117 results about "Space object" patented technology

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 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 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.

The application belongs to the technical field of soft robots, and discloses a soft robot for growing to grab objects in a limited space based on a nested structure. The soft robot comprises a first cylinder film, a second cylinder film, an inflation mechanism, a feeding mechanism and a recycling mechanism. The first cylinder film and the second cylinder film are hollow cylinders. The second cylinder film is arranged in the hollow cavity of the first cylinder film and attached to the inner wall of the first cylinder film. The hollow cavity of the second cylinder film is used for covering and taking back the objects to be grabbed. The first cylinder film and the second cylinder film have the same structure. The cylinder walls of the two comprise an inner film and an outer film. A sealed cavity is formed between the inner film and the outer film for inflation. The outer film of the first cylinder film and one end of the inner film of the second cylinder film are fixed. The inner film of the first cylinder film and the outer film of the second cylinder film are connected to the feeding mechanism. The application solves the problem of grabbing objects in a limited space.

Method for tracklet association and orbit parameter estimation of space object includes: propagating orbit to observation epoch, calculating average NIS of the tracklet, and determining whether the tracklet is abnormal according to the average NIS. If the tracklet is normal, the tracklet is directly associated with an object in cataloging database, no maneuver occurs, filtering method is used to update tracklet, and the cataloging database is updated. If the tracklet is abnormal, maneuver association and maneuver parameter joint estimation are triggered. Joint estimation method takes maneuver time and maneuver vector as optimized variables, calculates the average NIS, solves optimization problem by minimizing the average NIS to obtain optimal loss function and optimal maneuver parameters, sets a loss function threshold and maneuver parameter range to determine association, performs iteration for maneuver association until all tracklets are processed, and then obtains tracklet association and maneuver parameters.

The invention provides a gaze interaction system based on gravity vector constraint and spatial topology association, and the system comprises a gaze collection module which is used for collecting user gaze information and generating an original gaze direction vector; the attitude correction module is used for acquiring a gravity vector and constructing an attitude correction operator based on the gravity vector; the space object index module is used for maintaining a space object library; the collision judging and locking module is used for constructing a gazing ray based on the gazing direction vector after gravity alignment; and the protocol communication module is used for distributing a control instruction to a target space object according to a standardized interaction protocol and receiving an execution receipt. In different indoor and outdoor space environments, a unified space coordinate expression and object addressing mechanism can be constructed through multi-source positioning / sensing information; and space object broadcasting, gaze vector stream transmission, interaction locking receipt and instruction distribution are completed through a standardized protocol, and finally closed-loop interaction of WYSIWYG control of a physical entity is realized.

The application belongs to the field of orbit estimation, and relates to a method for robust orbit estimation of space targets under complex observation environment. The application reconfigures the traditional nonlinear observation equation into the cross product form of the line-of-sight vector, realizes the linearization of the measurement model, and makes the orbit estimation problem effectively solved by minimizing the cross product residual. An optimization strategy of minimizing the sum of absolute values of residuals is adopted, a relaxation variable is introduced to convert the orbit estimation problem into a typical linear programming problem. By solving the linear programming problem, the bias solution of the initial orbit state of the space target is obtained, the abnormal data is automatically rejected, and the influence of the abnormal observation data on the orbit estimation result is greatly inhibited. Compared with the traditional least square (LS) method, the application can provide more accurate, stable and robust orbit estimation results when dealing with large initial errors and abnormal data, has stronger adaptability, and is especially suitable for orbit estimation under complex space environment.

The utility model discloses a three-dimensional light processing machine formed by an optical three-dimensional space converter, a three-dimensional light-emitting and light-sensing assembly comprises a light source and light-sensing sheet assembly, and the light source and light-sensing sheet assembly photographs and records a three-dimensional real image of the three-dimensional space converter to obtain two angle coordinates and one object distance coordinate of a three-dimensional space object; during shooting, the light source is used for sending light with the object distance range and shape corresponding to the object needing to be machined, the light sent during shooting is focused to the shot object or the position of each object distance of the object needing to be machined, and three-dimensional light machining of each depth can be achieved.

The invention discloses a three-dimensional scene object identification method based on display precision, and the method comprises the following steps: obtaining a viewpoint parameter of a current three-dimensional scene, and determining a display precision state of current three-dimensional space data based on the viewpoint parameter and a preset precision grading strategy; calculating a model precision deviation parameter for quantifying the geometric simplification degree of the current model according to the display precision state; based on the model precision deviation parameter, dynamically determining a space determination parameter for three-dimensional space object identification; responding to a user interaction operation, obtaining a corresponding screen coordinate and mapping the screen coordinate to the three-dimensional projection space; taking the mapped projection position as a center, constructing an effective judgment area according to the dynamic space judgment parameters, judging the three-dimensional space object in the effective judgment area, and determining a target object; based on the identification information of the target object, triggering and executing an interaction processing operation associated with the target object; the method has stability and practicability in a complex large-scale scene.

A system includes a plurality of satellites in orbit 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 receive image data from sensors in the imaging device, to increase a positional detection accuracy of the celestial image features by defocusing imaging optics of the imaging device, to capture image data in a volume of the sky as the FOV of the imaging device on each satellite moves in an orbital plane, and generate by a centralized computer at least 1,000 celestial image features using the image data transmitted from each of the satellites.