to the other end of the shock tube test section body. Visual structures are arranged on the side face and the end portion of the shock tube testing section body, the visual structures are matched with a visual module to directly shoot the fuel self-ignition combustion process of a reaction cavity in the shock tube testing section body, an image is formed, and the self-ignition process of the reaction cavity in the shock tube is recorded. And the ignition homogeneity on the radial section of the shock tube and the ignition homogeneity and the ignition position on the axial surface in the tube can be conveniently judged.

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.

The invention discloses a testing device and a testing method for a powder fuel combustion transient spectrum, and relates to the technical field of powder fuel spectrum testing. The testing device comprises a shock tube system, a multi-channel oscilloscope, a spectrometer, an I CCD detector, a pressure sensor and a multi-channel digital delay pulse generator; an optical signal generated by powder fuel high-temperature self-ignition is transmitted to an I CCD detector, the time distribution of the measured optical signal and the time distribution of the I CCD detector meet a one-to-one corresponding optical system, and transient spectral information of powder fuel high-temperature self-ignition luminescence at different time is obtained. The device can realize nanosecond-level time resolution, is suitable for a rapidly changing combustion process, can obtain high-quality transient spectrum data by combining a high-resolution spectrometer and an I CCD detector, realizes measurement of a high-resolution transient spectrum of high-temperature self-ignition combustion of the powder fuel, and can be widely applied to transient spectrum measurement of the powder fuel.

The invention relates to the technical field of shock wave experiments, and discloses a multi-shock wave focusing ignition promotion experiment device and method, the experiment device comprises a shock wave collision bin, the side wall of the bin body is provided with a plurality of connecting ports, and the connecting ports have different interval angles; the shock tube unit comprises two or more double-membrane shock tubes and gas distribution assemblies connected with the double-membrane shock tubes; the data acquisition unit comprises a photomultiplier, a plurality of pressure sensors, a constant current adapter electrically connected with the pressure sensors, and a data processing system electrically connected with the photomultiplier and the constant current adapter; compared with a traditional single-shock-wave single-set focusing ignition mode, multi-angle shock wave mutual coupling focusing ignition is utilized, the relation between shock waves of different incident angles and shock wave focusing is conveniently researched, the structure is simple, operability is good, repeatability is high, the ignition efficiency is greatly improved, and the blank of multi-shock-wave coupling ignition and experimental devices is filled up.

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.