52 results about "Shock tube" patented technology

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 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 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.

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.

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 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.

The present application relates to the technical field of aerodynamic test, in particular to a shock tube equipment test control system and method, the system comprises: an interactive submodule, the interactive submodule comprises a remote controller for controlling the shock tube system; a detection submodule, the detection submodule comprises a non-contact acquisition unit, a schlieren unit, an optical acquisition unit and a free field unit, the non-contact acquisition unit is used for acquiring dynamic pressure changes of the model surface, the schlieren unit is used for observing flow changes of airflow affected by impact; the optical acquisition unit is used for measuring physical information of the tested model after being impacted by the explosion wave, and the free field unit is used for measuring pressure distribution at different positions of the free field; a control execution submodule, the control execution submodule is signal connected to the interactive submodule and the detection submodule. The present application solves the technical problems that the shock tube wind tunnel test in the prior art cannot realize complex timing logic and accurate synchronous control.

This invention relates to the field of shock wave pressure measurement technology and discloses a dynamic compensation method for shock wave pressure sensors based on PINN. The method includes: obtaining step response data of the pressure sensor through shock tube calibration experiments and establishing a dynamic characteristic model of the sensor; constructing a physical information neural network, embedding the sensor dynamic characteristic model as a physical layer into the network structure; designing a composite loss function including data loss terms and physical constraint loss terms, and training the physical information neural network based on simulation data; inputting the distorted pressure signal to be corrected into the trained network, and outputting the corrected shock wave pressure signal. This invention achieves signal correction without requiring precise sensor model parameters and can recover the true pressure waveform that conforms to physical laws under strong noise conditions.

The present application relates to the technical field of shock tube test device vibration reduction and noise reduction in the engineering anti-blast industry, and particularly relates to a gradient design type engineering shock tube vibration reduction and noise reduction device. The device comprises a shock tube, an injection noise elimination module and a vibration reduction and noise reduction module. The shock tube is connected to the injection noise elimination module. The vibration reduction and noise reduction module is connected to the injection noise elimination module. The shock tube, the injection noise elimination module and the vibration reduction and noise reduction module are coaxially arranged. The gradient design type engineering shock tube vibration reduction and noise reduction device provided by the present application optimizes airflow and sound wave propagation paths by gradient design, thereby effectively reducing noise and vibration generated by the shock tube during operation, while maintaining the aerodynamic performance and operating efficiency of the shock tube. The vibration reduction and noise reduction module formed by periodically arranged functional units forms an acoustic black hole structure. Compared with traditional methods, the acoustic black hole structure has better acoustic and elastic wave control physical properties, can effectively reduce the propagation speed of the shock wave, and reduce the reflection at the boundary end.

The invention relates to a test evaluation method and system for a light radiation environment of a tail flow field, and the method comprises the steps: obtaining the spectral radiation data of a visible light wave band through a ground wind tunnel test, carrying out the correlation extrapolation design of a light environment in a real flight state, and achieving the accurate prediction of the light environment of the tail flow field under a high-altitude flight condition. The difficulties that a complex radiation mechanism is not clearly known and light environment data and rules are not mastered in the current wake flow field unbalanced state are overcome, and accurate prediction of the light environment is realized; in addition, the initial value Vini of the running speed of the shock tube is required to be equal to the Tmax, so that the temperature characteristic of the gas generated by the shock tube meets the test requirements, debugging is not needed in the test process, the method flow is simpler, and the test result accuracy is higher by designing the test model to be oblique.

The invention discloses a large-size free piston high-enthalpy pulse wind tunnel plenum chamber parameter diagnosis system and method. The system comprises an ionization probe set, a shock tube or an expansion tube, a pressure sensor, a secondary film, optical glass, a spectrum diagnosis module, a detachable protection tube and a high-speed data acquisition and processing device. The shock tube or the expansion tube is connected with the plenum chamber; the ionization probe group comprises a plurality of ionization probes which are dispersed on the tube walls of different sections of the shock tube or the expansion tube to measure the incident shock wave speed; the secondary membrane is arranged at the tail end of the shock tube or the expansion tube; a pressure sensor and two pieces of optical glass which are mounted on the pipe wall of the same section are arranged in front of the second film; the pressure sensor is used for measuring the total pressure, and each optical glass is connected with a spectrum diagnosis system through a detachable protective tube; the spectrum diagnosis system is used for detecting gas components in the shock tube through optical glass; and the high-speed data acquisition and processing device is connected with all the ionization probes, the pressure sensors and the spectrum diagnosis system, and is used for acquiring and analyzing data.

A coreless shock tube system includes a bundle of coreless shock tubes, meaning the tubes are not wound on a coil. The bundle may be a cylindrical coil of shock tube. Optionally, two washer-like end plates are placed at the ends of the coil to provide axial support. Self-adhesive tape partially covers the coil and end plates. A detonator is attached to one end of the tube and is concealed within the coil, through an end plate, for storage and transport. An igniter is attached to the other end of the tube. For use, the detonator is removed from the coil and connected to an explosive device. The package is then separated from the detonator and explosive, unwinding the tube through the end plate for deployment. The igniter is then actuated to ignite the shock tube and activate the detonator and explosive.

The invention discloses a wide-range colorimetric temperature measuring device suitable for shock wave temperature measurement, which relates to the technical field of shock wave heating and dynamic temperature measurement and comprises a shock wave tube, a quartz window and a temperature measuring device. The temperature measuring device comprises a one-to-four near-intermediate infrared optical fiber, four optical filters for screening different working wavebands, four transimpedance amplification circuits, four multiple amplification circuits, a 16-channel synchronous acquisition card and an upper computer, the temperature measuring device which is simple in structure, wide in temperature measuring range, fast in response and low in cost is arranged to measure the temperature of reactants heated by shock waves, signals output by a transimpedance amplification circuit are amplified again by different amplification factors, synchronous acquisition of channel signals is achieved by applying a 16-channel synchronous acquisition card, and the temperature of reactants heated by shock waves is measured by combining a colorimetric temperature measuring technology. According to the requirement of temperature measurement, a proper radiation wave band is selected to carry out ratio calculation, so that the temperature measurement error is reduced, the measurement range is wider, and the reliability is higher.

An arming device 10, for example for use with a shock wave interrupt device or shock tube comprises a waterproof housing which includes a safety catch. When the safety catch is released, it opens a pa

The present application relates to the technical field of shock wave experiment, and discloses a multi-shock wave focusing ignition promoting experiment device and experiment method, the experiment device comprises a shock wave collision bin, a plurality of connecting ports are arranged on the side wall of the bin body, and different interval angles are arranged between the connecting ports; a shock wave tube unit, the shock wave tube unit comprises two or more double diaphragm shock wave tubes and a gas distribution assembly connected with the double diaphragm shock wave tubes; a data acquisition unit, the data acquisition unit comprises a photomultiplier tube, 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 tube and the constant current adapter; compared with the traditional single shock wave single focusing ignition mode, the multi-angle shock wave is used for mutual coupling focusing ignition, not only the relationship between the shock wave of different incident angles and the shock wave focusing can be conveniently studied, but also the structure is simple, the operability is good, the repeatability is strong, the ignition efficiency is greatly improved, and the blank of multi-shock wave coupling ignition and experiment device is made up.

The invention discloses an engine health assessment method and system based on one-dimensional shock tube flow, and relates to the technical field of engine fault intelligent diagnosis. The method comprises the following steps: acquiring the running state and corresponding running data of each device in the engine; working condition classification in the Riemann problem of the one-dimensional Euler equation is matched according to the operation state and the operation data of the device, and the working condition classification comprises strong shock waves, weak shock waves, strong expansion, weak expansion and contact interruption leading; constructing an engine state prediction model based on a depth operator network according to the working condition classification, and training the engine state prediction model by using a data set corresponding to the working condition classification; and performing health assessment on the engine device by using the trained engine state prediction model. According to the method, the flow problem of the equivalent one-dimensional shock tube is solved by using the depth operator network, so that the accurate evaluation of the health state of the engine is realized.