206 results about "Satellite imaging" patented technology

The invention provides a satellite-ground cooperative in-orbit real-time geometric positioning method and system for optical satellites. The method comprises the following steps: an optical satellite imaging and positioning model suitable for an onboard real-time processing unit is constructed, initial values of onboard positioning model parameters are acquired by calibration parameters or design parameters for camera interior and platform installation relation by a ground laboratory, after the satellite is in orbit, ground calibration field image data is acquired and downloaded, calibration matching and calibration parameter calculation are completed in a ground processing system by using the downloaded calibration field images; calibration results are verified and model parameter annotation is updated. The method and the system aim at limitation of onboard processing environment, and combine the ground processing system, so that a satellite-ground cooperative processing mode is formed, in-orbit high-precision real-time geometric positioning of optical remote sensing satellite is realized, application usefulness and timeliness of earth observation systems are improved, and necessary bases are provided for intelligent and high-efficient remote sensing data onboard real-time processing technology.

An apparatus, system and method for fire suppression and containment is provided in accordance with one embodiment of the invention. A conduit with a plurality of nozzle connections, in various configurations to create specific fire suppressant discharge patterns. Each conduit can be operated individually or connected to another conduit by a predetermined length of hose forming a contiguous system, traversing large areas of land. The invention and components form a multipurpose fire suppression apparatus. The system can be operated remotely or manually. An alternative embodiment can be installed in residential, commercial and industrial applications. Each system can be custom designed based upon environmental engineering requirements and system application-with regard to conduit diameters, material composition, shape, length and nozzle design without leaving the core design. The system components can also incorporate sensors, monitoring devices, robotics (i.e. RM all terrain vehicle) satellite imaging and wireless technology.

The invention discloses a system and a method for the meteorological information-assisted satellite imaging task planning. The method comprises the steps of 1, collecting observation requirements; 2,performing imaging task treatment on an observation target; (wherein the target region divided into small regions of 10 * 10 degrees by dividing longitude and latitude grids in the global range according to a cone projection mode during the task planning process; and the divided small regions are subjected to matching and judging during the cloud cover judgment) 3, performing cloud cover inspection for each imaging scheme (based on a statistical threshold value of 75%), removing pre-arranged plans which do not meet the cloud cover constraint condition, screening out a plan set which most meetsan optimal strategy, arranging plans according to the imaging time and the imaging angle, and generating a final planning scheme; 4, respectively transmitting the information of an imaging scheme and a receiving scheme to a satellite and a ground receiving station. According to the scheme, the cloud cover in each target imaging region can be evaluated before satellite imaging, so that the imaging quality can be obviously improved.

The invention provides a method and a device for collaboratively dispatching tasks among multiple earth observation satellites. The method comprises the steps of acquiring a directed acyclic graph corresponding to an initial to-be-observed task set of each satellite, wherein the directed acyclic graph comprises the content and a time sequence connection relation of each to-be-observed task; screening out overlapping tasks through comparing the directed acyclic graph of each satellite, wherein the overlapping tasks refer to tasks with the number of executable satellites being at least more than two; predicting an execution effect of each overlapping task according to parameters of the executable satellites; acquiring actual execution satellites of each overlapping task according to the predicted execution effect; deleting the overlapping tasks of the executable satellites except for the actual execution satellites in the initial to-be-observed task set, and generating a final to-be-observed task set of the executable satellites. The embodiment of the invention improves the satellite imaging efficiency and the utilization reasonability of satellite imaging resources.

A system for operating an integrated architecture for near real-time satellite communications, comprising a plurality of collector satellites augment by aerial and terrestrial sensing systems that capture a plurality of EO, SAR and / or Signals sensor data of a portion of a region of the surface of the Earth, and a plurality of connector satellites that communicate with at least a collector satellite using a communication interface, and a method for using advanced environmental monitoring to adaptively task a collector satellite.

The invention discloses a determination method of an imaging condition of an agile satellite, comprising the following steps of: predicting and calculating three classic parameters which are MTF (Modulation Transfer Function), element resolution ratio and imaging width and are used for describing basic attributes, thereby determining the weight ratio accounted by all the parameters in an imaging condition determination system and finally determining the imaging condition of the agile satellite. In the determination method, the influence of imaging conditions of an agile satellite camera under various environments and working modes on imaging quality is considered comprehensively, comprehensive determination is carried out, design verification is carried out by utilizing ground simulation, a concise and objective decision-making basis is provided for a satellite user, meanwhile, the digging condition of specific imaging tasks is reflected to the satellite imaging capability. The determination method is the first comprehensive determination method for the imaging condition of the agile satellite in China, and therefore, the blank on the simulation analysis aspect of the satellite imaging condition in China is filled.

The invention discloses a satellite formation realizing method for earth ultra-width imaging, relates to a formation technique of satellite stable imaging, and belongs to the technical field of control and regulation. The method is applied to the problem of distributed ultra-width imaging, which breaks the single-star lower-point imaging mode of traditional satellite imaging and enables the satellite to achieve high-precision ultra-width imaging in the manner of formation imaging by carrying high-precision imaging load and combined with distributed satellite control technology, thereby greatlyenhancing the efficiency of satellite search imaging. The method proposes a distributed satellite formation ultra-width imaging mode based on J2 stability, which solves the problem that the satelliteis unable to achieve continuous imaging on the adjacent areas of the ground caused by small satellite gaze range, narrow imaging width, and the earth rotation.

The invention relates to a satellite demand processing system based on negotiation countermeasure conflict resolution. The method includes that a client acquisition module determines a preliminary access track of a satellite and outputs the preliminary access track to users; the users submit access demand lists to an acquisition list archiving module; the acquisition list archiving module feeds product data to the corresponding users, sorts the rest legal access demand lists by priority and stores and archives the same; an acquisition list processing module extracts acquisition list information in priority order, performs redundancy resolution on time information and space information in the acquisition list information, generates an acquisition mission list and sends the acquisition mission list to a satellite mission planning module; the satellite mission planning module performs strip division on an observation area in the acquisition mission list according to satellite imaging capacity, and combines with satellite orbit access features to generate a satellite observation list; a command generation module generates the satellite observation list into a remote control command, and uploads the remote control command to the satellite; an acquisition list feedback module acquires data information corresponding to the satellite observation list from a ground data processing public management platform of the satellite.

The present invention is a semi-automated process to extract object motion and attributes from utilizing a remote sensing methodology using Earth Observation data from single pass satellite imagery. Many single pass satellite sensors collect imagery that include a panchromatic and multispectral image with a slight temporal offset. The method of the present invention performs image processing, object segmentation, object measurement, image normalization and image matching and velocity calculation to extract physical attributes of the object, object location, and object motion.

The invention provides an in-orbit measuring system for deformation of a satellite large-array-plane antenna based on a fiber grating. The system comprises a light wave generator 1, multiple grating measuring points 3, a light wave demodulator 4 and an information processor 5 which are connected successively via a conduction fiber 2; the light wave generator 1 comprises a main light source and a splitter, and provides light wave needed by the multipath conduction fiber; the multiple grating measuring points 3 are arranged on the surface of the satellite large-array-plane antenna, and used for forming a sensing network; the light wave demodulator is used to demodulate the collected light wave, and further obtains the strain and temperature of each grating sensing point; and the information processor 5 is used to calculate the strain and temperature of each grating sensing point, and obtains the deformation parameter of the surface of the antenna array plane. The invention also provides an in-orbit measuring method for deformation of the satellite large-array-plane antenna based on the fiber grating. Thus, convenience is provided for antenna structure control or signal compensation, and improves the anti-interference performance of satellite imaging.

The invention relates to an SAR satellite simulated on-orbit load data obtaining system and obtaining method. According to SAR satellite imaging parameters, SAR echo data is manufactured and is stored in a task planning computer; a navigation signal simulator and an attitude and orbit control ground equipment synchronically output on-orbit simulated flight relevant excitation to an SAR satellite to execute the simulated on-orbit flight; an imaging planning instruction is sent to the SAR satellite; an imaging mode, radar work parameter information, imaging moment, imaging duration, imaging process attitude information and load data downloading moment are transmitted to the SAR satellite. When the preset SAR satellite imaging moment is reached, an echo signal is sent to the SAR satellite; the SAR satellite packs formed load data; when the preset SAR satellite load data downloading moment is reached, load data receiving equipment receives a load data signal sent by the SAR satellite; demodulation receiving and restoration are performed, so that the load data receiving is completed.

The invention discloses an autonomous operation and control system of an agile imaging satellite. The autonomous operation and control system comprises a ground support system and an imaging satellite. The imaging satellite is equipped with a satellite housekeeping subsystem, an antenna subsystem, rest on-satellite subsystems, a satellite-borne replanning subsystem and a real-time task receiver. After the antenna subsystem receives a multi-source task message, the task requirement message is transmitted to the replanning subsystem, and the replanning subsystem generates a new task planning scheme, on the one hand, the new task planning scheme is transmitted to the antenna subsystem and sent back to a ground operation and control center, on the other hand, an instruction is generated and transmitted to the satellite housekeeping subsystem, and after the operation and control center receives the planning program from the satellite, the control instruction and the digital transmission scheme same with the satellite are synchronously generated, and sent to a measurement and control center and a ground station. The autonomous operation and control system can enhance the ability of the satellite to perform complex tasks; the actual observation efficiency of the tasks on the satellite can be effectively improved; the pressure of a measurement and control channel can be relieved, and the complexity of ground control is decreased; and a response can be effectively quickly made to emergencies.

The invention discloses a hyper-heuristic algorithm-based satellite task planning method. The method includes the following steps that: 1, the priority dominance relation data of a target are obtained; and 2, a tabu search algorithm or a simulated annealing sub-heuristic algorithm is adopted to search priority combinations so as to obtain a planning result. According to the method of the invention, the sub-heuristic algorithm is adopted to search the combined application of the heuristic rule information of multi-angle priorities, and therefore, a super-heuristic algorithm-based and efficiently robust satellite imaging and transmission joint planning method can be provided.

A system for space-based global quick delivery of a disaster relief unmanned aerial vehicle is characterized by comprising a carrying relay transmission spacecraft (1), an autonomous reentry delivery cabin (2) and an unmanned aerial vehicle (3). The carrying relay transmission spacecraft (1) runs on a satellite orbit, the autonomous reentry delivery cabin (2) is connected with the carrying relay transmission spacecraft (1), and the autonomous reentry delivery cabin (2) carries the unmanned aerial vehicle (3). The characteristics that an on-orbit spacecraft can reach any place globally quickly and the characteristics that the unmanned aerial vehicle can go deep into a disaster core area to collect information in a close range are utilized comprehensively. The unmanned aerial vehicle is loaded on the spacecraft to perform on-orbit flight, the global coverage characteristics of the unmanned aerial vehicle are utilized to break through voyage and speed limitation of a conventional spacecraft, the disaster emergency response speed is improved, reentry means is utilized to deliver the unmanned aerial vehicle above a disaster area to perform closing up reconnaissance, the problem that the satellite imaging resolution is not enough is solved, and the disaster emergency response efficiency is improved.

The resolution obtained by an imaging system utilizing separable photons can be achieved by an imaging system making use of entangled photons. Since resolution is not being increased from the separable-photon system, the imaging system utilizing entangled photons can take advantage of a smaller aperture. This results in a smaller and lighter system, which can be especially valuable in satellite imaging where weight and size play a vital role.

The invention discloses a method for inverting underground fluid volume change and three dimension surface deformation using InSAR. For an area influenced by underground fluid motions, firstly, the InSAR technology is utilized to obtain a measurement value of a surface deformation field in a slope distance direction after geographical coding of the area; then InSAR slope distance direction deformation measurement values are utilized to invert depth and thickness of an underground fluid block source in a nonlinear manner; further a combined solution model is established for all surface observation points and the underground fluid block source using satellite imaging geometry and elastic half-space theories; and finally, the least square method is used for computing three dimension deformation of the surface observation points and volume change of the underground fluid block source. The invention breaks through the technical difficulty that InSAR cannot precisely monitor three dimension deformation caused by underground fluid motions, and actively promotes practical development of the InSAR technology. In addition, the invention can obtain results about underground fluid volume change, and can provide important scientific values for reach on the geophysical process inside the earth.

The invention relates to a space camera flutter analysis method based on a target image. The method comprises the steps that an imaging system is built at first, black and white rectangular targets comprising the specific space frequency and high contrast are placed on a collimator focal plane, the targets are illuminated by a high-stability uniform light source to be used as object targets, and are imaged on a camera focal plane through a collimator and a space camera to form clear target images, the gray scale centroid method is adopted for analysis, and an accurate image shift deflection amount is obtained. According to the space camera flutter analysis method, image analysis is combined with the optical measurement fundamental, the image shift is directly measured on an image, the influence of flutter on space camera imaging is directly analyzed, the image shift deflection amount is obtained for the first time, the gap in the prior art is filled, and the basis is provided for analyzing the influences on satellite imaging quality and finally improving and maintaining the satellite imaging quality.

The invention relates to a high-accuracy high-resolution satellite imaging simulation engine and an implementation method. The engine comprises a scenario resolving module, a scenario organization and management module, a two-stage task division module, a ray tracing module and an image synthesis module. According to the engine and the implementation method, a large-scale and complex landform scenario can be quickly rendered based on a ray tracing rendering technology by using a Sender-Worker-Receiver parallel calculation model, a two-stage task division method and a dynamic adaptive scheduling method, the problem of single node performance bottlenecks during data communication is solved, load balance and high expansibility between nodes are ensured, time for satellite imaging simulation is shortened, and the simulation efficiency is improved.

The invention discloses an imaging satellite task planning method considering meteorological information. The method comprises the following steps of loading meteorological data information in a future predetermined time; calculating visible time windows of all to-be-arranged observation tasks of an imaging satellite; obtaining a core stripe of a to-be-observed region; generating a task pre-planning scheme according to the meteorological data information and core stripe data; loading latest meteorological forecast data in a day before a work plan is sent to the satellite; and determining a final task planning scheme according to the latest meteorological forecast data. An assessment method for judging whether a cloud layer causes shielding to satellite imaging or not has the advantages of simplicity, a relatively small calculation amount and a high calculation speed.

The invention relates to a staring-imaging-based in-orbit signal-to-noise ratio test method of a satellite. Repeated imaging of an earth surface uniform region is carried out by a satellite with an ultra-high time resolution and a high spatial resolution; on the premise that the illumination condition and the surface radiation characteristic are consistent basically, statistics of mean values of detector cells and standard differences of the imaging at the uniform region is carried out and ratios of the mean values and to standard differences are used as pixel signal to noise ratios; and then a mean value of a plurality of pixel signal to noise ratios is used as an image signal-to-noise ratio. With the method, an influence caused by inconsistency of the pixel response spaces can be eliminated. When statistics of the standard differences of imaging data of each pixel at multiple times is carried out, uncertainty of repeated sampling is mainly reflected; and thus the noises can be effectively retrained in terms of numerical value and the actual signal to noise ratio of the satellite image can be reflected, thereby evaluating the remote sensing satellite imaging capability of the geosynchronous orbit objectively. Therefore, the method has the practical application value in development of in-orbit testing and in-orbit operation state image quality evaluation in satellite ground system engineering.

The invention provides a geostationary satellite imaging navigation and registered orbital motion compensation method. The method includes the following steps: a first step, writing an expression of adesired target point coordinate on an earth ellipsoid corresponding to a preset scanning mirror rotation angle according to a scanning reflective mechanical optical path model of a remote sensing instrument while a satellite is at a nominal fixed point; a second step, calculating a desired scanning mirror rotation angle while the satellite is at an orbital position after drifting and points to aground desired target point; and a third step, using the desired scanning mirror rotation angle to subtract the preset scanning mirror rotation angle to acquire an orbital motion compensation amount.The acquired image and an earth nominal grid image generated by the satellite at the nominal fixed point are consistent, errors are controlled in an indication range, and the research and developmentdifficulty of a system can be lowered, and the realizability of engineering can be improved.

The invention relates to a resource satellite imaging task arrangement and service method, which has functions of arranging task; calculating Greenwich mean time, Peking time and local time of a position when the satellite travels through the position; calculating earth station coverage area and running rate of the satellite; calculating distance between arbitrary two points on surface of the earth; calculating corresponding relation of side-sway distance and side-sway angle; calculating corresponding relation of latitude and longitude as well as PATH and ROW; calculating corresponding relation of date and PATH number; calculating corresponding relation of loop number and the PATH number; converting the data and data product; calculating date corresponding to a data adding a number of days; converting second product and data; and converting degree, minute, second and number of degrees. According to the sun synchronization and regression characteristic of the satellite, the invention calculates conditions of other track including passing data and image time by using a track (such as a track passing through Beijing) as reference, arranges imaging with high efficiency and satisfies various demands of users.

The invention provides an agile imaging satellite linear scan strip pre-generating method based on a point target and a satellite three-axis gesture rapid determining method, relates to the field of spacecraft imaging mission planning, and aims to solve the problems that related linear push scanning strip generating methods do not exist in the area of satellite imaging planning in the prior art, push scanning imaging mode realized by agile satellite can not be considered in target planning caused by ignorance of satellite yaw motor performance in an existing satellite gesture determining method with two-axis gesture calculation, and thereby target planning performance is lowered. Geodetic longitude and latitude of each target point to be observed are converted into plane right angle coordinates through screening point target, calculation is optimized, linear scan strips are obtained, and then new target points corresponding to the target points to be observed are determined through the obtained linear scan strips. Corresponding geodetic coordinates of each new target point are calculated, parameters of satellite three-axis gesture are calculated, and the satellite three-axis gesture is determined. The agile imaging satellite linear scan strip pre-generating method based on the point target and the satellite three-axis gesture rapid determining method are suitable for satellite imaging target planning.

The invention provides an extracting method for fixed star sensitive east and west parameters of stationary satellite imaging navigation and registration. The extracting method comprises the following steps of obtaining a changing curve of a total gray value of pixels of each line along with time; obtaining a moment that a fixed star image center crosses a center line of the pixels of the line; fitting a motion law of the fixed star image center in east and west line coordinates of a satellite remote sensing detector array; obtaining a moment that the fixed star image center crosses a center line of the east-west direction of the satellite remote sensing detector array. According to the extracting method provided by the invention, high-frequency error of star positions caused by factors such as optical imaging of the detector, circuit noises, high-frequency wobble of a satellite and the like can be eliminated by multiframe data information fusion processing and curve fitting, thereby improving the identification accuracy of fixed star position parameters. The extracting method can be used for stationary satellite imaging navigation and registration, and has important significance for improving on-orbit thermal deformation precision of a remote sensing imaging system and the imaging navigation and registration processing property by acquiring parameters such accurate time and the like that the fixed star crosses the center of the detector array.

The invention discloses a multi-satellite imaging task planning method, which comprises the following steps of: establishing a task model, and representing all point target tasks by using the task model; taking the orbital circles as a reference, taking tasks in the orbital circles as nodes of the clustering graph model, and constructing undirected edges among the nodes in the clustering graph model based on clustering constraint conditions to obtain an imaging task clustering graph model; aggregating the point target tasks meeting the clustering constraint condition into clustering tasks based on a heuristic rule, and calculating side swing angles of the clustering tasks based on a median theorem; constructing and utilizing constraint conditions and an objective function of task planningto construct a task planning directed acyclic graph model corresponding to the imaging task clustering graph model; and based on the task planning directed acyclic graph model, performing task planning by adopting a maximum and minimum ant colony algorithm to obtain a multi-satellite imaging task planning scheme. Under different data scales, a satisfactory task planning result can be obtained, andthe method has good stability.

A satellite side-sway angle obtaining method based on the image characteristics comprises the following steps: (1) obtaining the imaging date of a remote sensing image; (2) choosing a proper landmark on the remote sensing image, and obtaining latitude information of the landmark; (3) according to the parameters of the satellite orbit, obtaining the imaging local time (Tlocal) of the latitude of the landmark; (4) according to Tlocal, calculating the solar time angle (Tangle); (5) calculating the solar declination [delta] of the imaging date; (6) calculating the solar altitude according to [delta], Tangle, and the latitude (Lat) of the landmark; (7) measuring the shadow length (Lshadow) of the landmark on the remote sensing image, and calculating the height of the landmark (Height) by combining the solar altitude; (8) measuring the projection difference (Lproject) of the landmark on the remote sensing image, and finally calculating the side-sway angle (Sangle) when satellite imaging is carrying out according to the Height. The provided method can obtain the side-sway angle of a satellite through a remote sensing image by using the remote sensing satellite imaging mechanism and sunshine geometrical relationships, when the ephemeris data cannot be obtained.

A system for use in locating a fault in a power generation and delivery system is provided. The system includes a fault detection module configured to detect an occurrence of the fault and to generate a fault event notification, a satellite imaging system configured to acquire satellite image data, and a fault location module coupled to the fault detection module and to the satellite imaging system, the fault location module configured to receive the fault event notification from the fault detection module, receive satellite image data of a target area that includes the fault from the satellite imaging system, and determine the location of the fault based on the satellite image data.

The invention discloses a quick rotary ultra-width pendular satellite imaging method, and relates to ultra-width pendular imaging methods. By the aid of the quick rotary ultra-width pendular satellite imaging method, the problems of incapability of meeting ultra-width imaging requirements on ground regions by conventional imaging methods and incapability of carrying out seamless splicing imaging on imaging regions of two adjacent orbits of a single satellite can be solved. The quick rotary ultra-width pendular satellite imaging method includes steps of firstly, computing the widths L<5> perpendicular to orbits; secondly, computing the widths L<1> in flight directions; thirdly, determining whether critical values of distances L2 of the centers of the optical axes of detectors on tracks of sub-satellite points on earth surfaces are the widths L<1> of the flight directions or not; fourthly, computing the spinning speeds of the detectors along the directions of the orbits; fifthly, computing corresponding resolution ratios A<c> of the detectors during ultra-width imaging under various orbit conditions; sixthly, computing horizontal frequencies F of CCD (charge coupled devices); seventhly, computing superposition distances L<6> among imaging regions of every two corresponding orbits and the like. The quick rotary ultra-width pendular satellite imaging method has the advantage that the quick rotary ultra-width pendular satellite imaging method can be applied to the field of ultra-width pendular imaging.

The invention provides an intelligent satellite earth observation pattern base acquiring method and system. The intelligent satellite earth observation pattern base acquiring method includes the steps that each kind of single ground feature scene is subject to satellite imaging analog simulation experiments, ground feature characteristics are analyzed, and observation pattern parameters of each kind of single ground feature scene are selected; satellite imaging analog simulation experiments of multiple ground feature scenes are carried out, coupling relations of observation pattern parameters of the multiple ground feature scenes are analyzed, and the observation pattern parameters of the multiple ground earth scenes are selected; an intelligent satellite earth observation pattern base is built according to the selected observation pattern parameters of each kind of single ground feature scene and the selected observation parameters of the multiple ground earth scenes. Due to the adoption of the intelligent satellite earth observation pattern base acquiring method and system, observation pattern parameters of all kinds of scenes can be selected through imaging analog simulation experiments of single ground feature scenes and imaging analog simulation experiments of multiple scenes to build the complete intelligent satellite earth observation pattern base for targeted actual intelligent satellite earth observation selection. The intelligent satellite earth observation pattern base acquiring method and system have wide application value.

The invention provides a remote sensing satellite system and a video image real-time transmission method thereof. The remote sensing satellite system comprises a satellite imaging device mounted on a satellite and used for acquiring a video image of a target object in real time; a ground receiving device arranged on the ground and used for receiving a video image in real time; and a data transmission device mounted on the satellite and used for transmitting the video image to the ground receiving device. The remote sensing satellite system and the video image real-time transmission method thereof provided by the invention solve the problems of dynamic target detection, recognition and tracking, and satellite rapid application and so on that are difficult to be realized by the existing satellites, so that users can quickly acquire video information of a target area, and the rapid application ability of the satellites in response to unexpected things can be improved drastically.