278 results about "Space object" patented technology

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention relates to a robot sensing and decision-making method based on a lightweight multi-modal large model. The method comprises the following steps: constructing a semantic voxel map; collecting multi-modal data based on the semantic voxel map and preprocessing the multi-modal data, wherein the multi-modal data comprises visual data, point cloud data and a target semantic tag; performing feature extraction on the preprocessed multi-modal data, and performing dynamic cross-modal attention fusion to obtain multi-modal fusion features; inputting the multi-modal data into a lightweight multi-modal large model at the same time, and performing semantic analysis to obtain global space object semantic description; and based on the global space object semantic description, the target and direction embedding vector and the multi-modal fusion feature, a reinforcement learning algorithm is adopted to carry out hierarchical navigation decision making to obtain a target decision, and the target and direction embedding vector is a preprocessed target semantic tag. And the accuracy, timeliness and adaptability of robot perception and navigation decision making in a complex scene are improved.

A system can use a plurality of co-located telescopes to generate enhanced telescopic imagery of space objects. The system may be configured to receive telescopic imagery data of a plurality of space objects obtained from the plurality of co-located telescopes. The system can receive at least two imaging criteria. The available imaging criteria can include a target signal sensitivity comprising a minimum signal to noise ratio (SNR), a target number of spectral bands comprising a minimum number of spectral bands, a spectral range associated with one or more of the spectral bands, a location of the plurality of co-located telescopes, a target data cadence comprising a minimum number of frames per minute, a target number of space objects to be tracked, a target minimum spatial resolution, among others. The system can transmit instructions to the plurality of telescopes and generate enhanced telescopic imagery.

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention discloses a method, a system and a device for predicting hoisting of a balance beam of a crane. The method comprises the following steps: acquiring operation data of the balance beam in an operation space; establishing a measurement range model according to the position data; calculating an adjustment value of each lifting hook according to the inclination angle data and the spatial position data; according to the data of the horizontal distance between the balance beam and the surrounding space object, judging and determining a safety area of the operation of the balance beam; calculating the stress and strain of the balance beam by using the structural parameters of the balance beam; calculating an attitude angle in the lifting operation process by using acceleration data of the lifting operation of the balance beam; and analyzing the calculated data by using a fusion algorithm to obtain a balance beam hoisting operation model, a monitoring index and a prediction result. The system comprises modules corresponding to the method, the device comprises an ultrasonic distance measuring sensor, an inclinometer, an acceleration sensor, a processing module and a display device, the operation efficiency can be guaranteed, and the operation safety can be improved.

The invention relates to a system and method for autonomous navigation of a host satellite equipped with moving and orienting means, a unit for controlling these means, and at least one on-board image-acquisition camera, said method comprising the following steps: acquiring (E1) a plurality of images; default processing of said images, referred to as long-range processing (E2), configured to detect and identify space objects and to calculate their relative orbits; conditional processing of said acquired images, referred to as short-range processing (E3), configured to estimate the attitude of at least one of said space objects, referred to as target object, detected during the long-range processing, this step being implemented when said long-range step detects at least one space object located at a distance estimated to be less than a predetermined threshold distance; determining (E4) a possible rendezvous between at least said target object and the host satellite; preparing and transmitting instructions (E5) to said control unit of said moving means based on at least one rendezvous and / or risk of collision determined in the previous step.

A method of generating a simulated image for training a model to detect resident space objects (RSOs), a method of training the model, and a method of detecting RSOs are provided. The method includes generating a foreground of the simulated image including RSOs by calculating coordinates of an imaging satellite at a given time, determining an area of interest given a field of view (FOV) of the imaging satellite, and calculating coordinates of all RSOs and saving the coordinates if the RSO is within the area of interest. The method further includes generating a background of the simulated image including stars by querying a star catalogue database for coordinates of all stars that fall inside the FOV, adding noise, and translating RSO and star coordinates to pixel coordinates. The method further includes generating the simulated image by choosing an imaging mode, setting an exposure time, and rendering the simulated image.

A system includes a plurality of satellites orbiting around a celestial body in a plurality of orbital planes. Each satellite includes an imaging device having a field of view (FOV) to capture an image of a sky that includes celestial image features of resident space object (RSO), stars, and / or planets. The satellite processor is configured to input the image data for each image into a pre-processing software pipeline to generate for each image a contrast-enhanced image data replica of each image, and an enhanced image data replica of each image, to receive from an output of a known-unknown RSO split data processing pipeline, a determination that a candidate RSO is a known RSO stored in an RSO catalog, or an unknown RSO, and to assign to the candidate RSO based on the determination, an RSO ID of the known RSO listed in the RSO catalog, or a new RSO ID.

The invention discloses a power transmission line insulator defect detection method based on deep learning, and the method comprises the steps: S1, obtaining an aerial image, carrying out the preprocessing of the aerial image, and generating an insulator defect detection data set; s2, based on a YOLOv8n model, introducing a space object attention module (RCS-OSA), and improving the feature extraction capability under a complex background; s3, adding an extrusion excitation network (SENet) in the neck network of the model to enhance the feature expression ability between channels; s4, constructing a small target detection layer, and adding a high-resolution feature map (160 * 160) to capture small defect target information; s5, optimizing a detection head by using multi-scale feature fusion and a dynamic label distribution strategy, and improving the recognition precision of the model on insulator defects under a complex background; and S6, outputting defect positions, types and confidence coefficients based on a detection result, and generating an electric power inspection report. According to the method, the accuracy and robustness of insulator defect detection under the complex background of the power transmission line are effectively improved, and the method has relatively high applicability and real-time performance.

The invention discloses an intelligent generation and application method and system for structural data of an engineering drawing, and the method comprises the steps: obtaining the engineering drawing, analyzing the engineering drawing, and determining a data relation, graphic data, text data and image data reflected by the engineering drawing; screening, identifying and combining the data relationship, the graphic data, the text data and the image data to obtain a drawing object, a component object and a space object; and outputting engineering drawing structured data based on the drawing object, the component object and the space object, and applying the engineering drawing structured data. According to the method, the engineering drawing is analyzed and the data of the engineering drawing is structured, so that the processing efficiency and accuracy of the engineering drawing are improved.

The invention discloses a full-process closed-loop quick response satellite collision avoidance method, which comprises the following steps of: 1, observing and acquiring an orbit state of a space object, and then carrying out multi-source data fusion so as to construct a space object database; 2, screening out high-risk collision sources which have the possibility of collision with the own satellite; 3, obtaining a determined high-risk collision source according to the track state historical record of the possible high-risk collision source and the own track state; 4, generating an initial evasion maneuvering scheme, and optimizing the initial evasion maneuvering scheme through a multi-objective optimization algorithm; and obtaining a final evading maneuvering scheme for subsequent execution. And 5, according to the engine startup and shutdown time and the thrust vector contained in the final evasion maneuver scheme, the satellite engine is controlled to work with the specified thrust vector within the given startup and shutdown time, and collision evasion maneuver is executed. Compared with a conventional method, the method has the advantage that the response speed is higher.

The system and method for decelerating space objects moving at high velocities are provided. The system comprises at least one closed volume containing a combination of gas, liquid, solid particles, or a mixture thereof. The volume can be transported to the targeted location using a range of means, including a chemical gun, light gas gun, electromagnetic coil gun, superconducting quench gun, a rocket, or a combination thereof. The volume is strategically positioned on the trajectory of the moving object. Upon penetrating the walls of the volume, the object passes through it, experiencing deceleration.

We present a ground-based laser system for searching, ranging, and tracking that actively illuminates small resident space objects (RSOs) in low Earth orbit (LEO) and observes position and transit-time of reflections, enabling orbital custody of most one-to-few centimeter-sized objects. A diode-pumped alkali laser (DPAL) augmented with mode-locking and Q-switching serves as an illuminator and offers exceptionally high spectral brightness due to its output beam's sub-nanosecond pulse duration and picometer-level spectral linewidth. Kilohertz fast-rastering enables interrogations of distinct few-meter-sized sky-patches at megahertz rates. Paired on the observation side with one or more telescopes outfitted with Faraday anomalous dispersion optical filters (FADOFs), image intensifiers, multi-pixel arrays, and nanosecond timing, the combined system could offer nearly background-free discoveries of RSOs every hour, even during daytime. Periodically re-flashing previously discovered objects to maintain orbit custody expends only a small fraction of total observing time.

The invention discloses a space target three-dimensional reconstruction realization method based on radiation field generation. The method comprises the following steps: acquiring image data of a space target for preprocessing; an improved generated radiation field network is built, and an image is sampled to obtain an image patch; obtaining a group of three-dimensional sampling points in a layered sampling mode, performing multi-frequency position coding, splicing with a shape vector, sending into a shape coding layer to obtain feature representation, and inputting into a color head together with a sight direction code and an appearance variable to calculate the color of the sampling points; for each ray, colors of all sampling points are synthesized into a final pixel color based on a volume rendering equation, and the final pixel color is combined into a patch image to be output; inputting the real patch and the patch image into a discriminator, and calculating confrontation loss and discrimination loss; and acting the weight obtained by training on a generator to obtain rotating videos of the space target at different visual angles. The method can realize three-dimensional reconstruction of a space target, and has the advantages of flexible data driving, cross-view geometric consistency, efficient training and the like.

Some of such technologies enable a technique for calibrating a radar based on using -A- an elemental antenna, which can be embedded on a housing hosting a set of antenna elements, or -B- an antenna mounted to a reflector (108). Some of such technologies enable a radar site containing a first ID phased array (112) and a second ID phased array (112), where the first ID phased array sends a set of signals and receives a set of reflections based on the set of signals, and the second ID phased array receives the set of reflections.

A display system can be configured to receive, via a user interface, a first identifier associated with a first space object and determine a first maneuver of the first space object. The first maneuver can include a perturbation of the path of the first space object. Based on the first identifier and the first maneuver, the display system can identify one or more path parameters associated with a path of the first space object and generate a display interface. The display interface can include a longitude-time graph having a longitude axis spanning from a lower-longitude limit to an upper-longitude limit and a time axis spanning from the lower-time limit to the upper-time limit and an indication of the one or more path parameters.

Methods and systems of creating accurate data representations of the positions and other characteristics of target space objects using data from a plurality of space-borne artificial satellites and ground-based sensors. Such methods and systems are deployable either on a single satellite, on a plurality or swarm of satellites, and / or in a ground-based system. Various artificial intelligence and machine learning processes described herein are employed to generate a latent data representation of passively-received broad spectrum multi-modal signal data systematically integrated with advanced multi-sensor data fusion algorithms.

An in-vehicle-object detection method for a radar device includes: a) obtaining multiple receiving signals corresponding to multiple space objects by an antenna array of the radar device; b) computing multiple first distances between the antenna array and the multiple space objects based on the multiple receiving signals; c) filtering a background noise of the multiple first distances to obtain multiple second distances between multiple indeterminate objects of the multiple space objects and the antenna array; d) performing a beamforming based on the multiple second distances to compute angle information corresponding to each of the multiple second distances; e) generating a distance-angle heatmap including multiple regions of interest (ROIs); and f) determining whether each ROI in the distance-angle heatmap is associated with a human feature to decide whether each of the indeterminate objects is related to human or unhuman.

Various embodiments comprise a multi-agent spacecraft system for rendezvous and proximity operations. The spacecraft system comprises a chief spacecraft and a deputy spacecraft. The chief spacecraft maneuvers to the orbit of a Resident Space Object (RSO) and deploys a deputy spacecraft to rendezvous with the RSO. The deputy spacecraft maneuvers to the RSO and senses the RSO during the rendezvous and proximity operations maneuver. The deputy spacecraft generates a Three-Dimensional (3D) surface reconstruction of the RSO based on the sensing. The deputy spacecraft determines a roll rate and a relative trajectory of the RSO based on the sensing. The deputy spacecraft returns to the chief spacecraft.

The invention discloses a space target monitoring constellation configuration optimization method and system considering complex constraints, and belongs to the technical field of aerospace mission design and optimization. The method comprises the following steps: firstly, constructing a discrete orbit modal library meeting regression orbit dynamic resonance conditions; constructing generalized hybrid design variables consisting of integer indexes and real number fine tuning quantities on the basis of the library; establishing an optimization model taking the space volume coverage rate, the maximum revisit time and the system construction cost as targets and taking illumination, dynamics and maneuvering capability as constraints; performing rapid analysis and coarse screening on invalid links through track geometry; and finally, performing global optimization by using an improved non-dominated sorting genetic algorithm to obtain a Pareto optimal constellation configuration set. According to the method, accurate evaluation of the three-dimensional space target coverage efficiency is realized, the physical feasibility and long-term stability of a configuration scheme are ensured, and a high-dimensional multi-target optimization problem is efficiently solved.

The invention provides a data processing method based on image information fusion, which can be applied to the technical field of space object detection, and comprises the following steps: acquiring M frames of long exposure images and N frames of short exposure images; extracting information of a dark space object forming a point image from the long-exposure image to obtain a function that the motion trail and the flow of the object change along with time; extracting information of a dark weak source from the short exposure image, wherein the information of the dark weak source comprises a first position and a first flow; calculating a second position and a second flow of the object at the short exposure image acquisition moment based on the motion trail and the function of the flow changing along with time; determining the real position and the real flow of the object based on the position error and the flow error; and obtaining dark space object observation data. And high-precision positioning of the object in the dark space is realized by fusing information of the object in the dark space in different exposure images. The invention further provides a data processing device and equipment based on image information fusion and a medium.

A database (102) of a rocket launch assistance device records orbit forecast information of a mega-constellation satellite group (301) that is acquired from a space information recorder included in a mega-constellation business device and space object information that is acquired from a rocket launch business device. The orbit forecast information of the mega-constellation satellite group (301) is composed of a prediction value of an orbit of at least one representative satellite (331) out of the mega-constellation satellite group (301) and a prediction value of an orbit of a constituent satellite (332), which is a value relative to the prediction value of the orbit of the representative satellite (331).

Systems and methods of the present disclosure enable simulation of imaging of resident space objects (RSOs) by one or more space-based image sensors. The simulation includes obtaining a satellite constellation configuration having satellite configuration parameters for at least one satellite in a constellation of satellites. The simulation also includes obtaining an RSO configuration having RSO configuration parameters RSOs. The simulation may use the satellite and RSO configuration parameters to simulate constellation ephemeris data for each of the satellites and RSOs. Based on the position of each RSO and satellite, detectability of each RSO by each satellite is simulated based on a photometry simulation using the satellite configuration parameters, including sensor characteristics of a simulated sensor. Imagery may also be simulated based on an image generation model, the sensor configuration, the photometry simulation and at least one background model.

The invention relates to the technical field of aerospace, in particular to a space debris environment quantification method based on risk entropy, and the method comprises the steps: S1, discretizing an evaluation time range into a plurality of time periods, and recording the duration of each time period as delta t; any time period tj can be expressed as tj belongs to [(j-1) * delta t, j * delta t]; j < = N, where N represents the total number of time periods; simulation is carried out, and it is assumed that N + 1 possibilities exist in the in-orbit collision disintegration condition of the space object objk; specifically, if N time periods exist, there is N possibilities for the space object to collide and disintegrate; if the space object is still not disassembled at the end of simulation, judging that N + 1 possibilities exist in collision and disassembly of the space object; s2, calculating a collision probability in a time period; and S3, calculating a risk entropy according to the collision probability, and judging the influence of the space object on the space debris environment according to the risk entropy. The space debris environment quantification method based on the risk entropy can be used for quantification of uncertainty of the space debris environment.

A space surveillance method for detecting space objects in orbit around the Earth in images captured during the daytime, the method including the following steps: capturing a plurality of infrared images of the daytime sky using a camera including at least one infrared sensor, detecting space objects in orbit around the Earth on the basis of the images, the detection of bright spots being implemented by a deep-learning artificial intelligence system, and identifying each object detected from a catalogue of known space objects in orbit around the Earth.

A display system can be configured to identify a space object and an object alert associated with a change in one or more movement parameters of the space object. The system can generate data configured to display a display region and an object alert indicator within the display region. The system can display the object alert indicator at a location within the display region and display, within a second display region, a listing of a plurality of alerts comprising the object alert. The system can receive a user selection of an alert from the plurality of alerts configured to be displayed in the second display region and automatically generate updated data configured to display an updated display region based on the user selection of the alert. The updated display region can include a panned, rotated, and / or zoomed perspective of the display region.

To continuously provide service while avoiding collision with a space object, by control of orbits of satellite groups and control of passage timing.SOLUTION: A megaconstellation business device is a business device for managing 100 or more satellite constellations. The satellite constellation provides service by coordination between satellite groups. The megaconstellation business device includes a satellite constellation formation part 11 for forming a satellite constellation having a plurality of orbital planes in which a plurality of satellites fly at the same nominal orbital altitude on the respective orbital planes. The megaconstellation business device includes a satellite constellation formation part 11 for continuously providing service while avoiding collision, by control of orbits of satellite groups and control of passage timing, after having predicted possibility of collision with a space object falling down in an orbit, a launching rocket, a satellite transiting in the orbit, or debris.SELECTED DRAWING: Figure 28

The embodiment of the invention provides a space object processing method and device, a storage medium and a program product. In the object processing method, a first virtual object can be moved to a target placement surface in a target space in response to a placement operation on the virtual object in the target space. In the process that the virtual object moves towards the target placement surface, the virtual object can be adjusted to a target posture, and the target posture is the posture that the target adsorption surface is placed on the target placement surface. Furthermore, before the virtual object is in contact with the target adsorption surface, the posture of the virtual object is adjusted to the target posture that the target adsorption surface is placed on the target placement surface, so that the risk of spatial position conflict between the virtual object and the target placement surface can be reduced in the adsorption process of the target adsorption surface and the target placement surface; therefore, the mode penetrating phenomenon in the mixed reality interaction process is reduced to a certain extent, and the reality sense of object placement operation in the target space is improved.

The invention discloses a spacecraft long-term collision risk assessment method, and belongs to the field of aerospace. The implementation method comprises the following steps: dividing space objects into a plurality of space object groups according to a geocentric distance, a right ascension, a declination, an orbit inclination angle and an area-mass ratio, selecting the density of the object groups as the macroscopic representation of the space debris environment, considering multi-source environmental factors such as atmospheric resistance, and establishing a space debris environment macroscopic representation and rapid evolution model by adopting a continuity equation; giving a numerical solution of the evolution model; the density of a space object in a certain volume element, the density of a spacecraft, the collision sectional area and the collision speed are calculated respectively, then the long-term collision probability of the spacecraft and the space object is calculated, the long-term collision risk of the space station is evaluated based on a long-term collision risk macroscopic evaluation method, and the safest orbit of the space station is determined according to the evaluation result. Satellite and constellation launching and task post-processing strategy optimization, space traffic management and space debris treatment are supported.

The invention discloses a space object sensing method based on a privacy protection camera and a radar, and the method comprises the steps: obtaining the three-dimensional space characteristics of a current space through the radar, judging whether a human body exists in the current space or not through the three-dimensional space characteristics, and starting the privacy camera to collect a global image if the human body exists in the current space; obtaining two-dimensional space features of the current space through the global image, and fusing the two-dimensional space features and the three-dimensional space features of the current space to obtain fused space features of the current space; inputting the fusion feature of the current space into a pre-trained object recognition model to obtain an object type of the current space; interference source labels and universal furniture labels are marked according to the object types of the current space, the current space objects with the interference source labels are filtered, and universal furniture distribution of the current space is obtained; and according to the current space general furniture distribution, radar detection parameters are adjusted according to detection areas, and detection thresholds of different detection areas are obtained.