170 results about "Atmospheric layer" patented technology

A satellite system for observing space objects includes two or more satellites positioned in an Earth orbit and configured to observe objects in various orbits including those viewed (i) against the Earth's background; (ii) against a sunlit Earth background; and (iii) against a space background. An electromagnetic sensor may be provided on at least one of the satellites that is responsive to electromagnetic radiation having a wavelength that discriminates against substantial reflection of electromagnetic radiation from the Earth's atmosphere to observe the space object. A method of observing a space object using a satellite system is also disclosed.

The invention discloses a method and device for cleaning space debris. According to the method, electromagnetic force is applied to the space debris running on an original orbit; the speed and / or direction of the space debris are / is changed under the action of the electromagnetic force; the space debris of which the speed is changed is changed to run on a new orbit under the action of gravity; at least the height of the perigee of the space debris on the new orbit is smaller than the height of the perigee of the space debris on the original orbit; the space debris running on the new orbit finally falls into the atmosphere of the earth under the action of atmosphere resistance. The device comprises a satellite bearing platform which is provided with an electric field device cleaning the space debris or a magnetic field device cleaning the space debris or a combination of the electric field device and the magnetic field device. The method and device for cleaning the space debris do not have high requirements for the accuracy of position detection of the space debris, micro space debris can be effectively cleaned, solar energy can be fully utilized for power generation, and self-carried energy is saved. The device for cleaning the space debris has the advantages of being simple in structure, low in manufacturing cost, and better in pulse action effect.

Simple APCV, ADPCV and PICV's are provided. The APCV's are referenced to the atmosphere and control the gauge pressure, either upstream or downstream. The ADPCV's are the same as the APCV's, differing in that they are not referenced to the atmosphere. They are instead referenced to a second point in the fluid flow system and control the differential pressure. The PICV's are control valves connected in series with ADPCV's and control the fluid flow rate through the valve independently of variations in the line pressure. A preferred APCV has a valve body (1) with connections for a single-phase fluid line and a flow passage between the inlet (2) and the outlet (3) of said fluid line, with an opening having a defined seat office (7) intersecting the flow passage. A moveable assembly, comprising a disk (5) or cup is connected to a pressure sensing member (4), having essentially the same effective surface area. The moveable assembly, is biased by a force, and is free to automatically move to any intermediate position between fully open and closed, producing a desired outlet pressure which minus the reference pressure, times the effective surface area of the disk or cup generates an opposing force equal to the biasing force.

The invention relates to a method for acquiring a complex refractive index of urban aerosol on the basis of various ground-based remote sensing technologies. The method comprises the following steps of: acquiring the extinction coefficient and the scattering extinction ratio of the aerosol through an inverse algorithm by virtue of Raman laser radar echo signals, and integrating the extinction coefficient of a certain route to acquire the optical thickness of the aerosol on the route; continuously correcting the extinction coefficient and the scattering extinction ratio by performing iterative alignment on an aerosol optical thickness of a whole atmospheric layer acquired via a sun photometer and the aerosol optical thickness acquired via a laser radar according to a Monte Carlo principle; then acquiring the particle size distribution of the aerosol via a particle spectrometer; and finally, acquiring the complex refractive index of the urban aerosol according to a mie-scattering model by virtue of the known scattering extinction ratio of the aerosol and the particle size distribution of the aerosol. According to the invention, the complex refractive index of the urban aerosol is acquired by the Raman laser radar, the sun photometer and the particle spectrometer, and the method has the advantages of small error, high discriminability and high universality.

The invention relates to a tomography method of using the limb sounding data for inverting atmospheric ozone profiles. The method comprises the following steps: respectively calculating the intersections between the gaze vector and the atmospheric grid radial and vertical boundary and atmospheric layer horizontal boundary, merging two types of intersections, then calculating the distance between adjacent intersections to obtain intercept; applying the tomography method in a correlate equation about volume emissivity and radiance, using the square iterative reconstruction technology to obtain the inverse iteration model of the volume emissivity, calculating the volume emissivity; and finally using an oxozone photochemical model to connect the volume emissivity with the ozone number density, and selecting the Newton iteration method to invert the ozone profiles.

The invention relates o a near-surface temperature inversion method based on FY-2C thermal-infrared waveband data as well as NCEP (National Centers for Environmental Prediction) atmospheric profile data. The inversion method comprises the steps of A) calculating an atmospheric transmittance tau[i](theta), wherein the tau[i](theta) represents the atmospheric transmittance at the waveband i when the observation zenith angle is theta; B) respectively calculating land surface emissivity epsilon[IR1] and epsilon[IR2] of FY-2C at the wavebands IR1 and IR2; C) calculating a temperature change rate Rt(h) in different atmospheric layers, wherein Rt(h) is the reduced rate of temperature at the height h; D) calculating steam content proportion Rw(h) in different atmospheric layers, wherein the Rw(h) represents the percentage of steam in total water content at the layer whose height is h; and E) calculating the near-surface temperature Ta via the formula Ta=(B0+B1TIR1+B2TIR2-bT0) / a.

The invention relates to a fiber reinforced high temperature thermal barrier composite ceramic thick coating material. The fiber reinforced high temperature thermal barrier composite ceramic thick coating material has the following structure: spray coating layers having the 'concrete' action and reinforced layers which are arranged between the spray coating layers and have the 'steel bar' action are arranged in turn on the surface of a metallic matrix workpiece of a spray coating and cementing bottom layer; the spray coating layers at least have 3 layers and are prepared from a powdery composite coating material with double effects of high temperature thermal barrier and ablative heat protection by a plasma spraying process; and the reinforced layers are formed by high temperature fibers which wrap the spray coating layers in a paralleled or staggered mode for one or two times, and the use temperature of high temperature fibers is more than or equal to 700 DEG C. The material is prepared by the following steps: preparation of a matrix, spray coating, wrapping and the like. The material can be coated on the surfaces of various aircrafts moving at a high speed in the atmospheric layer through the plasma spraying process so as to have the actions of the high temperature thermal barrier and the ablative composite protective layer. The material can improve the upper limit of the working temperature of a metallic matrix in a high temperature environment and simultaneously prolong the service time of the metallic matrix in a high temperature extreme environment. The material has high practicability and is suitable for the industrialized production.

The invention relates to solder paste for welding electronic devices, in particular to low-rosin halogen and lead-free solder paste and a preparation method of the low-rosin halogen and lead-free solder paste. The low-rosin halogen and lead-free solder paste is composed of solder powder and an soldering flux, wherein the weight percentage of the solder powder is 88-90 percent; the weight percentage of the soldering flux is 10-12 percent; and the solder powder consists of the following components by weight percent: 95.3-97% of Sn, 2-2.5% of Ag, 0.5-1.5% of Zn and 0.5-0.7% of Cu. The solder paste does not contain lead or halogen, is beneficial for environmental protection, and can not damage the atmospheric layer, the heavy pollution to the environment is greatly reduced, the residual solder waste after welding is little, the solder paste is colourless and transparent, has stable performance under normal temperature, can not absorb moisture, does not contain halogen, has no corrosion after welding, is particularly suitable for the no-clean operation, and better conforms with the environmental protection requirements.

Systems and methods for concentrating solar energy in the high earth atmosphere and transmitting the concentrated solar energy to the earth's surface. A system includes a light weight solar concentrator, supported by a light weight, rigid, buoyant, structure (36). The buoyant structure is suspended high in the earth's atmosphere above clouds and weather. Steerable mirrors, and / or a steerable structure, enable the concentrator to track the sun. In one embodiment, a buoyant light pipe (20) enables the transmission of concentrated solar energy from the high altitude concentrator to the earth's surface for further use. The system provides concentrated solar energy for use at any location on the earth, such use including generation of electricity via thermal or photovoltaic means and, direct and indirect process heat. The uses of process heat include desalination and hydrogen or methanol or other fuel production. A high solar concentration ratio enables high temperature, and hence high efficiency heat engine operation. With the provision of a thermal storage unit a system can provide utility scale continuous electricity generation and process heat at any location on the planet.

The invention relates to an SST inversion method and system based on Landsat 8 data. The method comprises that Landsat 8 optical and thermal-infrared remote sensing images and corresponding atmospheric contour data are read; on the basis of water-body and seawater emissivity data and a spectral response function of a Landsat 8 TIRS (Thermal Infrared Sensor), the atmospheric contour is used for driving, and channel brightness temperatures in the aerosphere top of two channels of the TIRS under different combined conditions of atmospheric conditions, SSTs and emissivities are simulated; and the obtained total atmospheric column water vapor content is used to divide the atmospheric column water vapor content into intervals, a split-window algorithm is used to construct SST inversion algorithms of the different water vapor content intervals, the SST is calculated, and a result is output. The system comprises a remote-sensing image reading module, an atmospheric water vapor data reading data, a data processing module and an SST inversion module. The system and method can be used to obtain high-precision SST.

The present invention is related to a method for detecting and / or measuring atmospheric accretion on a suspended electrical cable span (2) of overhead power lines, said suspended electrical cable span (2) having a sag (D) and a local tension (H), and being submitted to wind pressure (wwind), comprising the steps of independently:measuring said sag (D), and optionally measuring the wind pressure (wwind), over a first time range,measuring the local tension (H) over a second time range,the results of both steps being complemented and / or combined, so that to allow atmospheric accretion detection and / or measurement.

The invention provides a ground-based multi-channel microwave radiation meter based on meteorological detection, comprising a motor, a calibration unit, a power supply unit, antenna and feeding units, receiver units, and a data acquisition and system control unit. The antenna and feeding units are used for receiving microwave radiation signals from the atmosphere and a calibration object, and adopt a dual-frequency independent reflecting surface. The receiver units are used for sequentially performing down conversion, amplification, filtering, detection, integration and low-frequency amplification on the microwave radiation signals received by the antenna and feeding units to generate detection data, and the receiver units adopt receivers of a super-heterodyne local oscillator frequency-hopping system. With the microwave radiation meter, a vertical profile from the earth surface to a 10-km-high atmospheric layer can be measured, high-resolution temperature, relative humidity and water vapor profiles can be provided, and uninterrupted observation can be realized to provide whole-process data of weather process evolution.

The invention discloses a GNSS receiver and an intermediate frequency data processing method thereof, and belongs to the technical filed of receivers for a GNSS. The GNSS receiver comprises five parts, namely, an intermediate frequency data compression part, an intermediate frequency data storage part, an intermediate frequency data reading part, an intermediate frequency data uncompression part and an intermediate frequency data processing part. A GNSS radio signal is required to be transmitted through the atmospheric layer, the strength of the signal reaching the ground is very weak; the GNSS receiver needs to process intermediate frequency data which are long enough, so that a satellite signal can be searched; and a method combing GNSS intermediate frequency data storage and parallel signal processing is adopted, so that the time for searching the satellite signal can be greatly reduced. However, intermediate frequency data can occupy lager storage circuits, and thus the application of the method in actual practice is restricted. According to the GNSS receiver and the intermediate frequency data processing method, the intermediate frequency data are compressed and uncompressed, so that the storage size of the intermediate frequency data can be decreased, and the cost and the energy consumption of the whole GNSS receiver are reduced.

The diffraction of electromagnetic radiation from periodic grating profiles is determined using rigorous coupled-wave analysis, with intermediate calculations cached to reduce computation time. To implement the calculation, the periodic grating is divided into layers, cross-sections of the ridges of the grating are discretized into rectangular sections, and the permittivity, electric fields and magnetic fields are written as harmonic expansions along the direction of periodicity of the grating. Application of Maxwell's equations to each intermediate layer, i.e., each layer except the atmospheric layer and the substrate layer, provides a matrix wave equation with a wave-vector matrix A coupling the harmonic amplitudes of the electric field to their partial second derivatives in the direction perpendicular to the plane of the grating, where the wave-vector matrix A is a function of intra-layer parameters and incident-radiation parameters. W is the eigenvector matrix obtained from wave-vector matrix A, and Q is a diagonal matrix of square roots of the eigenvalues of the wave-vector matrix A. The requirement of continuity of the fields at boundaries between layers provides a matrix equation in terms of Wand Q for each layer boundary, and the solution of the series of matrix equations provides the diffraction reflectivity. Look-up of W and Q, which are precalculated and cached for a useful range of intra-layer parameters (i.e., permittivity harmonics, periodicity lengths, ridge widths, ridge offsets) and incident-radiation parameters (i.e., wavelengths and angles of incidence), provides a substantial reduction in computation time for calculating the diffraction reflectivity.

The embodiment of the invention discloses a method and device for optimizing numerical weather forecast through assimilated inversion of water vapor content. The method comprises: calculating the layered water vapor content of each atmospheric layer through inversion according to the radiance received by an observation satellite and generated by ground radiation, optimizing the initial field of the numerical weather forecast mode according to the calculated layered water vapor content of each atmospheric layer to obtain an optimized initial field, and carrying out new weather forecast throughthe optimized initial field. The optimized initial field considers the influence of water vapor in the atmosphere on the field, so that the weather forecast of the optimized initial field can reflectthe real weather condition more accurately compared with the weather forecast based on the original initial field. According to the method, the optimization of the initial field by combining satelliteobservation data is realized, and the weather forecast closer to the real condition can be obtained through the optimized target initial field.

The invention discloses a satellite integrity monitoring method and system based on mutual deviation. The method includes the steps of resolving the satellite position, clock correction and the geometrical distance between a satellite and a receiver, calculating atmospheric layer retardation and hardware channel retardation, calculating the pseudo-range deviation value, constructing the mutual deviation datum quantity, establishing the detection quantity and judging the integrity of the satellite. By means of the satellite integrity monitoring method and system based on mutual deviation, breakdown satellites can be accurately detected in time, the positioning result of a user is kept within the range of four to eight meters all the time, the positioning error of the user is effectively lowered, and the positioning accuracy of the user is guaranteed.

A motorcycle helmet having an oxygen conversion unit, which converts polluted air to breathable oxygen and other harmless compounds, while riding through the polluted atmosphere.

The invention discloses a pressurizing multi-grade condensation method for recycling oil gas. An air compressor is used for pressurizing the oil gas; cold quantity needed by each grade is provided for a pressurizing oil gas cooler through air cooling heat exchangers and a three-grade overlapping type refrigeration system. The pressurized oil gas passes through the air cooling heat exchangers and then is divided into two paths to be subjected to heat exchange with two heat exchangers which are arranged in parallel to recycle the cold quantity in liquid-state oil and tail gas respectively; then the oil gas sequentially passes through cooling heat exchangers of 2 DEG C, -30 DEG C and -80 DEG C, and the liquid-state oil and the tail gas are condensed and separated grade by grade. The tail gas is throttled to normal pressure before being exhausted to an atmospheric layer, and is subjected to heat exchange with the oil gas from the cooling heat exchangers to recycle the cold quantity again. The method disclosed by the invention has the three advantages that the water removing rate and the oil gas recycling rate can be easily improved after pressure is improved; the two parallel heat exchangers can be used for improving a heat transferring temperature difference and the cold quantity in the liquid-state oil and the tail gas is recycled to the greatest extent; the air cooling heat exchangers also can be used as overlapped refrigerating cycle condensers, so that a refrigerating system is relatively compact and efficient.

The invention discloses a new sky landing method as well as sky landing equipment, namely a sky landing safe chair. Sky landing comprises landing on a star, the moon or the earth. The sky landing method comprises the following steps: gas is produced by igniting in the landing process, a gas protective layer is inflated, friction force is generated between the gas protective layer carrying a landing person and the atmospheric layer when landing under the inflated state, the landing is at a low speed, the gas protective layer is separated between the landing person and the earth, the moon or the star when the landing person lands on the surface of the earth, the moon or the star, that is the landing person lands on the gas protective layer, and the landing person is protected in an omnibearing manner, when ignition is conducted on the water surface or underwater, the gas protective layer carries the landing person to float on the water surface or float out the water surface. The sky landing safe chair has the characteristics that the gas protective layer is lapped to be annular like a swim ring to be encircled on the purpose-made chair; an electrical appliance controls the ignition in landing, so that the gas protective layer is inflated, and the landing person is wrapped to the core to fall instantaneously. The equipment is safe, quick, universal and all-weather, safely falls at all heights greater than 1 second altitude difference from the ground, and can save the person's life in 1 second.

The invention discloses a movable in-situ sensing and measuring device for a near-surface atmospheric composition. The device comprises an air suspension device which is taken as a moving tool for an instrument in an atmospheric layer, wherein a safety rope for ensuring safety and positioning is tied on the air suspension device; a geographical space positioning module, a microprocessor, a communication module, a gas measuring module and a gas concentration sensor are arranged on the air suspension device; the geographical space positioning module is used for receiving a signal of a global positioning system according to a data acquisition command of the microprocessor, and determining the geographical space position of the air suspension device; and the gas concentration sensor is used for detecting the concentration of a tested gas composition in the atmospheric layer, sending a command according to data of the microprocessor, and transmitting the gas concentration signal and the geographical space position to a ground monitoring center in a wireless mode. The movable in-situ sensing and measuring device for the near-surface atmospheric composition provided by the invention has rich measuring parameters, higher measuring accuracy and low cost.

A fastening device for use in a spacecraft comprises a shaft and a head, which is connected by a first solder to the shaft. The first solder comprises a material of which the melting point is lower than the temperature acting on the fastening device on re-entry of a spacecraft equipped with fastening device into the earth's atmosphere.

The invention discloses a surface solar radiation calculation method based on deep learning which solves the problems that an existing method is long in calculation time and poor in universality and cannot be applied to cloud conditions. The method comprises the following steps of constructing an earth surface solar short wave radiation data set based on an atmospheric radiation transmission model; taking the surface solar short-wave radiation data set as a training sample; training through the neural networks to obtain a deep learning model, wherein the solar zenith angle, the aerosol opticalthickness, the atmospheric water vapor content, the cloud phase state, the cloud optical thickness, the cloud particle effective radius and the surface albedo are used as the neural network input layers, and the surface albedo, the surface downlink total solar radiation, the surface downlink direct solar radiation, the surface downlink diffused solar radiation and the atmospheric layer top upwardradiation are used as the neural network output layers. According to the method, the comprehensive, rapid and accurate calculation of the surface solar radiation is realized.

The embodiment of the invention provides a Mars exploration method and a Mars probe. The Mars exploration method comprises the steps that the Mars probe is launched from the earth, lifts off and enters an earth Mars transfer orbit, orbit trimming is conducted, and the Mars probe enters a Mars atmospheric layer; pneumatic braking is conducted through the Mars atmospheric layer, and the Mars probe enters and parks on a large elliptical orbit around the Mars; when the Mars probe parks on the large elliptical orbit around the Mars, dust storm on the Mars is monitored; and when the situation that the dust storm on the Mars is formed is determined, the Mars probe enters the Mars atmospheric layer to sample the dust storm on the Mars. According to the scheme, the cost can be reduced during Mars exploration.

The invention discloses a water color satellite atmospheric layer top radiation product quality evaluation and cross calibration method. The method comprises the following steps: establishing a multi-source satellite quasi-synchronization effective pixel selection constraint condition; finding that radiation signal abnormity caused by the natural process has high interstellar correlation; designing a multi-source satellite radiation product error analytical equation; combining a dynamic cross radiation calibration mechanism; and determining the influence of the radiation product quality on the water color product. According to the scheme, constraint conditions of quasi-synchronous observation are specified for the first time, an analytic equation of multi-source satellite radiation product errors is determined, dynamic evaluation and cross calibration of the water radiation product quality are achieved, the defect that a traditional method is seriously influenced by abnormal signals caused by the natural process is overcome, and the water radiation product quality and the automatic service level are improved; and moreover, the method is easy to implement, can be used for dynamically monitoring and improving the quality of water radiation products, and has wider practical application value and economic value.

The sun imparts 174 petawatt per second on the earth, and a large portion of this energy is absorbed by the earth's atmosphere in the form of translational energy for the gaseous molecules, i.e. continuous random motion in the average speed range of 500 meters per second on earth's surface. This invention utilizes a partition with large number of through-holes which all have the characteristic of providing greater cross section for gas molecules to transit from one side to the other than the reverse, thus creating a higher statistical probability for the molecules to move from one side of the partition to the other side. By stacking a number of such partitions to emphasize the direction of movement probability of the gas molecules within a container having two open ends, the number of gas molecules at the end of the stack will be more numerous than at the head, thus a pressure differential is established, and this pressure difference is used to push against the stacks of the partition to provide thrust on the container or to drive a turbine to generate electricity or to perform works.

The invention provides an air suction type solar heat micro thruster. The air suction type solar heat micro thruster mainly comprises a main body, an air intake channel, a diffuser pipe, a light collecting system, a heat exchange structure and a spraying pipe. The air suction type solar heat micro thruster has the advantages that the air suction type solar heat micro thruster can be applied to an ultra-low orbit satellite in an atmospheric layer which is 120-300km away from ground, air entering the micro thrust is heated by collected solar energy to obtain high-temperature air, the high-temperature air is sprayed out by the spraying pipe to produce about 0.02-2N thrust, and the thrust is very suitable for the attitude adjusting and drag compensation of the satellite; because a working medium of the micro thruster is mainly thin air, and the solar energy is used for heating, an aircraft only carries a small amount of propellant, thus the weight of the thruster is reduced, the maneuverability of an orbit is improved, the effective load of the aircraft is increased, and the on-orbit time of the aircraft is prolonged; by supplementing the propellant, the thrust produced by a thrusting system is increased, and the space application range of the aircraft is expanded.

The invention provides a device and a method for measuring the atmospheric transmissivity by an optical radiation measurement instrument. The device comprises a total diffuse reflection element, a shading element, the optical radiation measurement instrument and a computing element, wherein the total diffuse reflection element is used for carrying out diffuse reflection on sun light according to the preset angle so as to enable the sun light to be reflected into the optical radiation measurement instrument; the shading element is capable of keeping out the sun light irradiating the total diffuse reflection element when being arranged at a preset position; the optical radiation measurement instrument is used for measuring the total diffuse reflection element to acquire first response data containing total diffuse reflection sun light, and second response data which does not contain the total diffuse reflection sun light; the computing element is used for calculating the response difference between the first response data and the second response data; the whole layer atmospheric transmissivity at the response spectrum section of the optical radiation measurement instrument on the current measurement path can be obtained according to the response difference and the response data known in advance of the total diffuse reflection sun light positioned outside the atmospheric layer. The device and the method aim at accurately obtaining the whole layer atmospheric transmissivity at the response spectrum section of the optical radiation measurement instrument on the measurement path formed by the sun and the measuring device.