213 results about "Space object" patented technology

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.

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 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.

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.

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.

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.

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.

Disclosed is a ground-based radar system (1) for observing space objects (A) in orbit, the radar system (1) comprising at least one transmit antenna (2) for transmitting incident electromagnetic waves (S) and at least one cylindrical parabolic reflector (6), the cylindrical parabolic reflector (6) being fixedly mounted and comprising a reflective outer surface (7) suitable for concentrating the incident electromagnetic waves (S) into a beam of determined pointing direction (D), the reflective outer surface (7) being exposed to bad weather, the radar system (1) comprising at least one de-icing fluidic network (10) extending under the reflective outer surface (7) of the cylindrical parabolic reflector (6), the de-icing fluidic network (10) being controllable between an inactive mode (OFF), and an active mode (ON) in which a de-icing fluid (F10) flows through the de-icing fluidic network (10) in order to de-ice the reflective outer surface (7) so as to preserve the determined pointing direction (D).

The invention discloses a ground-based radar space object long-time energy accumulation method based on an orbital element model, and the method comprises the following implementation steps: 1, building an orbital element parameter space, and mapping the grid points of the parameter space into the distance between a target and a radar; and step 2, calculating an envelope position and a phase which need to be compensated according to the mapped distance history at each parameter space grid point. And step 3, compensating a corresponding phase for the echo signal after pulse compression along the calculated envelope position, and then performing coherent superposition, thereby realizing long-time coherent accumulation of echo energy. According to the method, the orbital elements are adopted to construct the parameter space, energy accumulation is carried out in the parameter domain, due to the fact that the orbital elements can better represent the actual motion of a space object, the energy accumulation effect can be improved, meanwhile, the orbital elements are small in parameter space dimension, and the algorithm calculation amount can be greatly reduced.

A system and method for decelerating space objects are provided. The system comprises at least one enclosure that is inflated by a medium, such as a gas, liquid, solid particles, or any mixture thereof. The enclosure can be transported to a predetermined orbital location in the path of the space object. Upon penetrating the enclosure membrane, the object passes through the medium and is thereby decelerated leading to decay of its orbit and / or disintegration thereof.

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.

A space traffic management device (100) mounted in a mega-constellation business device (41) specifies one to a plurality of representative satellites from a mega-constellation satellite group flying on orbits having the same nominal orbital altitude, and has quasi-real-time high-accuracy orbital information of the representative satellite and orbital information relative values of constituent satellites other than the representative satellite, relative to the representative satellite. The space traffic management device (100) shares the quasi-real-time high-accuracy orbital information of the representative satellite and the orbital information relative values of the constituent satellites relative to the representative satellite, with the space traffic management devices (100) mounted in a plurality of business devices.

System and method for prediction and avoidance of RF interference for a satellite from one or more of resident space objects (RSOs) includes: obtaining orbit data and transmission data for the satellite and the plurality of RSOs; calculating a visibility window; performing comparison of transmission parameters; calculating an orientation of each of the RSOs; when there is a match of transmission parameters and the orientation is within a predetermined threshold, adding the compatible RSO to a compatible RSO list; generating a course of action (COA); scoring each of the compatible RSO; selecting a best scored COA; scheduling the first course of action; and autonomously executing the first course of action by the satellite to avoid RFI.

An object of the present disclosure is to provide a space surveillance and tracking radar that can analyze a risk of collision between space objects and a risk of falling of space objects and list the space objects, that is, can be specialized in surveillance and tracking of the space objects, and an analysis method of a space surveillance and tracking radar.

A monitoring system (1) for an orbiting space object (5) comprising a ground-based radar system (2) (7) including an antenna (6) with a controllable pointing direction for moving a space observation window (11) within a field of view (12), the pointing direction having a predetermined value (Zref) associated with the space object (5), the monitoring system (1) comprising ground-based optical sensors (3) (7) and a control unit (4) configured to determine a first orbital restitution (O1) from first positions (P1) of the space object (5) measured by the optical sensors (3), and, if the first orbital restitution (O1) crosses the field of view (12) of the radar system (2) outside the space observation window (11) associated with the predetermined value (Zref) of the pointing direction, to determine a command for the pointing direction of the antenna (6). Abstract figure: Figure 1

A device for radiolocation of objects in space (100), comprising: a frequency-modulated continuous-wave FMCW generator (101), a transmitting-receiving antenna (102) connected to the generator (101), a non-linear quadripole (103A) squaring the input signal, connected at its input to the generator (101) and to the antenna (102), and at its output to a filter (104A, 104B).A ground penetrating radar system (200) adapted to detect wave-reflecting objects (301) located in the vicinity of a wave-propagating medium (300), comprising: the device for radiolocation of objects in space (100), an echo signal amplifier (201), an analogue-to-digital echo signal converter (202) and a processing and visualisation circuit (203).

The invention relates to a satellite system (100) for monitoring and detecting space objects (102) in near-celestial space, in particular for monitoring and detecting space debris, preferably for determining at least one property of the space objects (102), comprising satellites (108, 110, 112, 114, 160) arranged on at least one first principal orbit (104), a torus-shaped monitoring area (116) extending around the celestial body, wherein each of the satellites (108, 110, 112, 114, 160) has an observation device (164) arranged and configured to generate images of space objects (102) within an observation field (108b, 110b, 112b, 114b) and to image space objects (102) within the torus-shaped monitoring area (116), at least one Control device (166) which is arranged and designed to align the observation fields (108b, 110b, 112b, 114b) in such a manner,that images of the space objects (102) located in the torus-shaped monitoring area (116) are generated.

The application discloses a kind of based on photometric signal's space target open set identification method and device, belong to target identification technical field.The method includes: obtaining multiple training samples;Training sample is generated for the photometric signal of in-library space target;Each training sample is preprocessed into normalized observation sequence, and multiple signal features are extracted, to train identification model using multiple training samples, so that identification model determines the rejection threshold of each category in-library space target;The photometric signal of the target to be identified is preprocessed into normalized sequence to be identified, and multiple signal features to be identified are extracted from normalized sequence to be identified, multiple signal features to be identified are input into identification model, so that identification model determines the identification result of the target to be identified according to the rejection threshold of each category in-library space target;Identification result in-library space target or out-of-library space target.The application has higher identification accuracy to in-library space target and out-of-library space target.

A multi-task, multi-radar resource scheduling method for space object detection is proposed. This method constructs an allocation relationship model between detection tasks and detection equipment, establishing an objective function that optimizes the overall task priority and overall equipment time utilization. A genetic algorithm is used for combinatorial optimization to find an optimal equipment allocation scheme for all search tasks. Based on the search task planning results based on the genetic algorithm, the system is updated and tasks are transformed. The remaining tracking tasks and tasks transformed from search to tracking are then processed. A joint algorithm combining deep reinforcement learning and multi-objective evolution is constructed to achieve multi-objective optimization and resource scheduling. This invention uses a two-layer planning strategy to allocate tasks of different natures to two independent planning levels, thereby reducing problem complexity and matching the most suitable optimization algorithm for each type of task.

The invention discloses an infrared polarization image measuring device of a space target and a using method thereof, and belongs to the field of space image measurement. According to the method, the device comprises a satellite model, a guide rail, a translation platform, an electric rotary table, a wide-spectrum infrared polarization sensor and a light source, the wide-spectrum infrared polarization sensor is arranged at the tail end of the guide rail, and the wide-spectrum infrared polarization sensor is used for shooting infrared polarization images of the satellite model under different conditions; the satellite model is arranged on the electric turntable, and the electric turntable is used for adjusting the rotation angle of the satellite model according to a preset direction instruction; the electric rotary table is arranged on the translation platform, and the translation platform is used for performing displacement on the guide rail according to a preset displacement instruction so as to adjust the distance between the satellite model and the wide-spectrum infrared polarization sensor; the light source is used for adjusting illumination conditions of the satellite model. According to the invention, infrared polarization images of various space targets under different conditions can be obtained.