156 results about "High altitude environment" patented technology

The invention relates to an engine plateau environment laboratory which comprises an intake pressure simulation system, an exhaust pressure simulation system, a high and low temperature control chamber and a control system. The high and low temperature control chamber is used for placing an engine, the intake pressure simulation system is formed by sequentially connecting an intake pressurizer tank, a low-temperature box body and a refrigeration unit, and the exhaust pressure simulation system comprises an exhaust heat exchanger, an exhaust pressurizer tank, an exhaust electric control valve, a vacuum pump and a gas-water separator. Dispersive high-altitude natural environmental conditions (pressure, temperature and moisture) are intensively simulated in the laboratory, thereby improving the precision and the efficiency of the engine high-altitude environmental experiments.

A consumer based novel personal exercise apparatus that allows simultaneous simulation of mild to high altitude environments with algorithmically driven novel additional environmental stressors that may be pre-programmed or personally developed via physiological feedback during training. Additional stressors include the ability to transiently alter chamber pressure at variable frequencies and amplitudes with a range of changes with the option of random pressure oscillations designed to personalize training programs. Additional stressors include small variations in inspired CO2 levels and temperature allowing individuals to stimulate breathing and temperature conditions in preparation for desired environmental conditions.

The invention relates to a high-altitude simulation testing system for a piston engine. The high-altitude simulation testing system is characterized by comprising an engine test bed (4), an engine air intake temperature control system (1), an engine air intake humidification system (2), an engine air intake pressure control system (3), an engine exhaust cooling device (5) and an engine exhaust vacuum-pumping system (6). The high-altitude simulation testing system provided by the invention can effectively complete the testing of various working conditions of an engine in any combined environment of the three parameters (pressure, temperature and humidity) on the ground and the high-altitude environment with low temperature and low air pressure. Compared with the traditional cabin vacuum-pumping or wind tunnel testing system, the high-altitude simulation testing system provided by the invention has the advantages of simple and reliable system, small investment, low energy consumption, low operation and maintenance cost, multiple functions and the like, and can accurately control the air intake temperature of the engine.

The invention discloses a manufacturing method of a controllable heating and defrosting capacitive type high-altitude humidity sensor, relates to the field of high-altitude humidity sensors and the manufacturing method thereof, and solves the problem that the humidity data acquisition operation is seriously influenced as the surface of the conventional humidity sensor is frosted due to excessively low temperature in a high-altitude environment. The high-altitude humidity sensor is characterized by comprising a base, a first insulation layer, a first temperature sensor bonding pad, a second temperature sensor bonding pad, a first heater bonding pad, a second heater bonding pad, a temperature sensor electrode, a heater electrode, a second insulation layer, a lower electrode, a humidity sensing layer, an upper porous electrode and a groove. The manufacturing method comprises the steps as follows: manufacturing the high-altitude humidity sensor by adopting the methods of photo-etching stripping, magnetic control radio-frequency sputtering, corrosion hollowing, spin coating and evaporation coating. The high-altitude humidity sensor is suitable for the fields of climate and weather.

The invention relates to an artificial pavo critatus breeding method under a high-altitude environment. The artificial pavo critatus breeding method comprises the following steps: early young pavo critatus is obtained by a hybridization technology; by simulation and improvement of a production environment, the fertilization rate of seed pavo critatus is increased; a special pavo critatus incubation machine is designed; an artificial pavo critatus breeding technical flow is made; a standardized artificial pavo critatus breeding technical flow is customized. According to the artificial pavo critatus breeding method, the difficulties of low artificial pavo critatus breeding incubation rate and low survival rate in plateau areas are solved.

The invention relates to an artificial breeding method for African ostriches under a high-altitude environment. The method comprises the following steps that the environment adaptability of the African ostriches is improved by utilizing a 'hybridization technology'; the laying environment is simulated and improved to improve the fertilization rate of breeding ostriches; a dedicated African ostriches hatcher in a high-attitude area is designed; an artificial hatching technology process of the African ostriches is formulated; a standard artificial breeding technology process of the African ostriches is formulated; warm-keeping poultry sheds in an experimental group are transformed; a feed formula is innovated. The method solves the problems of artificial breeding of the African ostriches under the high-altitude environment.

The invention discloses a thermal power plant boiler group inspection method, the inspection method is applied to an inspection robot, and the inspection robot comprises a mobile device and a detection device; The detection device comprises an integrated holder device, a thermal infrared imager, a high-definition camera, an environment monitoring device, a positioning device, a battery electric quantity detection circuit, an ultrasonic obstacle stop system and an embedded CPU. And the thermal infrared imager, the high-definition camera, the environment monitoring device, the positioning device, the battery electric quantity detection circuit and the ultrasonic fault stopping system are respectively connected with the embedded CPU. By adopting the inspection method provided by the invention, full-coverage inspection can be carried out on key equipment of the waste heat boiler of the thermal power plant, the operation and maintenance cost is saved, the danger coefficient of inspection operation carried out by operation and maintenance personnel in high-temperature, high-pressure and high-altitude environments is reduced, the personnel safety is guaranteed to the maximum extent, the technological content of the power plant can be improved, and the national property loss is reduced.

The invention discloses a high-altitude environment detection system of a multi-rotor unmanned aerial vehicle. The high-altitude environment detection system comprises a control core, a GPS module, apulse width detection interface, an environment information monitoring module, a cloud control center, a camera and a character superimposition module. The high-altitude environment detection system has the advantages that extensibility of other functions is provided to existing high-altitude environment detection systems, a function-extensible aircraft detection system capable of detecting high-altitude environments is provided to facilitate environment monitoring for large-area regions, and the high-altitude environment detection system is adaptable to existing environment renovation.

The invention discloses a multi-factor comprehensive plateau alpine climate environment simulation acceleration test device, which comprises a test box body, a pressure system, a light source system,a temperature and humidity adjustment system, a circulating wind system and a control system. The test device uses a PLC or a single-chip microcomputer to control radiant power and total ultraviolet ratio of a light source as well as actions of pressure rise and fall, temperature rise and fall, humidification and dehumidification and wind speed and the like. The test device can form an artificially-simulated or enhanced plateau alpine environment composed of five environmental factors, that is, light, air pressure, temperature, humidity and wind speed, and is used for testing and evaluating plateau alpine climate environment adaptability of materials, parts and equipment. By controlling some environmental factors, the test device can also simulate cold environment, dry and hot environment,tropical rainforest environment and high-altitude environment and the like. The device can also be used to carry out a number of existing standard tests, comprising low pressure test, light aging test, high and low temperature test and damp heat test and the like to achieve an effect of one box with multiple uses.

The invention relates to a heating type humidity sensor for a sonde and a preparation method of the heating type humidity sensor as well as a humidity detection circuit, belonging to the technical field of a humidity sensor, and aiming at solving the problems that a humidity sensor for a sonde is easily dewed in a high-altitude severe environment with low temperature and high humidity and has large humidity fluctuation in the high altitude environment, and measurement results are influenced by the distributed capacitance of a circuit board. The humidity sensor is a flat plate sandwiched capacitive humidity sensor with a snake-like heater. The invention also provides the preparation method of the sensor and the humidity detection circuit based on capacitance charge-discharge and a comparison method. According to the invention, temperature drift and zero drift are effectively inhibited, and the influence of parasitic capacitance to measurement results can be reduced. The heating type humidity sensor is used for the sonde.

The present invention relates to a system for operating a flying object that is flown from the ground. The flying object operation system includes a flying object that is filled with a gas therein to stay in the sky, a ground unit installed on the ground, a wire unit connecting the flying object to the ground unit, and a buoyancy-generation unit disposed on a side of the flying object to obtain buoyancy through friction with air, thereby transferring the obtained buoyancy to the flying object. In the present invention, since additional wind-derived buoyancy obtained by the buoyancy-generation unit connected to the flying object is further generated, sufficient buoyancy may be supplied to the flying object in a high-altitude environment to stably operate the flying object. Also, since power generated by using the wind power generation unit is transmitted to the ground through the wire unit, the flying object operation system may be utilized as wind power generation equipment.

The invention discloses a flight type high-altitude environment detecting instrument. The flight type high-altitude environment detecting instrument includes an unmanned aerial vehicle, cameras, a solar panel, an anemograph, a box body, a sampling main tube, sampling branch tubes, a suction ventilator, a detection power source, a detection controller, a pressure reducing valve, a gas mixer, a first detection box, a second detection box, an exhaust fan and a one-way valve; the unmanned aerial vehicle includes a rack, brushless motors, blades, a flight power source, a GPS module, supporting legs, a signal transmitter and a signal receiver; the brushless motors are mounted at four corners of the rack; end portions of the brushless motors are provided with the blades; the flight power source is mounted at the center of the bottom of the rack; and a flight controller is mounted at the lower part of the rack. The flight type high-altitude environment detecting instrument of the invention has the advantages of novel structure and scientific and reasonable design. With the flight type high-altitude environment detecting instrument adopted, environment detection of special terrains such as high-altitude space and valleys can be realized, and the defect that an a traditional environmental quality detecting device can only carry out short-distance detection can be eliminated; and multi-point sampling is realized, measurement data are comprehensive, and the accuracy of measurement can be improved.

The invention relates to an annular ejector for a high altitude environment simulation test, which is characterized by comprising an adapter flange, an ejecting nozzle, an ejecting gas inlet pipe and an ejector outer tube. The ejector nozzle is arranged in the ejector outer tube and in tube threaded connection with the adaptor flange fixed with the ejector outer tube through a bolt assembly, one end of the ejector outer tube is of a boss structure, and a seal member is arranged between the adaptor flange and the boss structure. The annular ejector for the high altitude environment simulation test adopts split design, abandons traditional integral design, and can adjust the performance in a certain range only by adjusting the specification and dimension of the ejector nozzle according to the requirement of the test without changing the whole annular ejector and dismounting a connecting pipeline so as to improve working efficiency and effectively reduce test cost.

The invention provides a testing device for an aircraft fuel system in a simulated high altitude environment, comprising a low temperature gas supply system, a vacuum pumping system and a fuel system, wherein the low temperature gas supply system is used for creating a low temperature environment of the simulated high altitude; the vacuum pumping system is used for pumping air out of a pressure-proof fuel tank to create a low pressure environment of the simulated high altitude; the fuel system comprises the pressure-proof fuel tank, a fuel pump and an engine which are sequentially arranged; the low temperature gas supply system realizes the purpose of cooling fuel in the pressure-proof fuel tank through a plate type heat exchanger; and the vacuum pumping system is connected with the pressure-proof fuel tank. Accordingly, the invention also provides a testing method for the aircraft fuel system in the simulated altitude environment. Therefore, by adjusting the working pressure and temperature of the fuel system, the low temperature and low pressure environment of the high altitude is simulated, and working parameters of the fuel system are recorded, thereby analyzing and testing the fuel system.

The invention discloses a method for detecting imaging resolution of an aerial camera in a high-altitude environment condition, and belongs to the technical field of aerial photography. The method comprises: installing a camera on a camera support, putting the camera support in a temperature-altitude test box, fixing a collimator on an optical vibration isolation platform, fixing a resolution plate in front of a light source of the collimator; installing a light passing window on the temperature-altitude test box, disposing a 45 degrees plane mirror under the light passing window, adjusting the camera and the collimator to make optical axes of the two parallel with each other; light beams passing the resolution plate, reflecting a target image by the 45 degrees plane mirror, the target image being generated by the resolution plate through the collimator, and obtaining the reflected target image by the camera; and adjusting temperature and pressure, simulating different high-altitude environment, controlling camera imaging through a camera synthetic operation instrument, discriminating the image to obtain a result of imaging resolution detection. The method is easy in operation, high in reliability, easy in principle, high in detection precision, and is flexible and reliable. The method enables to obtain images in real time, so as to perform interpretation and comparison. The method has high efficiency and good operability.

A method and a device for aircraft airborne environment gas automatic collection are provided. The device comprises mini air pumps, a gas sensor, an analog to digital (A / D) converter, a speed detecting circuit, a micro-processor, a storage device, a switch circuit and a wireless communication circuit which are all arranged on an aircraft. When the aircraft works, by means of timing control of the single chip, the switch circuit sequentially opens the mini air pumps, gas in high-altitude environment is sequentially collected, the collected gas passes through a gas detector, a detection parameter is input into the micro-processor through the A / D converter, the micro-converter stores gas acquisition data and speed detection data and sends the data to a ground monitoring receiver or a monitoring station through the wireless communication circuit. Preferably, the method and the device for aircraft airborne environment gas automatic collection can overcome the shortcoming of fixed point collecting errors caused by response time of the gas sensor, can acquire the environment gas data at a spatial determined position, provides basis for spatial distribution research of the environment gas, and is suitable for gas collection and analysis in the fields of safety environments, carbon emission, environment protection and the like.

A personal exercise apparatus that allows simultaneous simulation of mild to high altitude environments with algorithmically driven environmental stressors that may be pre-programmed or personally developed via physiological feedback during training. Additional stressors include an ability to transiently alter pressure in a chamber of the personal exercise apparatus at variable frequencies and amplitudes with a range of changes with an option of random pressure oscillations designed to personalize training programs. The additional stressors further include small variations in inspired CO2 levels and temperature allowing individuals to simulate breathing and temperature conditions in preparation for desired environmental conditions.

The invention discloses a system for observing and controlling distributed environmental parameters, which has the characteristics of modularization and universalization in function implementation method thereof and which is mainly composed of a main control part module, a data acquisition part module, a vibrating signal high-speed measurement part module and a data processing system part module. The observing and controlling system with higher reliability and stability satisfies the requirement of users on modern management test and can be used in a plurality of environmental simulation tests, including double aero-thermodynamics test, depression and temperature impact test, temperature height test, dust environment test, high-altitude environment simulation cabin test and the like, thus the test efficiency of large comprehensive environmental simulation test equipment is enhanced, test time and expenditure are saved, and excellent economical benefit is realized.

An embodiment of the invention provides a solar cell performance test system. The system comprises a high altitude balloon filled with inert gas and a solar cell test module, wherein the high altitudeballoon is connected with the solar cell test module, the solar cell test module comprises a solar cell and a test device for testing performance of the solar cell. In the system, the solar cell testmodule is connected with the high altitude balloon, so as to test working performance of the solar cell circularly in the high altitude environment and record measured data in real time. Light intensity, spectrum distribution, temperature and other environment parameters in the test environment are set to close to actual environment parameters, so that the solar cell performance test results aremore accurate. The solar cell test system has a simple structure, is light, and can be applied to high altitude test.

The invention discloses a parking heater. The heater includes a control system, a fuel supply system and a heat exchange system, wherein the control system includes a motor for driving a new wind wheel in the heat exchange system to rotate, an atmospheric pressure sensor for detecting a current atmospheric pressure value, a cabin temperature sensor for detecting a current temperature value inside a cabin, and a controller assembly for adjusting the oil injection process of the fuel supply system and the speed of the motor according to the current atmospheric pressure value and the current cabin temperature. The atmospheric pressure sensor and the cabin temperature sensor can obtain the current atmospheric pressure value and the current cabin temperature value in real time, and the controller assembly can control the oil injection process and the motor speed according to the air inlet pressure and temperature, so that the parking heater is more environment-friendly and more adaptable to a high altitude environment.

The invention discloses a compact high altitude environment simulation system based on closed air circulation and a control method. The system is mainly composed of a high and low temperature closed environment chamber, a compressor, an expansion machine, a heat exchanger, a compression-side four-way reversing valve and an expansion-side four-way reversing valve, wherein the high and low temperature closed environment chamber is provided with a compression-side air vent and an expansion-side air vent; and the compressor and the expansion machine are coaxially arranged, and a high speed motor for driving the compressor and the expansion machine is arranged between the compressor and the expansion machine. According to different demands, the system can work in a refrigerating mode or a heating mode; when the system works in the refrigerating mode, the compression-side air vent serves as an air inlet, the expansion-side air vent serves as an air outlet, and the air in the closed environment chamber sequentially passes through the compression-side four-way reversing valve, the compressor, the heat exchanger, the expansion-side four-way reversing valve and the expansion machine so as to complete a refrigerating cycle; and when the system works in the heating mode, the compression-side air vent serves as an air outlet, the expansion-side air vent serves as an air inlet, and the air in the closed environment chamber sequentially passes through the expansion-side four-way reversing valve, the expansion machine, the heat exchanger, the compression-side four-way reversing valve and the compressor so as to complete a heating cycle.

A method for surface treating a titanium gas turbine engine component. The method includes providing a gas turbine engine component having a titanium-containing surface. The component is heated to a temperature sufficient to diffuse carbon into the titanium and below 1000° F. The surface is contacted with a carbon-containing gas to diffuse carbon into the surface to form carbides. Thereafter, the carbide-containing surface is coated with a lubricant comprising a binder and a friction modifier. The binder preferably including titanium oxide and the friction modifier preferably including tungsten disulfide. The coefficient of friction between the surface and another titanium-containing surface is less than about 0.6 in high altitude atmospheres.

The Tibet region in China has the characteristics of high altitude, low air oxygen content, large day and night temperature difference and low night temperature, so that a traditional activated sludgeprocess adopted for domestic sewage treatment at present confronts with the problems of low aeration efficiency, high energy consumption, weak functional microorganism activity and the like when being applied to the Tibet region; meanwhile, the treatment of a large amount of residual sludge threatens the ecological environment of the Tibet region. According to the method, a chemical enhanced primary treatment (CEPT) process and an integrated partial nitrosation-anaerobic ammonia oxidation (CPNA) process are combined, so that the capture of carbon and phosphorus in the inlet water and the whole-course autotrophic nitrogen removal under a low-oxygen condition are realized. The captured carbon source is used for producing biogas through anaerobic fermentation, and can supplement heat for a CPNA process under a low-temperature condition. The CEPT-CPNA process has the advantages of low energy consumption and less residual sludge generation, can solve many problems in the traditional method, and belongs to a sustainable sewage treatment process suitable for a high-altitude environment.

The invention provides a method for determining the burnout height of a combustion chamber of a pulverized coal boiler. The method comprises the steps as follows: Step 1: a high-altitude environment is simulated, and combustion characteristic parameters of fire coal in the high-altitude state are acquired through a combustion test of the fire coal on a test bed; Step 2: according to the characteristic parameters, the correlation between the carbon content of coal-fired fly ash of the fire coal and the dwell time of pulverized coal of the fire coal in the boiler is obtained; Step 3: according to the correlation between the carbon content of the fly ash and the dwell time of the pulverized coal in the boiler, the dwell time value, corresponding to the limit value, required to be reached during actual boiler design, of the carbon content of the fly ash, of the pulverized coal in the boiler is obtained, and the burnout height of the combustion chamber is obtained in combination with the flue gas velocity of the pulverized coal in the combustion chamber. With the method for determining the burnout height, the boiler design in a high-altitude area has more scientific bases, the problems of high carbon content of the fly ash and low boiler combustion efficiency due to insufficient burnout time which is possibly caused by the fact that the burnout height of a boiler in the high-altitude area is determined as per the empirical formula only are solved, and the boiler design risk is effectively reduced.

The invention discloses a bidirectionally-transformable unmanned aerial vehicle of an H-shaped structure. The bidirectionally-transformable unmanned aerial vehicle of the H-shaped structure comprises a fuselage and arms which are arranged on the two sides of the fuselage and are parallel to each other. A lifting structure is arranged in the middle of the fuselage. The lifting structure is connected with oblique T-shaped parts through transverse stress pipes, and the oblique T-shaped parts are fixed to the middle portions of the arms correspondingly. Rotor wing assemblies are arranged at the two ends of each arm correspondingly. According to the bidirectionally-transformable unmanned aerial vehicle of the H-shaped structure, the lifting structure is additionally arranged on the fuselage so that the arms of the unmanned aerial vehicle can rise and fall, the center of the unmanned aerial vehicle can be better adjusted, the unmanned aerial vehicle can adapt to various complex high-altitude environment, and the stability of the unmanned aerial vehicle is improved; the unmanned aerial vehicle can be protected against disturbance from the arms when executing shooting work, and the shooting effect of the unmanned aerial vehicle is improved; and folding of the fuselage and the arms of the unmanned aerial vehicle is achieved, the arms and the fuselage of the unmanned aerial vehicle can be folded together in the unmanned aerial vehicle transporting process, the size of the unmanned aerial vehicle is reduced, the assembled and debugged unmanned aerial vehicle can be directly used conveniently when needed, and the practicability of the unmanned aerial vehicle is improved.

The invention provides a method for entering a same-tower double-circuit alternating-current transmission line tangent tower equal potential. The method comprises the following steps: an operator arrives at a position parallel to a charged body of a high-voltage alternating-current transmission line through a grounded tangent tower and / or a closest position to the charged body and is at least kept away by a first distance, wherein the first distance refers to the distance between the operator and the charged body; the operator leaves the tangent tower, approaches the charged body and is at least kept away by a second distance, wherein the second distance refers to the sum of the distance between the tangent tower and the operator and the distance between the operator and the charged body; and the operator arrives at the charged body and is kept away by a third distance, wherein the third distance refers to the distance between the operator and the tangent tower. By the adoption of the method of the invention, the problem that operators may easily suffer from an electric shock and be injured in high-voltage and high-altitude environments is solved and the personal safety of operators is ensured.

The invention discloses an imaging detection system for an aerial camera under a high-altitude environment condition. The system comprises an unmanned aerial vehicle, an aerial camera module and a ground data receiving module. The aerial camera module is used for collecting image signals and motion state data of the aerial camera, carrying out compensation processing on the image signals and then sending the image signals to the ground data receiving module. The ground data receiving module is used for carrying out image quality detection on the received image signals and judging an image state aerial camera of the under the high-altitude environment. The system has the beneficial effects that lowpass filtering processing is carried out on the image signals photographed by the aerial camera under the high-altitude environment, thereby obtaining a secondary blurred image; the secondary blurred image is taken as a reference image; the change condition of the parameter information of image blocks before and after the filtering is extracted as the basis for imaging quality detection, so the defect that a traditional reference image-free imaging quality evaluation method generally is high in computing complexity is effectively solved; the operation complexity is effectively reduced; and the operation speed and the system accuracy are improved.

The invention provides a self-heating product applicable to a high-altitude environment. The self-heating product is characterized by comprising a heat-generating agent which comprises a heat-generating component, a sustained-release component and an initiating component in a weight ratio of (0.8-1.2): (0.03-0.07): (2-5), wherein the heat-generating component comprises, in percentages by weight, 10% to 55% of calcium hydroxide, 9% to 45% of carbonate, 8% to 45% of an active metal substance and 2% to 3% of graphite; the sustained-release component is macromolecular polysaccharide; the initiating component comprises, in percentages by weight, 10% to 40% of glycerol and 60% to 90% of water; the raw materials of the heat-generating component and the sustained-release component are mixed and packaged to obtain a heat-generating package; and the raw materials of the initiating component are mixed and packaged to obtain an initiating package. The self-heating product provided by the inventioncan generate heat through self-generated high-temperature steam to achieve the heating purposes of eating, drinking, disinfection, etc.