34 results about "Solar observation" patented technology

The invention relates to a solar image registration method based on normalization cross-correlation and SIFT, and belongs to the field of astronomical technology and image processing. The method comprises the following steps: firstly, carrying out downsampling preprocessing on a group of full-solar observation images from a space-based (SDO) and a group of solar local high-resolution observation images from a ground telescope (NVST) respectively; secondly, using a normalization cross-correlation matching algorithm to solve the problem that the view fields of the to-be-registered area are inconsistent; calculating the optimal matching position of the full-day image and the local high-resolution image, and using the position to intercept a sub-image to serve as a to-be-registered reference image; Performing feature detection on the to-be-registered image by adopting a feature detection operator (SIFT) based on scale invariance to obtain a feature point set; Using an MLESAC algorithm to eliminate mismatching feature point pairs; And finally, solving transformation parameters among the images by using a least square method to obtain a registration result. According to the invention, rapid, automatic and high-precision registration of solar images of different observation sources is realized.

The invention discloses a probing and tracking camera for targets on solar observation blind areas, which can be arranged on a satellite to observe and track targets on the solar observation blind areas. The camera comprises an attenuation filter, an optical system, a probe and a data processing circuit; wherein, a ray of light from an object space passes through the attenuation filter and the optical system and forms an image on the probe. The attenuation filter is used to adjust the intensity of light coming into the camera, and the optical system adopts a double-Gauss near infrared teleobjective system; the probe adopts a CMOS probe, and the dynamic range is designed as follows: the brightness of the sun, sunspot images is designed out of the dynamic range of the camera, and the brightness of the observed targets is designed within the saturation value of the camera. The data processing circuit conducts reverse-phase processing over the images output by the probe, so as to enable the system to acquire higher positioning precision of the targets. The probing and tracking camera in the invention, together with a sun sensor, a two-dimensional tracker and an image processing system, forms a whole probing and tracking system for targets.

The invention discloses an aerosol remote sensing inversion method and an aerosol remote sensing inversion system for lack of short-wave infrared data. The aerosol remote sensing inversion method considers the influences of angle and surface type of the earth on a band relationship, constructs a band regression coefficient lookup table for angled grid division and surface feature type classification by using a multi-angle data set, and performs inversion to obtain aerosol optical thicknesses of surfaces of different surface feature types. The method introduces an aerosol correction index (ACI)and NDVI seasonal variation characteristics as limiting conditions for the problem that the aerosol optical thickness inversion results are highly sensitive to the relationship between bands. The core technology of the aerosol remote sensing inversion method is that an aerosol optical thickness lookup table and the band regression coefficient lookup table are established based on the direct correlation of the surface feature spectral bands by combining with influences of different solar observation angles on the band relationship, can rapidly and precisely obtain the aerosol optical thicknessinversion results of different surface features through inversion by screening conditions, and improves the operation efficiency and inversion precision by adopting the above technical means.

A system for real-time solar observation comprises an optical detector operable to detect sunlight and to produce image data from detected sunlight, a shadow detector operable to produce image data relating to a shadow cast by a reference object, and a controller operable to receive image data from the optical detector and from the shadow detector. The controller is operable to determine at least one of a sunrise period, a midday period and a sunset period in dependence upon received image data.

The invention provides a separated solar observation satellite configuration, which comprises a platform cabin and a load cabin, wherein the platform cabin and the load cabin are connected through a magnetic suspension actuator (1); the separated solar observation satellite configuration also comprises an antenna mechanism; the antenna mechanism comprises an antenna bracket (11); the platform cabin comprises a platform cabin top plate (5); and the antenna bracket (11) is arranged on the platform cabin top plate (5). The separated solar observation satellite configuration can achieve the full physical space isolation between cabins, thoroughly eliminates the micro-vibration effect of the satellite platform on the load, and improves the pointing precision and stability of the satellite by two orders of magnitude. According to the design layout of the antenna bracket in the separated solar observation satellite configuration, the shielding of the field of view of the antenna can be eliminated. The load cabin body in the separated solar observation satellite configuration is attached with a battery sheet, so that a prior fixedly-connected cable is replaced, the quality is reduced, andthe separation of cabin sections is ensured.

The invention provides an on-orbit spectrum calibration method for a hyperspectral remote sensing instrument. The on-orbit spectrum calibration method comprises the steps of: S1, calculating a centralwavelength position of each channel of an on-orbit solar observation spectrum of a target hyperspectral remote sensing instrument based on on-orbit solar observation data and ground calibration coefficients of the target hyperspectral remote sensing instrument; S2, positioning speed information precisely based on a satellite, performing frequency shift correction on the central wavelength position of each channel of the on-orbit solar observation spectrum according to Doppler frequency shift characteristics, and acquiring an effective central wavelength position of each channel of the on-orbit solar observation spectrum; S3, calculating an on-orbit spectrum calibration error of the target hyperspectral remote sensing instrument based on the effective central wavelength position of each channel of the on-orbit solar observation spectrum and a solar standard spectrum standard absorption line position; S4, and performing on-orbit spectrum precise calibration on the target hyperspectral remote sensing instrument based on the on-orbit spectrum calibration error. The on-orbit spectrum calibration method can effectively improve the precision and stability of spectrum calibration.

The invention provides a solar observation satellite platform. A solar observation telescope is mounted on a load suspension plate and is isolated from a vibration source of the satellite platform; anattitude measurement and high-precision actuator and a control computer are mounted on the suspension plate, and an attitude control closed loop is realized in the suspension plate; the suspension plate is connected with a platform compartment in a non-cable mode, and a laser/WIFI communication terminal is used for information interaction; and an electromagnetic induction coil is used for supplying power to equipment on the suspension plate. The solar observation satellite platform can be used in aerospace missions with high stability requirements for the platform, such as solar observation and star observation, the solar observation telescope is no longer affected by flexible parts and moving parts of the platform compartment in the solar observation process, the control closed loop of the actuator is measured through the load suspension plate, and the platform stability performance is greatly improved.

The invention provides a satellite inter-module connection method under over-constrained conditions, comprising: a maglev mechanism, a one-off unlocking device and a maglev mechanism tool mounted on aplatform module roof. The electromagnetic sucker end of a repeatable unlocking device and a repeatable unlocking device tool are mounted on the platform module roof; the suction end of a re-connectable release device is mounted on a load module suspending plate; the load module suspending plate is mounted above the platform module roof; the maglev mechanism is connected with the load module suspending plate; after the maglev mechanism tool is released and the load module suspending plate is lowered, the bottom of the load module spending plate is in contact with the top of the repeatable unlocking device tool; the one-off unlocking device is connected with the lateral side of the load module suspending plate, and the repeatable unlocking device tool is released. The method herein has theadvantages that the steps are clear, assembly is simple, the demand for reliable connection of two modules can be met under the over-constrained conditions, and the method is applicable to sun-oriented solar observation tasks having high requirements on attitude precision and stability.

The invention provides a solar observation satellite ground test device and system. The solar observation satellite ground test device comprises an experiment satellite cabin and air floating platforms (9). The experimental satellite cabin is provided with air feet (8). A gas cylinder (6) is arranged in the experimental satellite cabin. The gas cylinder (6) comprises a medium with set pressure. The gas feet (8) comprise a first gas path, and the gas cylinder (6) comprises a second gas path. The first air path communicates with the second air path. A medium can be transmitted to the outside ofthe experimental satellite cabin through the first gas path and the second gas path which communicate with each other, that is, the medium in the gas cylinder (6) can be ejected through the gas feet (8). The air floating platforms (9) are arranged on one sides of the air feet (8) of the experimental satellite cabin at intervals. An active air floating design is adopted and is different from traditional suspension or single-axis air floating, and omnidirectional attitude control verification of three degrees of freedom of a load cabin and three degrees of freedom of a platform cabin through theair feet.

The invention discloses a full solar disk sun imager adopting two-channel atomic light filtering technology, which comprises a telescope (01), a light filtering sheet (02), a lambda/4 wave plate (03), a polarizing light splitter (4), an atomic light filter (05), an atomic light filter (11), a light splitter (06), a light splitter (12), an interferometer (07), an interferometer (09), an interferometer (13), an interferometer (15), a CCD (08), a CCD (10), a CCD (14), a CCD (16) and a computer (17). The polarizing light splitter, the atomic light filters, the four interferometers, the four CCDs and the like are fixedly connected without time sequence control, thus four high-resolution spectrum images of the sun can be obtained simultaneously, and the full solar disk brightness, the Doppler velocity and the magnetic field intensity can be obtained after treatment. The technical scheme has the characteristics of scientific scheme, stable and reliable system, convenient use and the like, improves the stability and the precision of measurement of the solar magnetic field, and provides a better detecting device for observing sun and monitoring and predicting space weather.

The invention provides an embedded type solar observation satellite configuration. The embedded type solar observation satellite configuration comprises a loading cabin, a platform cabin, an electromagnetic snap connection device, a cabin crossing cable, antennas and a platform load, wherein the loading cabin is embedded into the platform cabin of the satellite configuration and is connected withthe platform cabin through the electromagnetic snap connection device in a physical isolation manner; the platform load is arranged in the platform cabin and is connected with the antennas through thecabin crossing cable; a side plate is adhered to the outer surface of the platform cabin, a platform cabin view field opening hole is formed on the side plate; the platform load is used for observinginformation through the platform cabin view field opening hole. The embedding of the loading cabin is designed to provide protection for operation of equipment arranged in the loading cabin; and meanwhile, the design of a thermal control system is facilitated; because of the platform cabin view field opening hole, the loading view field is uncovered; an installation path of the cabin crossing cable cannot affect motion of a suspension plate in the loading cabin, so that power supply and data communication between the antennas and the platform load can be realized. The embedded type solar observation satellite configuration disclosed by the invention has the advantages that physical isolation between the satellite platform cabin and the loading cabin can be realized, so that the precisionand the stability of the solar observation satellite are greatly improved.

The embodiment of the invention relates to a measuring apparatus and correction method of wavelength drift in different view fields for a narrowband light filter. The correction method of wavelength drift in different view fields for a narrowband light filter includes the steps: cutting-in a scaling light source and a diffusion sheet into an optical path on which the narrowband light filter is; scanning the spectrum of the scaling light source through the narrowband light filter; according to the spectrum of the scaling light source, determining the wavelength drift in different view fields for the narrowband light filter; shifting out the scaling light source and the diffusion sheet from the optical path; scanning the spectrum of an observation target through the narrowband light filter; and according to the wavelength drift in different view fields for the narrowband light filter, calibrating the spectrum of the observation target, and obtaining the real spectrum and the velocity field information of the observation target. The measuring apparatus and correction method of wavelength drift in different view fields for a narrowband light filter can be used for small-bore and large-view-field sun observation of space and ground base, such as a full solar disk photosphere and chromosphere image, can also be used for coronagraph observation of space and ground base to finally realize accurate background calibration of wavelength and velocity field, and can be used for small-bore and large-view-field remote sensing to earth, based on the narrowband light filter.

The invention belongs to the solar physics of the field of astronomy in China and provides an automatic extraction method for the sun outline. The method comprises the following steps: aiming at the full-disk monochromatic image of the Huairou Solar Observing Station of the National Astronomical Observatories of China, obtaining the gray scale information of the solar limb by using morphological close operation and erosion operation; then, extracting a limb coordinate by using a self-adaptive threshold method; finally, fitting the limb coordinate by combining a least square fitting method, and thus obtaining a connected solar limb binary image. Compared with other international algorithms, the method can process lower-quality solar observation data with instrument noise and fills the blank of domestic related fields. The method has important significance and practical value on determining the solar disk radius and the earth-sun distance, calculating the position of solar activity in the solar disk and researching the evolution law of the sun outline.

The invention discloses a solar film image timestamp information extraction method based on deep learning, and the method comprises the steps: step 1, positioning and cutting a timestamp information rarea in a solar color ball film image; wherein the timestamp information is year, month, day, hour and minute information used for representing shooting time in the sun color ball film image; step 2,segmenting single characters: further segmenting the characters in the timestamp information area to obtain single characters; and step 3, character recognition: firstly, training a network by adopting a large number of samples, then recognizing the single character obtained by segmentation in the step 2 by using the trained network, and integrating and storing recognition results of the single character. A digital timestamp in a solar observation image film is automatically recognized by a machine, and recognized time information is output. Therefore, the workload of manual identification and time information writing is reduced, the digitization process of the batch of film data can be accelerated, and the precious historical data can be more conveniently used for solar physics research.

The invention relates to a design method of a satellite solar wing configuration to meet the requirement of payload observation to the sun. The method comprises the following steps: 1, analyzing the field of view requirements of payload observation to the sun, and determining the field of view envelope of payload according to the payload working mode; 2, analyze that arrangement requirements of the solar fin in-orbit state, and determining the relative positional relationship between the solar fin and the satellite body according to the variation of the solar illumination angle; 3, analyze that restriction requirements of the carry rocket on the satellite outline size, and determining an optional arrangement form of the load and the solar wing launch state according to the outline state ofthe satellite body; Step 4, according to the constraint conditions determined in the above three steps, embedding the payload solar observation field into the solar wing, defining the layout positionof the payload and the solar wing on the satellite body, and forming a satellite solar wing configuration satisfying the payload solar observation demand. The invention breaks through the functionallimitation that the solar fin is only used for supplying power to the satellite, and enables the solar fin to give consideration to the function of allowing the sunlight to pass through the solar finso as to load the solar observation.

The invention discloses a correlated photon self-calibration solar irradiance spectroradiometer of 266-nanometer pumping. Under a self-calibration mode, absolute spectrum photon rate of a correlated photon light source is acquired by internally arranging a new correlated photon self-calibration radiation calibration light source and integrally designing a self-calibration optical path and a solarobservation optical path, and the absolute spectrum power response calibration of a solar observation optical path simulation detector is achieved; and under a solar observation mode, solar absolute spectral irradiance within a wave band range being 365-976 nanometers is measured, and a solar observation channel observation result is corrected according to a calibration coefficient acquired in theself-calibration mode. High-accuracy observation of solar spectrum irradiance from visual light to near-infrared band is achieved by transferring two different radiation-order dynamic ranges from anangle of a basic principle of calibrating quantum efficiency of a single-photon detector by a correlated photon method, and the scientific problem of traceability of a solar observer in a space platform is solved.

The invention discloses a method for forecasting solar flare outbreak based on a 3D convolutional neural network. The method comprises the following steps: 1, constructing an observation data cube byadopting continuous observation data; 2, training the 3D convolutional neural network model by adopting the training set; and 3, inputting the test set into the trained 3D convolutional neural networkmodel for prediction. According to the method, a series of solar activity area images which are continuous in time are positioned, tracked, intercepted and corrected, so that the problem of image distortion subsequently input into a model can be avoided, and a result is more realistic; and the processed data is matched with a specific 3D convolutional neural network of the method, and time sequence information contained in solar continuous observation data can be fully extracted, so that evolution process information of an activity area is captured, and the accuracy of solar flare forecastingof the model is effectively improved; and meanwhile, due to the fact that continuous sun observation data is used, the complexity of observation data collection and arrangement work is effectively reduced.

The invention discloses a solar activity forecasting method based on spatial feature information of solar observation data, which comprises the following steps of: firstly, respectively training two dichotomy classifiers by using image data of a grade i and a grade j to obtain dichotomy models of different network structures and trained parameters thereof; then loading the obtained dichotomy model and the trained parameters thereof, and obtaining the probability that one picture belongs to the class i by using a classifier trained by the class i data and the class j data; according to the method, an automatic data collection tool is implanted, the data collection period is greatly shortened, the collected data size is greatly increased, the grade of solar flare outbreak is predicted through the convolutional neural network, the prediction effect is good, the prediction success rate is increased through the One-Versus-One scheme, and the prediction efficiency is improved. The multi-classification prediction TSS indexes of the model are 0.7035 +/-0.0703, 0.4893 +/-0.0499, 0.4321 +/-0.2228 and 0.4363 +/-0.3308 respectively, compared with the current international optimal performance index result, the performance is equivalent, and the method has the advantages of being scientific and reasonable, high in applicability, good in effect and the like.

The invention discloses an all-time optical navigation method and device based on the combination of a fixed star and a satellite, and the method comprises the steps: observing the fixed star through a star sensor in a first preset time period, and obtaining a first optimal attitude matrix; observing a satellite by using an infrared optical sensor to obtain a first satellite observation equation; constructing a first index function through elevation information obtained by coupling prior information and a barometer; obtaining a first optimal longitude and latitude; in a second preset time period, observing the sun by using a sun sensor to obtain a sun observation vector; establishing an angle constraint equation of a sun observation unit vector and a satellite observation unit vector; constructing a second index function according to elevation information obtained by coupling prior information and a barometer to obtain a second optimal longitude and latitude; and obtaining a second optimal attitude matrix according to the satellite observation vector of the satellite observation equation and the sun observation vector. According to the invention, high-precision all-time navigation in a satellite radio denial environment is realized, and the problem that radio is disturbed and deceived is effectively solved.

The invention relates to a solar physical observation data processing technology and method. The data processing technology and method are characterized in that a system solves the historically left problem on observation data. The conversion is carried out corresponding to international standards FITs and parameters are read corresponding to CCD sizes and image color level changes in different periods; and virtual processing is carried out. For the calibration and magnetic field component processing problems troubling users, a workflow technology is adopted; and therefore, convenience and high efficiency are achieved. The object-oriented, workflow and man-machine conversation technologies are comprehensively adopted instead of a command line mode adopted by general physical parameter adjustment and a direct graphic method adopted by graphic processing through innovation, so that parameters can be conveniently and dynamically adjusted; and learning and applying are easy. Due to the adoption of the technologies, the processing time is greatly shortened. The adopted technologies are relatively mature, the key is that the technologies are fully applied to the processing for the first time, and a new milestone of simple and efficient data processing is opened up. The observation data processing technology and method can be used for Huairou data processing; a more advanced method is provided for data processing software in the field of the world; future novel observation data processing in China can be integrated in the software; and the software becomes necessary software for related data processing in China and the world.