178 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.

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.

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.

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.

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.

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.

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.

The invention belongs to the technical field of spacecraft orbit intelligent control, and discloses a satellite intelligent orbital transfer decision-making system and method, and the system comprises a sensing layer, a service layer, a decision-making layer, and an execution layer. Multiple traditional orbital transfer algorithms are packaged into a standardized MCP service, collision early warning service, situation awareness service and satellite approaching monitoring service are combined, large model reasoning decision is utilized, a LangChain framework is adopted to realize multi-service collaborative calling, and an optimal avoidance strategy can be autonomously generated when a satellite approaches a target satellite in combination with MCP control optimization. According to the invention, the collision with other space objects is avoided while the target satellite is effectively avoided, and the fuel consumption is minimized. According to the invention, the autonomous survival ability and task execution efficiency of the satellite in a complex space environment are significantly improved.

Software-defined space domain awareness systems, comprising a network of a plurality of sensor nodes operating in orbit, each node comprising a hosted payload configured to operate as a network participant in a multi-service SDA network. The hosted payload having a space domain awareness sensor, a processing unit configured to execute a software stack, and a standardized hardware and data interface for integration with satellite, planetary lander, planetary rover platforms or ground / planetary observatories (i.e., earth, moon or another planet). The software is configured to implement SDA algorithms including object detection, object identification and object characterization, autonomously execute tasking decisions using onboard data and shared information from other sensor nodes, synchronize and distribute tracking data via interoperable protocols across the network, and perform real-time propagation of object states and associated uncertainties. The network thus provides decentralized dynamic participation and the sensor nodes providing observation data and receiving tasking directives by the network.

The application discloses a three-dimensional space object semantic segmentation method and device based on a Gaussian splatting method. The method comprises the following steps: processing an RGB image set by using colmap software to obtain camera internal and external parameters and a sparse point cloud set describing a space of the RGB image set; inputting the camera internal and external parameters and the sparse point cloud set into an improved Gaussian splatting model to obtain 3D Gaussian points corresponding to each sparse point cloud in the sparse point cloud set and store the 3D Gaussian points, project the 3D Gaussian points to a 2D plane, and render pixel color and segmentation attributes by integration to obtain a preliminary RGB image and a preliminary segmentation image; and after iterative optimization of the model, the final RGB image and the final segmentation image corresponding to the camera internal and external parameters can be obtained according to the camera internal and external parameters. The application realizes mapping from 2D segmentation to 3D segmentation and is simple to deploy.

The invention relates to a satellite system (100) for monitoring and detecting space objects (102) in the area of space close to a celestial body, in particular for monitoring and detecting space debris, preferably for determining at least one object property of the space objects (102), comprising satellites (108, 110, 112, 114, 160) located on at least one first main orbit (104). Each of the satellites (108, 110, 112, 114, 160) has an observation device (164) which is mounted and designed so as to generate images of space objects (102) within an observation field (108b, 110b, 112b, 114b), and the at least one first main orbit (104) has an orbit height (178, 182) between 200 km and 800 km such that space objects (102) to be observed are preferably located at the same orbit height or higher orbit heights (178, 182) in order to align the observation field (108b, 110b, 112b, 114b) away from the celestial body (106).

Various examples are provided related to a space-based imaging approach for characterizing objects in space Earth or other planetary body. In one example, a method for characterizing objects in space includes illuminating an object in space about Earth or other planetary body with a narrow band, continuous wave (CW) radio beam transmitted by a transmitting telescope; receiving return signals from the object by receiving telescopes in an array, at least one receiving telescope in orbit; and generating a high resolution image of the object from the received return signals utilizing a near-field correction. In another example, a space-based imaging system includes an array of telescopes including a transmitting telescope that can illuminate an object in space; a plurality of receiving telescopes that receive return signals reflected by the object; and processing circuitry that generates a high resolution image of the object from the received return signals.

The present application belongs to the technical field of micro-mechanical gyroscopes, and discloses a position correction method for a gyroscope space counterpart, comprising the following steps: step 1: specific matching of the position of the gyroscope and the gyroscope space counterpart, so that the gyroscope space counterpart and the gyroscope can move synchronously; step 2: correction according to the azimuth distance error of the gyroscope and the gyroscope space counterpart; and step 3: automatic resetting of the position of the gyroscope space counterpart. The present application realizes the correction and automatic resetting of the position of the gyroscope space counterpart, and solves the azimuth error between the gyroscope and the gyroscope space counterpart due to the existence of the boundary and the error caused by the existence of the gyroscope zero drift problem.

The invention discloses a space target area-to-mass ratio estimation method and system based on historical TLE data, and the method comprises the steps: obtaining the historical TLE data of a space target, and screening a segment of TLE data with the longest duration and the semi-major axis decreasing with time; for TLE data in a selected time period, extrapolating the TLE data into ephemeris for precise orbit determination, and synchronously solving an atmospheric resistance coefficient; inversely calculating a satellite surface-mass ratio according to the atmospheric resistance coefficient; and processing the satellite surface-to-mass ratio, and outputting the processed satellite surface-to-mass ratio. According to the method, the surface-to-mass ratio can be reversely deduced without target matching by screening effective data segments of semi-major axis decline and combining precise orbit determination and atmospheric resistance coefficient calculation by utilizing the disclosed historical TLE data, the problem that the surface-to-mass ratio of a non-cooperative target is difficult to obtain is solved, the feasibility of obtaining the surface-to-mass ratio is improved, and the application range of space target monitoring is expanded.

The invention discloses a constellation satellite collision analysis method based on a space debris environment topology network model, and relates to the field of aerospace. The method comprises the following steps: carrying out volume element subdivision on a space target to obtain a plurality of space object group nodes; based on the migration direction of the space target group, the connection relation of the multiple space object group nodes is analyzed and processed, a topological structure is constructed, and a topological network is obtained; carrying out modeling processing on the topology network based on the space debris influence factors by adopting a fluid mechanics method to obtain a space debris environment topology network model; analyzing and solving the space debris environment topology network model by adopting an adjacent matrix to obtain an evolution prediction result of the space debris environment; and performing collision analysis on the constellation satellites according to the evolution prediction result by adopting a collision probability algorithm to obtain a collision analysis result. The invention aims to quickly realize fragment evolution so as to carry out collision analysis of constellation satellites.

The invention discloses an image-based space target physical parameter identification method. The method comprises the following steps: acquiring multiple frames of continuous images in a process of capturing a space target by a service satellite by using a camera; the method comprises the following steps: converting an image into a grey-scale map, identifying an identification point preset on a service satellite in the image, performing ellipse fitting on a closed contour of the image to obtain coordinates of the identification point to pre-generate a multi-angle rendering image set, establishing a mapping relation library of 2D pixel coordinates of the identification point and known 3D coordinates, and resolving pose information of the service satellite; estimating a camera pose and a space target pose; and calculating to obtain the position of the mass center of a combination body formed after the service satellite captures the space target. According to the embodiment of the invention, the method achieves the high-precision calculation of the position of the center of mass of the combined body, obtains the initial value of a physical parameter which can be directly applied to the subsequent dynamic identification, avoids the dependence of contact excitation on fuel and structure safety, enables the identification process to be higher in safety and task sustainability, and improves the recognition efficiency. And the efficiency and the reliability of parameter identification are obviously improved.

The application discloses a ground-based space target monitoring radar atmospheric refraction error correction method. The ground-based space target monitoring radar atmospheric refraction error correction method comprises the following steps: based on the vertical distribution of atmospheric refraction index and the radar elevation angle measurement value, the signal propagation path is accurately recursively calculated by using the refraction theorem and geometric relationship, the corresponding elevation angle, geocentric angle and target apparent distance of different heights are calculated, and a one-to-one corresponding relationship between the apparent distance and the distance, the elevation angle measurement error is established; then, according to the radar distance measurement value, the radar distance and the elevation angle measurement error are calculated by interpolation, and finally, the distance and the elevation angle measurement error caused by the atmospheric refraction of the space target monitoring radar are corrected. The ground-based space target monitoring radar atmospheric refraction error correction method has higher error calculation precision under the condition of given layer interval, has more stable error correction performance, and can more accurately correct the atmospheric refraction error of the space target monitoring radar.

Embodiments can relate to a system for efficiently and dynamically classifying an object of an input image. The system can include an input module for receiving an image of an area of interest captured by an image capture device. The system can include a memory including a synthetic dataset composed of templates, wherein at least one template can be constructed of a statistical mean of shapes. The system can include a processor having a detection module and a classifier module. The detection module can be configured to scan an image to identify a streak pattern. The classifier module can be configured to compare a streak pattern to classify a streak pattern as being representative of a resident space object or representative of a star. The system can include a user interface configured to generate an output identifying a streak pattern as a resident space object or a star.