38results about "Cosmonautic vehicle tracking" patented technology

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

The ever increasing number of orbiting bodies in low Earth orbit has made it infeasible to calculate potential conjunctions between orbiting bodies more than a few days in advance, even with the aid of supercomputers. Disclosed embodiments utilize machine learning to predict potential conjunctions between orbiting bodies faster than state-of-the art systems by orders of magnitude. This enables potential conjunctions to be identified well in advance (e.g., 30 days or more), so that they may be prioritized (e.g., for fine calculations), visualized, and remediated (e.g., via control of the impacted satellites).

The present invention provides an orbit design system for a global carbon inventory satellite, comprising: a long residence unit in the northern hemisphere configured to enable the global carbon inventory satellite operates in a mid-orbit elliptical orbit, and enable the global carbon inventory satellite to be located above the latitude of the human activity intensive region when it operates to its apogee.

An orbital analysis unit (431) of a collision avoidance assist business device identifies a mega-constellation satellite group formed in an orbital altitude which the mega-constellation satellite group is anticipated to pass during a flight of an unsteady-operation space object. An announcement unit (432) of the collision avoidance assist business device announces a danger alarm and orbital information of the unsteady-operation space object, to a mega-constellation business device which manages the mega-constellation satellite group. A collision analysis unit (411) of a satellite mega-constellation business device analyzes collision of the unsteady-operation space object with an individual satellite constituting the mega-constellation satellite group. A countermeasure formulating unit (412) of the satellite constellation business device formulates a collision avoidance countermeasure when collision is predicted.

Systems, methods, and devices in a satellite for on-orbit recovery are described. The device includes a plurality of circuits that are electrically connected to a backplane of the device, and a controller configured to monitor parameters of at least one of the plurality of circuits, and configured to store the parameters that are monitored with respective timestamps and respective orbit locations of the satellite. The controller is further configured to identify an error of a first circuit of the plurality of circuits based on the parameters that are monitored and the respective orbit locations of the satellite.

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.

A display system can be configured to receive, via a user interface, an identifier associated with an orbital object and determine a maneuver of the orbital object. The maneuver can include a perturbation of the path of the orbital object. Based on the identifier, the display system can determine pre-maneuver and post-maneuver orbital parameters associated with the orbital object and generate a display interface. The display interface can include a longitude-time graph having a longitude axis and a time-axis and an indication of the determined orbital parameters. The post-maneuver orbital parameters can be determined based at least in part on the pre-maneuver orbital parameters.

In general, it provides a method for establishing communication and a user interface for doing so. [Solution] In a computer system configured to communicate via an alternative communication network when an individual communication network is unavailable, the alternative communication network test mode is activated in response to the detection of a set of inputs corresponding to a request to activate the alternative communication network test mode via one or more input devices, while the computer system's ability to communicate via the individual communication network is enabled, wherein activating the alternative communication network test mode includes disabling the computer system's ability to communicate via the individual communication network. While activated, a set of user interfaces is displayed via a display generation component.

A display system according to the present invention obtains data indicating an orbit of an artificial satellite and time-series data related to the artificial satellite. The display system performs 3D graphics display of the orbit of the artificial satellite and a graph of the time-series data such that the orbit of the artificial satellite matches the time axis of the graph of the time-series data.

In a transmission terminal (1), a control unit (101) selects number of parallelizations, and a parallelization unit (103) parallelizes data according to the number of parallelizations selected by the control unit (101); and in a reception terminal (2), a demodulation unit (205) and a demapping unit (206) perform processing according to the number of parallelizations.

To enable observation of celestial objects while moving relative to them. [Solution] The observation satellite 200 moves eastward relative to the space object between 10:00 and 18:00 solar time in the target area, changing the direction of its observation device from the anti-Earth direction to the east within a range of 30 to 90 degrees to allow the observation device to observe the space object, and then allows the observation device to observe the space object above the far side of the Earth between 18:00 and 6:00 solar time.

The present disclosure relates to a tunnel-based space debris removal system that captures and compacts orbital debris for safe removal. The system includes a tunnel structure having a curved funnel-shaped portion oriented toward Earth and rotatably mounted on a cylindrical portion via a turntable. Incoming debris is directed through the funnel into a collision box, where an electromagnetic foil slows and confines the particles. A hydraulic compaction mechanism with pneumatically-driven piston arms applies high-pressure force to compress the debris against compression plates, forming dense pellets suitable for storage. A power subsystem, comprising solar panels and integrated energy storage, supplies operating power to all functional units. The system ensures efficient debris capture, controlled compaction, and energy autonomy, providing a reliable method for orbital debris mitigation and enhancing long-term space sustainability.

The present application relates to a kind of reentry atmosphere spacecraft safety landing system, comprising: spacecraft on-board system software is configured to detect the power output of spacecraft flight power system, and when detecting no power output, first signal is continuously sent to landing intelligent system;Landing intelligent system is connected with the spacecraft on-board system software communication, and is configured to perform the following actions: receive first signal and time, when the duration of no power output reaches first duration, enter emergency rescue mode, send rescue information and spacecraft positioning information, and when the duration of no power output reaches second duration, start physical self-help system, second duration is greater than first duration;And ground emergency command control center is configured to perform the following actions: after receiving rescue signal and the positioning information of spacecraft, start unmanned aerial vehicle system to find spacecraft according to positioning information.The safe recovery of spacecraft can be realized by the system.

This invention relates to the field of aerospace telemetry and control and spacecraft flight control technology, specifically disclosing a method, system, device, and storage medium for automatic remote control command issuance for spacecraft. This invention establishes a remote control command library storing telemetry expectation values, configures dynamic control parameters including command mode identifiers and interpretation times for command sequences, sets dual-condition judgment rules before and after command issuance and corresponding control action relationships, and automatically selects blind issuance or non-blind issuance process based on dual criteria during traversal execution based on the command mode identifier. This solves the problems of low efficiency and excessive manpower required for state-aware remote control commands due to reliance on manual command issuance, and improves the automation level and multi-objective parallel processing capability of spacecraft on-orbit management.

The invention relates to a method for monitoring moving space objects, the method being implemented by a monitoring system (100), comprising the following steps: - sliding acquisition of at least one stack (12, 12') of image frames of space along a known trajectory on the celestial sphere, each stack of frames comprising at least three frames, each frame being recorded with an exposure time of less than 1 second, - detection, in the field of view, of a plurality of stars (14, 55), preferably several dozen, - estimation of the coordinates of the detected stars, - identification of the detected stars with a list of reference stars extracted from a stellar catalog, comprising several thousand reference stars, - establishment of a coordinate relation linking the celestial coordinates to the coordinates in the frames of the stars present in the list of reference stars, - detection of at least one moving space object (15,56) in at least one stack and estimation of their dated frame coordinates, - conversion of the dated frame coordinates of each detected moving space object into coordinates on the celestial sphere by the coordinate relation. Figure for abbreviation: [Fig. 1 ],

The invention relates to a satellite apparatus (100, 200) for imaging space objects (116, 116′), wherein the satellite apparatus (100, 200) is movable along an orbit (102) with a position-dependent orbital coordinate system (104), the satellite apparatus (100, 200) being movable along an orbit (102) with a position-dependent orbit coordinate system (104) (110, 110′, 218) and an imaging telescope sensor (210) that is arranged and configured to generate images (132) of space objects (116, 116′) in front of the starry background, and a control device (204) that is adapted to control the satellite apparatus (100, 200) in such a way that, in the intended operation, a predetermined pitch angle (114) is set between the telescope axis (110, 110′, 218) and the orbit axis (106), and to control the telescope sensor (210) such that streak images (132, 134) of space objects (116, 116′) and stars are continuously generated in order to obtain a plurality of streak images (132, 134) for generating a space object position map.

The current disclosure provides systems and methods of directly measuring angular velocity and angular acceleration of space objects and using the measured angular velocity and angular acceleration as inputs into new and unique algorithms for initial orbit determination. Sensors measuring locations and times of light events may be used to generate a virtual rate track image for identification of space objects. Right ascension and declination of the space object events versus time may be fit to polynomials or splines to determine associated angle, angular rate, and angular acceleration of the space objects. New and unique initial orbit algorithms may then be applied to estimate orbital elements of the space objects.

Method for managing a satellite receiving CDM messages relating to a secondary object (2) that could collide with the satellite at a TCA date. At each orbit, an autonomous orbit control module establishes a safe current plan on board, defining station-keeping maneuvers (14, 15). A preliminary filtering of the received CDMs is performed on board based on geometric and / or temporal criteria. For each selected risky CDM, a collision risk level is estimated on board based on onboard navigation data propagated at the TCA date of said risky CDM. In the event of a confirmed risk, an ACA collision risk management module develops a new plan on board by removing or replacing at least one maneuver from the safe current plan with a maneuver (16, 17) that allows both station-keeping within a mission window (301-302) and avoidance. Figure for the abstract: Fig. 4

The application relates to a satellite autonomous imaging planning method and system, and relates to the aerospace technical field, and solves the problems of insufficient overtop prediction accuracy, low autonomy and large satellite resource consumption in the prior art method based on high-precision orbit low orbit and accurate search overtop time. Based on satellite orbit information obtained through orbit recursion and longitude and latitude data of a ground target point, an included angle between a flight direction and a satellite-target point connecting vector is calculated, orbit recursion step length is dynamically adjusted according to the included angle value, and orbit data of the satellite overtop time is determined; according to the orbit data of the overtop time, it is judged whether the overtop orbit is located in the side swing shooting capability range of the satellite, if the requirement is not met, the orbit recursion is returned and continued, and if the requirement is met, the best imaging time and the satellite attitude are calculated respectively; the best imaging time, the satellite attitude and related orbit information are returned to a ground central computer, and are used for task storage and scheduling.

The objective is to observe celestial objects under optimal conditions using observation satellites. [Solution] The observation satellite observes artificial satellites or space objects such as debris or other spacecraft orbiting the Earth near geostationary orbit. The observation satellite is equipped with observation devices and a propulsion system. By controlling the propulsion system to decelerate the observation satellite, its orbital altitude is lowered. As the orbital altitude decreases, the observation satellite's orbital speed relative to the Earth's rotation speed increases, causing the observation satellite to move eastward relative to the space object. By controlling the propulsion system to increase the observation satellite's speed, its orbital altitude is raised. As the orbital altitude increases, the observation satellite's orbital speed relative to the Earth's rotation speed decreases, causing the observation satellite to move westward relative to the space object. The observation devices are operated at arbitrary timings during eastward and westward movement, and the average orbital period is adjusted.

The invention relates to a device (1) for monitoring objects in space orbit around the Earth, the device (1) comprising a frame (2), a plate (3), at least three optical monitoring modules (4), and a power supply and control unit (5) housed at least partially inside the frame (2). The plate (3) is mounted on the frame (2), and each optical monitoring module (4) is mounted on the plate (3) and comprises a rotary turret (400), an image sensor (408) mounted on the rotary turret (400) and a passive optical system (410) mounted on the inlet of the image sensor (408). The rotary turret (400) is configured to pivot over more than 360° about a first axis perpendicular to the plane in which the plate (3) extends and to pivot over 90° about a second axis perpendicular to the first axis and parallel to the plane in which the plate (3) extends.

The invention relates to a method for monitoring mobile space objects, the method being implemented by a monitoring system (100), the method comprising the following steps: - slidingly acquiring at least one stack (12, 12') of image frames of space according to a known trajectory on the celestial vault, each stack of frames comprising at least three frames, each frame being recorded with an exposure time of less than 1 second; - detecting, in the field of view, a plurality of stars (14, 55), preferably several tens, in the at least one stack; - estimating the coordinates of the detected stars; - identifying the detected stars with a list of reference stars extracted from a stellar catalog, the stellar catalog comprising several thousand reference stars; - establishing a coordinate relationship linking the celestial coordinates to the coordinates in the frames of the stars present in the list of reference stars; - detecting at least one mobile space object (15, 56) in at least one stack and estimating the dated frame coordinates of the at least one mobile space object; - converting the dated frame coordinates of each detected mobile space object into coordinates on the celestial vault by the coordinate relationship.

The present application relates to the technical field of space target detection, and discloses a star cluster cooperative space target search and orbit determination method, which comprises the following steps: a ground computing center generates prior guidance data of a space target and injects the star cluster; a wide field satellite node performs sky domain search according to the prior guidance data, extracts a two-dimensional observation error covariance through dimension reduction and shift superposition processing, and sends an inter-satellite data frame containing the covariance and instantaneous pose to a narrow field satellite node; the narrow field satellite node receives the inter-satellite data frame, performs reference alignment and state extrapolation in combination with a prior distance error variance and an earth-centered inertial coordinate system, and generates an extrapolated three-dimensional error ellipsoid; the narrow field satellite node generates a boresight maneuver trajectory according to the error ellipsoid to realize physical locking of the target; and the star cluster performs state convergence based on a cross-line-of-sight network to complete cooperative orbit determination. The present application overcomes the problem of limited single-satellite field of view and lack of depth data, and realizes effective capture and orbit determination of a multi-satellite cooperative space target.

A system and method for detecting space debris which is based on measurements of broadband non-thermal radiation and / or light emitted by either sparks or the expansion of the plasma-fragments cloud generated during high-speed collisions of solid materials. The method is based on the concept that broadband nonthermal radiation and / or light can be used to detect the formation of new debris and for tracking debris clouds. The emission of broadband nonthermal radiation and / or light is based on theoretical and observational evidence that the collision of particles of solid materials with each other transfer enough charge to create electric fields large enough to produce small electric discharges or sparks and that the expansion of the plasma-fragments cloud generated by collisions at orbital velocities produce thermal and non-thermal electromagnetic signals.

An antenna control method and an antenna system are provided. [Solution] The antenna control method includes loading initial transmission and reception direction data, receiving signals toward multiple satellites based on the initial transmission and reception direction data and acquiring multiple signal strength data, constructing a candidate list from the multiple signal strength data using a minimum strength threshold, selecting a satellite with the maximum signal strength data from the candidate list and defining it as the target, acquiring base frequency signal data of the target if the signal strength data of the target exceeds a predetermined strength threshold, substituting the base frequency signal data into a subspace tracking method to acquire principal eigenvector data and principal eigenvalue data, substituting the principal eigenvector data and principal eigenvalue data into the ESPRIT method to acquire the direction of arrival data of the target, and adjusting the beam based on the direction of arrival data to track the target.

An optical ground station for satellite communications comprises a base (12) having a bearing support (14), an intermediate frame (18) mounted on the base, having a circular arc-shaped guide (16) that engages with the bearing support to enable angular motion of the intermediate frame around a first (substantially) horizontal axis (22) corresponding to the axis of a circular arc-shaped guide, a first actuator (24) configured and positioned to rotate the intermediate frame relative to the base around the first axis, an optical communication terminal (30) mounted on the intermediate frame through a rotating bearing (32) that enables angular motion of the optical communication terminal around a second axis (34) perpendicular to the first axis, and a second actuator (33) configured and positioned to rotate the optical communication terminal relative to the intermediate frame around the second axis.

The system according to this embodiment aims to predict the location of space debris, correct the orbit of artificial satellites, and remove the debris. [Solution] The system according to the embodiment comprises an observation unit, a prediction unit, an avoidance unit, and a removal unit. The observation unit collects position data of space debris. The prediction unit analyzes the data collected by the observation unit and predicts the future position of the debris. The avoidance unit corrects the orbit of the satellite based on the prediction data obtained by the prediction unit. The removal unit captures and removes the debris based on the prediction data obtained by the prediction unit.

The objective is to provide flight safety measures that avoid collisions between artificial satellites and space objects under favorable conditions. [Solution] The observation satellite 200 changes its flight speed after it has begun orbiting one side of the Earth 101 (either the near side or the far side) through orbit control by ground equipment. As a result, the orbital altitude of the observation satellite 200 changes from the altitude of geostationary orbit 103. Furthermore, the observation satellite 200 changes its flight speed again before it begins orbiting the other side of the Earth 101 (either the near side or the far side) through orbit control by ground equipment. As a result, the orbital altitude of the observation satellite 200 returns to the altitude of geostationary orbit 103. Through orbital control, the space situational awareness system equipped with the observation device 200 provides a flight safety measure to avoid collisions between artificial satellites flying near geostationary orbit and space objects.