16results about How to "Guarantee test safety" patented technology

The invention relates to the field of aero-engine air environment simulation test equipment, and discloses a large-size thin-wall exhaust diffuser flexible connection structure, which comprises an inner cylinder, an outer cylinder and a first water guide plate, and is characterized in that the inner cylinder comprises a straight-section inner shell and a conical-section inner shell which are sequentially arranged along the airflow direction; the small-caliber end of the conical-section inner shell is smoothly connected with the outlet end of the straight-section inner shell; the first flexible connecting assembly is used for connecting the connecting plate and the straight section outer shell, the first flexible connecting assembly is fixedly connected with the first water guiding plate, the first flexible connecting assembly can absorb the axial thermal displacement difference of the straight section and the conical section of the inner barrel and the outer barrel, and the first water guiding plate is fixedly connected with the first flexible connecting assembly, so that the water guiding effect is improved; the high thermal deformation of the straight-section inner shell is transmitted to the first flexible connecting assembly, and the radial thermal displacement difference between the straight-section inner shell and the straight-section outer shell of the exhaust diffuser is absorbed, so that the thermal deformation of an inner barrel and an outer barrel of the exhaust diffuser is coordinated, and the test safety is ensured.

The invention discloses a vibration abnormity simulation test device and method for an aero-engine disc-drum type rotor system, and belongs to the technical field of aero-engine vibration simulation test. A front supporting assembly, a high-pressure compressor disc assembly, a disc-drum combined structural member and a rear supporting assembly of the device are sequentially arranged on a high-pressure turbine shaft, and the front supporting assembly is arranged on a front support assembly; the rear supporting assembly is arranged on the rear support assembly. The method comprises the steps that the high-pressure turbine shaft is connected into the driving motor through the elastic coupler; arranging a sensor for measuring abnormal vibration of the rotor system; after the device is adjusted to a preset abnormal state, the driving motor is started, and data collected by the sensor is transmitted and summarized to the computer for analysis. Compared with a real aero-engine disc-drum type rotor system, the aero-engine disc-drum type rotor system has high structural similarity and dynamic similarity, the structural design is more concise and reasonable, the vibration transmissibility is good, and the working state and the abnormal vibration characteristic of the connecting interface of the elastic supporting structural part and the disc-drum combined structural part can be simulated more truly.

The invention provides a non-power-cut test method for mutual inductance parameters of a power transmission line under excitation of different-frequency signals and a related device, and solves the problems of difficulty in accompanying stop and high safety risk of adjacent lines. The method comprises the following steps: selecting one circuit in the same corridor for power failure, connecting the head end with an induced electricity suppression device, and performing three-phase short-circuit grounding at the tail end; injecting a different-frequency sinusoidal current of 45-55Hz into the power failure line; the synchronous measurement device collects head and tail voltage and current of a running line based on a satellite synchronous clock; extracting pilot frequency signals through two-stage notch filtering and Fourier transform; and different-frequency zero-sequence self-impedance and mutual impedance are calculated and converted into power-frequency impedance. According to the invention, accurate test without power failure can be realized, and safety and power supply reliability are guaranteed.

The invention discloses a method for analyzing fluctuating wind pressure load of a wind tunnel structure based on linear regression. The method comprises the steps that fluctuating wind pressure data are obtained, the fluctuating wind pressure data comprise wind speed, peak frequency and fluctuating wind pressure, the peak frequency comprises upstream peak frequency and downstream peak frequency, and the fluctuating wind pressure comprises upstream pulsation and downstream pulsation; eliminating the fluctuating wind pressure data with error influence according to the variable coefficient and the F statistical magnitude to obtain optimized fluctuating wind pressure data; acquiring fluctuating wind pressure parameters according to the optimized fluctuating wind pressure data; obtaining a load analysis formula according to the fluctuating wind pressure parameters, wherein the load analysis formula comprises a fluctuating frequency function and a fluctuating wind pressure function; vibration loads are obtained according to the load analysis formula, the vibration loads comprise the frequency load and the wind pressure load, and the problem that in the prior art, large wind tunnel laboratory facility structure design is prone to generating a resonance phenomenon, and consequently safety risks exist in the structure is solved.

The invention relates to a prefabricated cabin type electrochemical energy storage environment simulation test device which comprises a multifunctional environment simulation test device buried underground, the multifunctional environment simulation test device comprises a box body and an environment simulation assembly arranged on the box body, and the top of the box body is opened and closed through a box door; the bridge crane is used for hoisting the prefabricated cabin type electrochemical energy storage cabin to enter and exit from the top opening of the box body; the fire-fighting assembly is used for extinguishing fire in the box body; the underground structure is adopted, the hoisting requirement of the large prefabricated cabin type electrochemical energy storage cabin can be met, fire can be extinguished timely and effectively when the energy storage battery pack is on fire accidentally in the test process, and the test safety is ensured. The multifunctional environment simulation test device is arranged underground, and the box body door is opened upwards, so that the prefabricated cabin type electrochemical energy storage cabin is convenient to hoist and carry, the carrying problem of the prefabricated cabin type electrochemical energy storage cabin is solved, and the requirement of the large prefabricated cabin type electrochemical energy storage cabin for environment simulation test is met.

The invention belongs to the technical field of helicopter tests, and discloses a device and a method for measuring power loss of an intermediate speed reducer in a helicopter ground joint test. The device comprises a decoder, an upper computer, a tail inclined shaft torque acquisition assembly and a tail horizontal shaft torque acquisition assembly. The tail horizontal shaft torque acquisition assembly is mounted on a tail horizontal shaft, acquires the torque of the tail horizontal shaft through a strain gauge and transmits the torque of the tail horizontal shaft to the decoder, and the decoder decodes data and transmits the decoded data to the upper computer; the tail inclined shaft torque acquisition assembly is mounted on a tail inclined shaft, acquires the torque of the tail inclined shaft through a strain gauge and transmits the torque of the tail inclined shaft to the decoder, and the decoder decodes data and transmits the decoded data to the upper computer; and the upper computer calculates the torque and the rotating speed of the tail horizontal shaft and the tail inclined shaft under typical working conditions according to the decoded torque data of the tail horizontal shaft and the tail inclined shaft, and further calculates the power loss.

This invention discloses a universal control interface system for converters used in AC drive system test benches, comprising a control unit, a main disconnection status signal circuit, a synchronization signal circuit, a mains current signal circuit, and a VCB enable signal circuit. The main disconnection status signal circuit includes a normally open contact status circuit, a normally closed contact status circuit, a second switch, a first rotary switch, and a second rotary switch. One end of the normally open contact status circuit is connected to multiple normally open main disconnection contacts connected in parallel, and one end of the normally closed contact status circuit is connected to multiple normally closed main disconnection contacts connected in series. The normally open contacts of the second switch are connected in parallel to the normally open contact status circuit, and the normally closed contacts are connected in series to the normally closed contact status circuit. The second rotary switch is located in the normally closed contact status circuit and is connected in parallel with one or more normally closed main disconnection contacts. This invention has advantages such as enabling interface conversion between different test bench main circuit topologies and different test samples, improving test efficiency, and enhancing the modularity of test bench design.

The invention discloses a device for measuring the internal pressure deformation of a cylinder under impact. The device comprises a shell structure, an ignition structure and a main body fixing and sealing structure, the shell structure accommodates the main body fixing and sealing structure, and the tail end accommodates the ignition structure; the ignition structure is fixed in the shell structure; the main body fixing and sealing structure is fixed in a stepped hole at the front end of an inner hole of the shell structure; gas generated after the primer is ignited enters the cylindrical sample, the inner wall of the sample expands in the radial direction under the action of impact internal pressure and axial constraint, the deformation amount is measured by the strain gauge, and an external wire of the strain gauge penetrates out of an inner hole of the shell, so that deformation data is obtained; a pressure measuring device on the shell body is communicated with the inner hole so as to measure the inner pressure; when the internal pressure is too large, the sealing piece is broken through, so that high-pressure gas escapes outwards, and overpressure protection is achieved; and meanwhile, a pressure relief bolt is arranged to ensure safety. The device can measure the deformation process of the cylinder sample under the action of different impact internal pressure levels, and can effectively ensure the test safety.

This invention discloses a test device and method for the impact performance of an engine conical wall structure, belonging to the technical field of aero-engine structural strength testing. The device includes: a hammer for generating a falling impact; a transition assembly for an interference fit connection with the front end of the conical wall structure; a bracket for a fixed connection with the rear end of the conical wall structure; a protective assembly positioned along the hammer's descent path and on the side of the conical wall structure to catch the hammer after the conical wall structure fractures; and a protective box positioned directly below the conical wall structure to receive the failed falling conical wall structure. The method includes static load calibration and dynamic impact testing steps. This invention can meet the requirements for both split and integrated installation of conical wall structures, achieving a stable connection and dual safety protection under high-energy impacts. It can simultaneously complete static load calibration and dynamic impact integrated testing, ensuring safe and reliable testing.

The present application belongs to the technical field of high-speed wind tunnel test, and discloses a high-speed transverse gas jet test device and test method. The test device comprises a test model located in the test section of a high-speed wind tunnel, the inner cavity of the test model is sequentially fixed with a balance and a support rod from front to back, the rear section of the balance is sleeved with a heat insulation sleeve, a gas generator is installed on the support rod, and the rear section of the support rod is connected with a high-speed wind tunnel support mechanism. The test device further comprises a fuel storage tank and an air storage tank which are placed outside the high-speed wind tunnel and provide fuel and air for the gas generator, and an ignition controller of the gas generator. The test method establishes a safety interlocking test timing, ensures the reliability and safety of the high-speed transverse gas jet test, provides a stable time of the hot jet of 10s order, a stable chamber pressure, non-toxic and harmless gas, can simulate the specific impulse, temperature, specific heat ratio and secondary combustion effect of the real high-speed aircraft jet gas, and has engineering practical value.

The utility model relates to the technical field of small-sized drop hammer impact test devices, in particular to a split mounting type drop hammer impact test device and a split mounting type drop hammer impact test system. The test device comprises a supporting system, and a lifting system is arranged in the supporting system; the releasing system is connected with the lifting system, the releasing system comprises a releasing grabbing clamp, a fixed steel frame and a three-pulley device, the fixed steel frame is arranged in the supporting system, the three-pulley device is arranged on the fixed steel frame, and the releasing grabbing clamp is connected with the fixed steel frame; and the hammer head and counterweight system is arranged below the release system and located in the supporting system, and the hammer head and counterweight system comprises a hammer head, a piezoelectric sensor, a counterweight steel frame and a connector. According to test requirements, hammer heads with different heights and different diameters and weights can be assembled and replaced, multiple times of impact can be completed at the same time, the working efficiency is high, and the test requirements under multiple scenes can be met.

The invention discloses a low-speed proximity electronic detonation module sliding elastic rope driving and intercepting device which comprises a testing tower and a steel cable, one end of the steel cable is fixed to the top end of the testing tower, and the other end of the steel cable is fixed to a ground fixing point; a tackle for simulating a projectile body is assembled on the steel cable, a proximity electronic detonation module with an adjustable installation angle is carried on the tackle, and different attack angles of the projectile body are simulated by adjusting the angle of the proximity electronic detonation module relative to the tackle; an elastic rope is arranged below the steel cable, the elastic rope is connected with the tackle, and the elastic rope is in a stretched state in the whole process that the tackle slides on the steel cable; an arresting cable mechanism is arranged at the lower end of the steel cable and used for arresting the tackle; and a ground effector required by the test is arranged on the ground below the steel cable, and data acquisition equipment is arranged on the ground. Lossless recovery of the electronic detonation module can be realized, and meanwhile, an initiating explosive device-free boosting mode is adopted, so that the working efficiency is greatly improved, and the test safety is ensured.

The utility model discloses an air pressure simulation device of a hydrogen fuel cell system, which relates to the technical field of hydrogen fuel cells and comprises an environment bin with an anti-explosion protective layer, and the anti-explosion protective layer is connected with the ground. A hydrogen fuel cell system is placed in the environment bin, an air inlet, a hydrogen inlet and a tail exhaust outlet are formed in the hydrogen fuel cell system, the air inlet is formed in the environment bin, the hydrogen inlet extends out of the environment bin, and the tail exhaust outlet is communicated with a tail exhaust tank located outside the environment bin; a pressure adjusting assembly is arranged on the environment bin and comprises a vacuum pump located outside the environment bin, and the vacuum pump is connected with the environment bin and the tail discharge tank so that the air pressure of the environment bin can be kept consistent with the air pressure of the tail discharge tank. According to the air pressure simulation device for the hydrogen fuel cell system, the whole hydrogen fuel cell system is placed in the environment bin, the air inlet and the exhaust outlet of the hydrogen fuel cell system are both located in the set low-air-pressure environment, and operation simulation of the hydrogen fuel cell system is more accurate.

The invention relates to the technical field of dry quenching, in particular to an experimental device and method for measuring the burn-out rate of dry quenching. Comprising a high-frequency ceramic core hearth furnace, an interface, a thermocouple and a purification mechanism, the interface is fixedly connected to the high-frequency ceramic core hearth furnace, and the functional cover plate is fixedly connected to the interface; a carbon monoxide breather pipe, a carbon dioxide breather pipe, an oxygen breather pipe and a nitrogen breather pipe which are communicated with the interior of the high-frequency ceramic core hearth furnace are arranged on the functional cover plate, and electromagnetic valves are arranged on the breather pipes; the thermocouple penetrates through the functional cover plate and is movably connected with the functional cover plate; and the purification mechanism is fixedly connected to the outer wall of the high-frequency ceramic core hearth furnace. The gas flow can be adjusted in real time according to actual circulating gas components in the dry quenching furnace, and the coke burn-out rate under the circulating atmosphere can be rapidly and accurately calculated.

The invention relates to the technical field of pile foundation engineering detection, and discloses a vacuum negative pressure loading uplift pile bearing capacity model test device, which comprises an observation model assembly, an uplift pile bearing capacity test assembly, an uplift pile bearing capacity test assembly, an uplift pile bearing capacity test assembly, an uplift pile bearing capacity test assembly and an uplift pile bearing capacity test assembly, and is characterized in that the observation model assembly comprises a model box, a soil sample and a simulated groundwater layer, sensor groups are uniformly distributed in the soil sample and are used for collecting soil pressure, pore water pressure and temperature in the soil sample; strain gauges are uniformly distributed on the model pile and used for collecting strain of the model pile; the vacuum negative pressure system is used for generating tensile force; and the traction system is used for transmitting the tensile force generated by the vacuum negative pressure system to the observation model assembly and pulling the model pile in the vertical direction to carry out an uplift bearing capacity experiment of the model pile. The tensile force generated by vacuum negative pressure is used for testing the uplift bearing capacity of the pile, the uplift bearing capacity of the pile under various complex working conditions can be tested, and even the influence of soil bodies with different properties and different water contents on the uplift bearing capacity of the pile foundation when underground water exists can be simulated.

This invention relates to an insulation support platform for frequency converters used in withstand voltage testing, belonging to the field of electrical equipment testing technology. The invention includes a platform assembly; a telescopic mounting assembly is connected to the bottom of the platform assembly, the telescopic mounting assembly including a height adjustment mechanism with at least two adjustable levels, allowing the height of the platform assembly to be adjusted in real time via the height adjustment mechanism; an insulating pad assembly is installed between the telescopic mounting assembly and the ground, the insulating pad assembly including an insulating pad body, the surface of the insulating pad body abutting against the telescopic mounting assembly having insulating protrusions, the insulating pad assembly used to block current conduction between the telescopic mounting assembly and the ground; an equipment fixing assembly for fixing the test equipment is detachably connected to the platform assembly; at least one test placement assembly for placing test items is detachably connected to the platform assembly. This invention ensures the safe and reliable conduct of withstand voltage tests.