87 results about "Helium cylinder" patented technology

The invention relates to a new method and a testing device for characterizing a PCT (percent) curve of hydrogen absorption and desorption of a hydrogen storage material. The testing device adopts the technical scheme that a high-pressure hydrogen cylinder and a high-pressure helium cylinder are connected with a filter by a reducing valve (3) and a reducing valve (4) and are connected with a valve (7) and a valve (14) by a valve (6) respectively; the valve (7) is connected with a mass flow control meter (8) and a valve (9); the valve (14) is connected with a pressure sensor (13) and a valve (12), is connected with a valve (10) in parallel, and is connected with a vacuum pump (11); a sample room (18) is connected with a filter (16) and a valve (15) and is connected with a gas circuit between the valve (14) and the valve (12) by a cross joint; a main body part of a testing system is placed in a thermostat (23); the sample room (18) is sheathed and connected with a heating jacket (19); a photoelectric isolation driver module (25) is connected with a data acquisition card (24); and the data acquisition card (24) is connected with a computer (26). With the adoption of the new method and the testing device, the defects such as errors, unbalance and low precision are overcome. The new method and the testing device are accurate and convenient to operate.

The invention provides an accumulator ultralow-temperature leak test device and method. The device is mainly composed of a vacuum leak test box for containing an accumulator, a liquid nitrogen low-temperature dewar flask connected with the vacuum leak test box through a pipe with a stop valve, a helium cylinder, a nitrogen cylinder, a vacuum pump, a compressed air source, a pressure gauge located in the vacuum leak test box, a temperature sensor, a sealing tool for vertically sealing the accumulator, a glove operation connector located on a box body and the like. The sealing tool is provided with three holes, namely a liquid nitrogen injection opening, a liquid nitrogen discharge opening and a helium injection opening, and the three holes are connected into the external liquid nitrogen low-temperature dewar flask, a safety discharge region and the helium cylinder through inside-outside connection pipes of the vacuum leak test box respectively. Furthermore, the vacuum leak test box is further provided with a helium mass spectrometer access opening, one end of the helium mass spectrometer access opening is connected with an external helium mass spectrometer, and the other end of the helium mass spectrometer access opening is located in a suction cavity in the helium mass spectrometer. By means of the accumulator ultralow-temperature leak test device, ultralow-temperature leak test can be conducted on the accumulator conveniently.

The invention discloses a cold helium heating and pressurizing system and method for a rocket oxygen tank. The cold helium heating and pressurizing method for the rocket oxygen tank comprises the steps that a certain number of cold helium cylinders are placed in the liquid oxygen storage tank, helium in the cold helium cylinders enters a gas pillow of the liquid oxygen storage tank after passing through a filter, an electromagnetic valve, a pressure reduction device, a throttling ring and a heater, and then liquid oxygen is pressurized. The cold helium heating and pressurizing system and method for the rocket oxygen tank have the advantages that helium in the cold helium cylinders enters the gas pillow of the liquid oxygen storage tank after being filtered, decompressed and heated, so thatliquid oxygen is pressurized, and the requirement for the pressure at an inlet of an engine is met. Through reasonable design of the cold helium heating and pressurizing system, it is ensured that under the normal operating condition of the cold helium heating and pressurizing system, the self weight of the heating and pressurizing system can be reduced, meanwhile, the effective utilization rateof helium can be increased, the carrying capacity of a rocket is improved accordingly; and meanwhile, the heating and pressurizing system has high safety and reliability.

The invention discloses a measuring device for core porosity. The measuring device comprises a helium cylinder tank, a pressure reducing valve, a sample chamber, a reference chamber, a pressure sensor, a digital display meter, a first valve, a second valve and a third valve; the situation of enabling helium to enter the sample chamber at first and then enter the reference chamber can be realized through the valves. The invention also discloses a measuring method for the core porosity. The measuring method comprises the following steps: (1) calibration: leading the helium into the sample chamber at first, then leading the helium into the reference chamber through pressure differentiation, and calculating to obtain reference chamber volume Vr and sample chamber volume Vc through a simultaneous equation, wherein the calibration is completed by repeating for many times; (2) measurement: calculating to obtain the core porosity through the simultaneous equation. According to the measuring device and the measuring method, disclosed by the invention, by leading high-pressure to-be-measured helium into the sample chamber at first and then leading the helium into the reference chamber through pressure differentiation, the pressure variation before and after the pressure differentiation can be remarkably increased, and the pressure variation is increased while the core pore volume is reduced; under the same device condition, the porosity of a core sample, particularly a low-porosity sample, can be more accurately measured by adopting the measuring device and the measuring method.

The invention relates to a high-altitude haze detecting device. According to the high-altitude haze detecting device, by combining a high altitude balloon with a pod, high-altitude haze detection is carried out; by using an electromagnetic pressure reducing exhaust valve I and a helium tank in the pod, the high altitude balloon is lifted; by using an antenna at the rear part of the pod and an electric steering engine and a propeller which are at the bottom of the pod, the device can be remotely controlled to control the advancing directions of the high altitude balloon in different wind layers, and the power of the high altitude balloon is provided by a storage battery pack in the pod; by using a measuring and compensating device in the pod, a high-altitude haze sample is collected to be detected; on the basis of a beta-ray and dynamic heating system method, a refrigerator and a weighing device are additionally arranged to carry out secondary weighing on condensed volatile substances so as to further improve the measuring accuracy; in order to increase the detection frequency, a paster storage device is used to store a paster and automatically change the paster; and as the pod cannot keep horizontal to affect a weighing result under an effect of wind power in the air; and by using a balancing device, the measuring and compensating device is kept in balance.

The invention discloses a helium circulating system comprising a helium cylinder, a heat exchanger, an evacuator, a pressure stabilizer, a first compressor, a second compressor, a temperature regulator, and an experimental segment. The output end of the helium cylinder is connected with the input end of the first compressor and the input end of the second compressor at the same time. The first compressor is connected with the pressure stabilizer. The pressure stabilizer is connected with the evacuator. The output end of the pressure stabilizer is connected to the input end of the second compressor. The output end of the second compressor is connected to the input end of the second compressor through a first flowmeter, forming a second compressor loop; the output end of the second compressor is connected to the input end of the temperature regulator through a second flowmeter, the output end of the temperature regulator is connected to the input end of the experimental segment, and the output end of the experimental segment is connected to the input end of the second compressor through the heat exchanger. The helium circulating system has the advantage that helium is fed into the experimental segment to provide the required low temperature or high temperature and pressure for the experimental segment.

The invention discloses a nitrogen injection stimulation coal seam pressure monitoring and methane desorption efficiency evaluation device and method. The device comprises a sealable sample cylinder and a reference cylinder which are arranged in a constant-temperature system parallelly, and the sealable sample cylinder and the reference cylinder are connected with a nitrogen bottle, a methane gasbottle and a helium bottle through gas incoming pipelines and connected with a vacuum pump through gas outgoing pipelines; each of the sample cylinder and the reference cylinder is provided with a pressure sensor for monitoring gas pressure therein, a strain monitoring system is mounted in the sample cylinder, and the sample cylinder is communicated with a gas chromatograph through a monitoring pipeline. Nitrogen is injected into a coal seam irregularly, and gas does not need to be injected into a coal rock gas reservoir, so that injection amount of non-hydrocarbon gas is reduced, and construction difficulty is lowered.

The invention discloses equipment for extracting helium from BOG gas with high hydrogen content and a process thereof, and relates to the field of equipment and process for extracting helium from BOGgas. The equipment comprises a catalytic dehydrogenation reactor, a cooler, a molecular sieve dryer, a feed gas compressor, a heat exchanger, a membrane separator, a vacuum pump, a buffer tank, a crude helium compressor, a helium purifier, a helium supercharger, a digital display type gas supply busbar device and a helium bottle; according to the invention, the permeability coefficient of gas molecules is increased in a manner of before- membrane pressurization and after- membrane vacuumizing; relatively high yield and purity of helium are achieved by using a relatively small membrane area; ina membrane separation process for extracting concentrated crude helium from BOG feed gas, Non-phase change is realized, and the equipment investment and the operation cost are reduced; the recovery rate of helium is increased before desorbed gas of the helium purifier returns to the feed gas compressor, and the helium yield of the whole device is as high as 99%; an interface is additionally arranged on an original BOG fuel gas pipeline to concentrate helium in BOG feed gas, and the loss of impermeable gas passing through a membrane separator is lower than 5%.

The invention discloses a helium low-temperature purification method and device and a helium refrigeration cycle system. The method comprises the steps of preparation before purification; pre-cooling; and purifying. The device comprises a pipeline system, a precooling heat exchanger, a low-temperature heat exchanger, a purifier, a Dewar tank, a vacuum pump and a helium tank group; a purification pipeline and a vacuum pipeline are arranged in the pipeline system, inlet stop valves are arranged on inlet pipe sections of the purification pipeline and the vacuum pipeline, outlets of the purification pipeline and the vacuum pipeline are converged on an outlet pipeline of the pipeline system, and an outlet stop valve is arranged on the outlet pipeline; the pre-cooling heat exchanger, the low-temperature heat exchanger and the purifier are sequentially in communication and mounted on the purification pipeline and are all packaged in the Dewar tank; the vacuum pump communicates with an inlet of the vacuum pipeline; and the helium tank group is in communication with an inlet of the purification pipeline. According to the helium low-temperature purification method and device provided by the invention, high-purity helium with the purity of 6N can be produced, and application occasions with high-purity requirements, such as the helium refrigeration cycle system and the like, can be met.

The invention belongs to the technical field of a detecting method for sensors, and particularly relates to a method and a device for vacuum cavity leakage detection for sensors with vacuum reference cavities. The method solves the problems that an existing leakage detecting method for the sensors with the vacuum reference cavities is low in detection accuracy and not free of missed detection, and only capable of detecting a single product and low in detection efficiency. The detecting method comprises the following steps: measuring output signals for products needing to be detected; and placing a plurality of the products into a pressuring tank, sealing the pressuring tank, evacuating air in the pressuring tank, filling helium into the pressuring tank, maintaining the pressure, evacuating the helium, measuring output signals of the products, and then comparing the output signals before and after the pressuring. The device comprises the pressuring tank capable of containing the plurality of the products to be detected, wherein the pressuring tank is provided with pipelines to be connected with a helium tank, a pressure instrument, a pressure switch and a vacuum pump. The device for the vacuum cavity leakage detection for the sensors with the vacuum reference cavities has the advantages of being high in detection accuracy rate, shortening the period of technical processes and being suitable for mass production.

The invention provides a nuclear magnetic resonance system and method for simulating high-temperature and high-pressure conditions. The system comprises a methane gas cylinder, a helium gas cylinder,a vacuum pump, a pressurization system, an oil storage bin, a high-temperature and high-pressure nuclear magnetic clamper, a low-field nuclear magnetic instrument, a control acquisition system and anexhaust system, according to the system, a rock sample to be measured is placed in a holder, fluorine oil in a heating oil storage bin is matched with a pressurizing system to apply confining pressureand high temperature to simulate a high-temperature and high-pressure environment to the holder, and a methane gas cylinder is matched with the pressurizing system to apply gas pressure to the holderto simulate a gas environment in a stratum; a low-field nuclear magnetic instrument is adopted to measure spectral information of a rock sample and store the spectral information in a control acquisition system. The method comprises the steps of standard plunger rock sample preparation and pretreatment, instrument calibration, device rock sample, confining pressure application, air tightness detection and vacuumizing treatment, original sample measurement, displacement experiment and variable gas pressure displacement experiment. The high-temperature and high-pressure environment and gas displacement of a real stratum can be simulated, and the credibility of a nuclear magnetic result is improved.

The invention discloses an unmanned aerial vehicle aerial survey UAV and method for an abnormal seepage area of an earth-rock dam, and the UAV comprises a power system and a rotor system which work independently, a non-contact charging landing gear, and a safety airbag. Ducted fans with small thermal infrared characteristics and high mechanical efficiency and safety are used in the power system and the rotor systems, lift force and thrust are independently provided for the unmanned aerial vehicle, an electromagnetic mutual inductance coil matched with a ground charging platform is arranged inthe non-contact charging landing gear, and the unmanned aerial vehicle is automatically and rapidly charged. The safety air bag is driven by a high-pressure helium cylinder to pop up and can be repeatedly used. According to the unmanned aerial vehicle, the unmanned aerial vehicle can be used for patrolling and detecting abnormal seepage regions of earth-rock dams and weir bodies, has the functionsof vertical take-off, hovering and top-speed flight, and can realize ultra-long endurance, heavy load and crash protection at the same time.

The invention relates to a pressurization gas cylinder arrangement method in a rocket oxygen tank cold helium pressurization system. 16 cold helium gas cylinders are arranged in an inner barrel section of an oxygen tank in lines. The 16 cold helium gas cylinders are arranged in 3 lines, and the numbers of the cold helium gas cylinders in the 3 lines are 5, 6 and 5. The 16 cold helium gas cylinders are further arranged in a layered manner. The 3 cold helium gas cylinders on each layer are 60 degrees away from one another on the circumference of the oxygen tank. The plane where the center position of the 3 cold helium gas cylinders on the bottom layer is located is 300 mm away from a rear equatorial plane of the oxygen tank. The interval of the cold helium gas cylinders on every two adjacent layers is 678 mm. Compared with the prior art, the arrangement mode and the number of the cold helium gas cylinders in the liquid oxygen tank are reasonably designed, under the condition that normal work of the pressurization system is guaranteed, the dead weight of the pressurization system can be reduced, meanwhile, the pressurization use helium amount can be reduced, so that the rocket carrying capacity is improved, and meanwhile the safety and reliability are relatively high.

The present invention relates to a free bird which can live in the air, water and on the land, and comprises a composite body which consists of an upper storehouse (1) and a lower storehouse (2). The upper storehouse (1) is provided with a high-pressure helium storage tank (11) and a compressor (13); the compressor (13) is dragged by a low-power direct current motor (12); the upper storehouse (1) and the lower storehouse (2) are connected by a high-elasticity membrane (6); a power device which combines a helium cylinder (7) and a spring (8) is arranged in a certain position between the upper storehouse (1) and the lower storehouse (2); the left side and the right side of the helium cylinder (7) are symmetric. The free bird has the advantage of freely moving in remote mountainous areas and steep mountains; thus the free bird solves the problems of moving inwards and outwards under the condition of inconvenient traffic, in particular in the backward mountainous areas of western China. In the mountainous areas with earthquakes, debris flow and other natural disasters, the free bird can be the best choice for rescuing.

The invention discloses a gas liquefaction experimental device and method for supercritical water-gas containing coal. The device comprises a high-pressure gas supply device, a supercritical water generation device, a coal gas liquefaction device, a pressure monitoring device, and a vacuum device. The gas supply device includes a helium cylinder, a gas cylinder, a gas booster pump. The supercritical water generation device includes a supercritical medium generating kettle, a muffle furnace heater, a satellite constant-current liquid boosting pump, and a temperature sensor. The coal gas liquefaction device includes a coal reaction kettle, a second muffle furnace heater, a temperature sensor, a second spiral tube condenser, a gas sample bag, a liquid collecting tube, and an anti-blocking ultra-fine filter sieve. The vacuum device consists of a vacuum pump, a vacuum pressure gauge, and a load pressure transmitter. The pressure monitoring device consists of a high-temperature-resistant pressure gauge, a high-frequency pressure transmitter, and a safety relief valve. According to the invention, the supercritical medium generating tank and the coal gas liquefaction tank are operated separately; and deionized water is added into the supercritical medium generating kettle to study the coal gas liquefaction effect.

The invention discloses a gas treating system applicable to online carbon dioxide measuring and relates to the technical field of measuring. The gas treating system comprises a carbon dioxide separating and collecting unit and a fine control injecting unit, wherein the carbon dioxide separating and collecting unit comprises a first two-position six-way selection valve which is respectively connected with an element analyzer, a carbon dioxide molecular sieve, a vacuum pipeline and a helium tank, and the vacuum pipeline comprises a dual-ring cold-trap pipe and a cross quantitative pipe which are connected; the fine control injecting unit comprises a four-position selection valve and a second two-position six-way selection valve, and the second two-position six-way selection valve is respectively connected with the four-position selection valve, an ion source, a precise-temperature-control cold trap and the helium tank. The gas treating system has the advantages that freeze separation and storage are performed on the carbon dioxide released by the combustion of the element analyzer, the carbon dioxide is injected into the ion source in a fine control manner by the pressure difference between a carbon dioxide tank and the gas ion source, and the flow speed of the carbon dioxide flowing into the ion source is determined according to the calibrated pressure of the carbon dioxide.

The invention belongs to the field of coal mine gas outburst disaster prevention and control, and particularly relates to a temperature change measurement experiment device and method in the coal adsorption and desorption process. The device comprises a high-pressure methane gas cylinder, a high-pressure helium gas cylinder, a reference tank and a sample tank, the reference tank is connected withthe high-pressure methane gas cylinder, the sample tank and a vacuum pump, a pressure reducing valve and a first valve are arranged on a pipeline between a high-pressure gas cylinder and the referencetank, a second valve is arranged between the sample tank and the reference tank, and a fifth valve and a vacuum meter are arranged between the vacuum pump and the reference tank; the reference tank,the sample tank and the vacuum pump are connected through a three-way valve, the sample tank is connected with an inlet of the three-way valve, and the reference tank and the vacuum pump are connectedwith an outlet of the three-way valve; the reference tank is provided with a a first pressure gauge, and the sample tank is connected with a second pressure gauge through a third valve. A first temperature sensor, a second temperature sensor, a third temperature sensor and a fourth temperature sensor are connected with a temperature recorder, and the temperature recorder transmits data to a computer.

The invention relates to a positive pressure leak hole calibration system and method with a lower limit of 10<-10>Pam<3> / s. The system comprises a molecular pump pumping system, a high-purity helium cylinder, a high-purity nitrogen cylinder, a gas sampling valve (V4), ten vacuum valves (V1, V2, V3, V5, V6, V7, V8, V9, V10, V11), three vacuum chambers (VC1, VC2, VC3), three vacuum gauges (G1, G2, G3), a quadrupole mass spectrometer (G4), a molecule flow sample inlet element (C), a getter pump (NEG), a calibrated positive pressure leak hole and a constant temperature cabinet.

The invention relates to a novel field rescue device. The novel field rescue device comprises a traction wire, an inflatable push sliding block, a top cover, an LED lamp, a battery, a folding balloon,a one-way inflation hole, a helium cylinder, a suspension rope, a lower casing, an upper casing and an upper outer casing sheet. When a user is in danger, the user only needs to turn on a switch, theballoon with an eye-catching distress signal then rises to the sky and emits a bright distress signal, so the user can be facilitated to discover by search and rescue personnel, after rescue, the novel field rescue device can be folded for cycle use.

The invention relates to a prismatic gas cooled reactor thermal hydraulic comprehensive experiment loop system, and belongs to the field of nuclear technology, wherein helium in a helium tank container enters a circulating fan through a loop pipeline, the helium flowing out of the circulating fan is divided into two paths: the first path of gas is heated to a set inlet temperature through an electric preheater, and then flows into an experiment section; an experiment assembly in the experiment section heats the first path of gas to a set outlet temperature, and the first path of gas flows out of the experiment section and then enters a mixer; the second path of gas directly flows into the mixer after flowing out of the circulating fan, and the two paths of gas flow out after being mixed in the mixer, enter a heat exchanger for cooling and then flow into the circulating fan again. The experimental system provided by the invention can realize full-high, full-pressure and full-temperature simulation of key thermal hydraulic phenomena of a reactor core fuel assembly, a control rod assembly and a structural component, reveals a flow heat transfer mechanism and rule, and provides verification data for existing analysis and calculation.

The invention discloses a helium tank support. The support comprises an installation plate assembly, a lower support rod assembly, and an upper support rod assembly; the installation plate is roughly in a triangular shape, the arc base line is provided with an installation angle support that is connected to an external bearing cylinder; a rounded tank installation embedded part is arranged on the top angle of the installation plate, the external cylindrical surface of the tank installation embedded part is provided with installation holes that are connected to a helium tank, a weight reducing groove is arranged between each two installation holes; a bearing beam structure is adopted in the axial direction of the central part, which is connected to the lower support rod assembly, of the tank installation embedded part, and the other part are provided with weight reducing grooves. A helium tank can be fixed on the bearing cylinder so as to enlarge the operation space over the middle plate of a communication capsule and improve the space utilization rate of a satellite, and thus an enough space can be created for the installation of a propelling system.

The invention discloses a laser gyroscope stable inflation and high-precision leak detection system. The system comprises a laser gyroscope inflation device, a helium mass spectrum leak detection device and a vacuum exhaust unit. The laser gyroscope inflation device comprises a helium gas cylinder, a neon gas cylinder, a gas mixing chamber, a pressure sensor, a mass flow meter and a gas inlet pipe connected with a laser gyroscope; the helium mass spectrometer leak detection device of the laser gyroscope comprises a helium mass spectrometer leak detector, a vacuum exhaust unit and a spray gun; the vacuum exhaust unit is composed of a mechanical pump, a molecular pump, a vacuum gauge and a vacuum exhaust pipeline. According to the invention, the laser gyroscope leak detection device and a laser gyroscope inflation packaging device are systematically combined together, so that the series of processes are connected more tightly, the cost is saved, the production efficiency is improved, an injection method helium mass spectrum leak detection technology is adopted, the leak detection precision of the laser gyroscope is greatly improved, and the minimum leak detection rate can reach the magnitude of 10 to 12pa * m <3> / s.

The invention discloses a remote leak detection system applied to a fusion reactor and a leak detection method of the system. The system comprises a leak detection unmanned aerial vehicle, a gas detection system, a data processing system, a detection alarm system and a control system, wherein the leak detection unmanned aerial vehicle is provided with a GPS positioning system, a helium supply system and an image system; the control system is connected to the leak detection unmanned aerial vehicle, the gas detection system, the data processing system and the detection alarm system in a wired orwireless mode. The helium supply system included in the leak detection unmanned aerial vehicle comprises a miniature helium cylinder, an electric control valve, a 360-degree rotating gas pipe connector and a gas path extension pipe. The helium cylinder provides helium for leakage detection; the electric control valve can be remotely controlled to be opened and closed, so that spraying and stopping of helium are controlled, and the spraying and blowing flow of the helium can be regulated and controlled by controlling the opening and closing degree of the electric control valve; the gas circuitextension pipe is connected to the 360-degree rotating gas pipe connector below the leak detection unmanned aerial vehicle body, and the position of the tail end of the extension pipe is adjusted through rotation of the remote control connector, so that the tail end of the gas circuit extension pipe accurately reaches a to-be-detected position.

The invention discloses a separable independent propulsion module system which comprises an independent propulsion module structure, a combustion agent storage box, an oxidant storage box, an independent propulsion module storage battery, an N thruster, a Beidou short message terminal, an N engine, an integrated sun sensor, an independent propulsion module control unit and a helium tank. Wherein the combustion agent storage box, the oxidizing agent storage box and the helium tank are arranged on the side wall of the independent propulsion cabin structure; the independent propulsion module storage battery is connected with the independent propulsion module structure; the N thrusters are connected with the independent propelling cabin structure through the bracket; the Beidou short message terminal is connected with the independent propulsion module structure; the N engine is arranged at the bottom of the independent propulsion cabin structure; the integrated sun sensor is connected with the independent propulsion module structure; the independent propulsion module control unit is connected with the independent propulsion module structure through screws. Separation design of the high-orbit satellite platform propelling system is achieved, and the method has the remarkable advantages of improving the satellite bearing capacity and prolonging the in-orbit service life of the satellite.

The invention provides a helium medium valve sealing performance test device and a test method thereof. The device comprises a high-pressure helium cylinder and a high-pressure nitrogen cylinder, wherein the outlet ends of the high-pressure helium cylinder and the high-pressure nitrogen cylinder are respectively connected with the inlet ends of a first needle type adjusting valve and a second needle type adjusting valve through pipelines; the outlet end pipelines of the first needle type adjusting valve and the second needle type adjusting valve are converged and then connected with the air inlet end of a clamp; the air outlet end pipeline of the clamp is divided into two branches, wherein one branch is connected with the air inlet end of a detection valve; the air outlet end of the detection valve is connected with a detection port through the pipeline, and the other branch is connected with the air inlet end of a pressure relief valve; the air outlet end of the pressure relief valveis connected with a pressure relief port through the pipeline; and when the sealing performance test is performed, the cleanliness of a helium medium valve is firstly checked, then the air inlet end of the clamp is connected with the outlet end of the high-pressure nitrogen cylinder or the high-pressure helium cylinder through the first needle type adjusting valve and the second needle type adjusting valve, and nitrogen or helium is filled in the helium medium valve to perform pre-detection and internal sealing and external sealing detection. The helium medium valve sealing performance test device has the advantages of being reasonable in structure, convenient to assemble, easy to operate and high in practicality.

The invention relates to equipment for testing the low-temperature target detection capability of an infrared camera under a deep space background, and belongs to the technical field of infrared camera detection capability testing. The device comprises an adjusting frame, a cold shield, a target black body, a background black body, a heating piece, a thermal switch, a first refrigerator, a secondrefrigerator, a molecular pump unit, a first compressor, a water chilling unit, a second compressor, a helium cylinder, a supporting frame, a temperature controller and a linear power supply, whereinthe device is used for performing ground testing of the dynamic range of a satellite-borne infrared camera and is important corollary equipment for Mars detection. The device is advantaged in that thetemperature of the background black body is controlled to be less than 40K, the temperature range of the target black body is controlled to be changed from 40K to 420K, temperature control precisionis + / -0.1 K, and temperatures of two black bodies are independently controllable; temperature change of an ultralow-temperature target is simulated, and the detection capability of the infrared cameraon the ultralow-temperature target is realized.

The invention discloses a low-temperature carrier rocket cold-helium pressurization cooling and conveying system. The low-temperature carrier rocket cold-helium pressurization cooling and conveying system comprises a helium bottle arranged in a liquid-hydrogen storage tank liquid phase, an outlet of the helium bottle is connected with an inlet of a first bubbling device and an inlet of a second bubbling device through a first throttling device and a second throttling device; the first bubbling device is located in the liquid phase of the liquid-hydrogen storage tank, and the second bubbling device is located in the liquid phase of a liquid-oxygen storage tank; and a liquid phase outlet of the liquid-hydrogen storage tank is connected with a first inlet of an engine, and a liquid phase outlet of the liquid-oxygen storage tank is connected with a second inlet of the engine. According to the low-temperature carrier rocket cold-helium pressurization cooling and conveying system, the heat insulation throttling refrigeration, the bubbling refrigeration, the bubbling pressurization, and the utilization of the cold energy and the pressure energy in the cold helium bottle are organically combined together, and dual effects of the high-efficiency pressurization conveying of the low-temperature carrier rocket and the cooling of propellants are achieved; and the consumption of needed pressurization gases can be greatly reduced, the number of the required helium bottles is reduced, the total take-off mass of the carrier rocket is reduced, the effective load is improved, the launching cost is further reduced, and the advantage of the obtained pressurization cooling effect is more remarkable.

The invention discloses a turbine vacuum system leakage detection comprehensive test device and method. The device comprises: a helium mass spectrometer leak detection system and an ultrasonic leak detection system, the helium mass spectrometer leak detection system comprises a helium cylinder, a constant pressure regulating valve, a spray gun, a vacuum pump and a helium mass spectrometer leak detector, the helium cylinder, the constant pressure regulating valve and the spray gun are connected in sequence, the vacuum pump is connected with a condenser, and a suction gun of the helium mass spectrometer leak detector is connected with an atmosphere exhaust interface of the vacuum pump. According to different characteristics of a helium mass spectrum leak detection technology and an ultrasonic leak detection technology, advantages and disadvantages are complementary, the two technologies are simultaneously applied to the leakage detection test of the steam turbine vacuum system. Optimization and summarization are carried out by combining different characteristics of a leakage detection environment; a leak detection instrument and a developed leak detection test special tool are used,and methods such as research, summarized constant-pressure quantitative test, fixed-point test and the like are comprehensively applied to carry out leak detection test on the steam turbine vacuum system, so that the accuracy and reliability of the leak detection test are improved, and the safe and stable operation of a unit is guaranteed.

The invention discloses a synchronous testing device and method for coal adsorption and desorption deformation anisotropy. The method is characterized in that on the basis of experimentally researching coal adsorption and desorption deformation through an existing method, an experimental device composed of a nitrogen cylinder, a helium cylinder, an electromagnetic valve, a pressure sensor, a vacuum pump, a vacuum gauge, a constant-temperature water bath box, an adsorption and desorption tank, a desorption and gas collection device, a resistance strain gauge, a strain gauge and a computer is adopted, an experimental coal sample is put into the adsorption and desorption tank, the electromagnetic valve, the pressure sensor and the constant-temperature water bath box are used for controlling different pressure and temperature conditions, epoxy resin adhesive ensures a sealed environment, a strain data acquisition system is used to carry out anisotropy measurement on desorption deformationof a coal body under different conditions, and an experiment result is automatically recorded by a data processing system. The operation process is trouble-saving and labor-saving, no redundant pipeline connection exists, the loss of excessive gas in the pipeline is avoided, and the device and the method can be suitable for synchronously measuring the stress strain of the coal body in all directions under different air pressure and different temperature conditions in real time.