337results about "Cosmonautic vehicle tracking" patented technology

In a space traffic management system (500), space traffic management devices (100) individually mounted in a plurality of mega-constellation business devices and in a debris removal business device (45) are connected to each other via a communication line (200). The debris removal device (45) performs Active Debris Removal (ADR) against debris formed by a satellite managed by a first mega-constellation business operator. The debris removal device (45) acquires real-time high-accuracy orbital information of a satellite group of a second mega-constellation business operator in a timeframe in which a debris removal satellite, during orbital descent, passes through an orbital altitude region where the satellite group of the second mega-constellation flies, the debris removal satellite passing through the satellite group while ensuring flight safety.

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.

A wireless communication system for transmitting data to a ground station includes a plurality of stochastically distributed orbiting satellites equipped with a plurality of antennas that traverse a portion of the Earth's surface divided into zones. The ground station has a unique address that identifies itself and the zone in which it is located. A local area network associated with a ground node includes at least one satellite that stores an identifier of a satellite antenna paired with a ground station antenna to form a wireless link for transmitting the satellite's onboard data to the ground station. Other satellites in the local area network store the address of the ground node and an identifier of an antenna paired with an antenna in another satellite that also stores the address of the ground node. A wide area network includes at least one satellite, each of which stores an identifier of an antenna paired with an antenna of another satellite that stores a ground node zone to form at least one inter-satellite wireless link. If the data-carrying satellite is not within a local area network associated with the destination ground node or the wide area network, the satellite transmits data toward the ground node's zone. [Selection diagram] Figure 5

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 provides a spaceflight signal simulation test method and device, electronic equipment and a storage medium. The spaceflight signal simulation test method comprises the following steps: acquiring flight path information of a spacecraft under a station center spherical coordinate system; the station center spherical coordinate system is a spherical coordinate system taking the measurement and control station as an original point; determining flight path information of the unmanned aerial vehicle under the station center spherical coordinate system according to the projection of the spacecraft in the target projection plane; the target projection surface is a spatial curved surface on a linear observation path of the measurement and control station and the spacecraft; determining a signal compensation parameter between the measurement and control station and the unmanned aerial vehicle based on the flight path information of the spacecraft under the station center spherical coordinate system and the flight path information of the unmanned aerial vehicle under the station center spherical coordinate system; and performing compensation processing on the analog telemetry signal of the unmanned aerial vehicle based on the signal compensation parameter. The flight path of the spacecraft is simulated through the unmanned aerial vehicle, the correctness of the antenna pointing to the spacecraft can be simulated and verified in the process that the antenna of the measurement and control station tracks and points to the unmanned aerial vehicle, and meanwhile the simulation test accuracy is greatly improved.

An electric vertical take-off and landing (eVTOL) aircraft can enhance energy efficiency, safety, and operational range. A deployable wing structure can provide aerodynamic lift during horizontal flight, reducing reliance on energy-intensive propellers. Integrated flexible solar panels capture solar energy, contributing additional power and optimizing energy management. The wing system also includes an emergency descent mode, doubling as a glide-assist device for controlled landings during critical failures. The system offers modular configurations for various missions, ensuring adaptability and improved flight performance. The eVTOL can be implemented with systems and methods for mitigating motion sickness. The systems integrate tactile feedback systems into wearable devices and environmental components. Sensors detect motion and environmental changes, and a computing device can generate corresponding tactile feedback signals. Tactile actuators embedded in the devices or components provide non-visual motion cues, such as pressure, vibration, and haptic feedback, to resolve sensory mismatches between the vestibular and proprioceptive systems.

A satellite constellation (100) includes a plurality of artificial satellites (111 to 116) that number a multiple of 6. Each of the plurality of artificial satellites orbits in an inclined circular orbit a plurality of times a day. Normals to a plurality of orbital planes corresponding to the plurality of artificial satellites are shifted by an equal angle from each other in an azimuth direction. The plurality of orbital planes make up one or more orbital plane sets each consisting of six orbital planes. Timings at which the six artificial satellites orbit on the six orbital planes of each orbital plane set are synchronized with each other.

A satellite constellation forming system (100) forms a satellite constellation (20). The satellite constellation (20) is composed of a satellite group (300). In the satellite constellation (20), the satellite group (300) provides a service cooperatively. The satellite constellation (20) has a plurality of orbital planes in which a plurality of satellites (30) fly at the same orbital altitude in each orbital plane (21). A satellite constellation forming unit (110) forms the satellite constellation (20) in which orbital altitudes of the plurality of orbital planes (21) are mutually different.

The disclosed technology is generally directed to a method for simulating light pollution by a satellite system including at least one satellite. In one example of the technology, the method may include receiving orientation and solar panel parameters associated with the satellite, a position of the Earth with respect to the Sun, importing a database including multiple point of interests (POIs) on the Earth, and determining a surface roughness parameter of the satellite using a Gaussian distribution model. Based on the orientation and solar panel parameters, the position of the Earth, and the surface roughness parameter: simulating the light pollution by the satellite to iteratively determine the light pollution at the POIs. The method may include storing the light pollution determined at the POIs in a buffer and dynamically rendering a user interface to display a visualization representing the light pollution by the satellite at the POIs.

The application discloses a spin-nutation collaborative inhibition method and system for a space tumbling target, and belongs to the technical field of aerospace. The method comprises the following steps: acquiring pose data of a space robot, and controlling the space robot to approach the space tumbling target according to the acquired pose data of the space robot; after the space robot approaches the space tumbling target, the space robot measures the space tumbling target, and acquires real-time state data of the space tumbling target by measuring the space tumbling target; a target stress position prediction model of spin-nutation collaborative inhibition is used to simulate and predict based on the acquired real-time state data of the space tumbling target, and a despinning condition required by a despinning tool in the space robot is determined; the space robot adjusts the pose according to the despinning condition, and controls the despinning tool to contact the space tumbling target, and implements contact despinning. The application can efficiently inhibit the nutation of the target in the initial stage of the despinning task, and effectively reduces the difficulty of the subsequent despinning task.

Disclosed herein is a method for remote monitoring, the method including determining, from event signals obtained from an event-based vision sensor, a rate at which those event signals are generated in response to changes associated with a particular object, and optionally determining a brightness of the particular object from exposure measurements associated with the event signals.

In a space traffic management system (500), space traffic management devices (100) individually mounted in a plurality of mega-constellation business devices and in a debris removal business device (45) are connected to each other via a communication line (200). The debris removal device (45) performs Active Debris Removal (ADR) against debris formed by a satellite managed by a first mega-constellation business operator. The debris removal device (45) acquires real-time high-accuracy orbital information of a satellite group of a second mega-constellation business operator in a timeframe in which a debris removal satellite, during orbital descent, passes through an orbital altitude region where the satellite group of the second mega-constellation flies, the debris removal satellite passing through the satellite group while ensuring flight safety.

Methods, systems, and devices for satellite operations are described. Positioning data for the non-geostationary satellites may be received from the non-geostationary satellites via one or more satellites in an orbit higher than the orbit of the non-geostationary satellite. Based on the positioning data, trajectories of the non-geostationary satellites may be calculated. Based on the trajectories calculated for the set of non-geostationary satellites, a distance between the set of non-geostationary satellites may be predicted to fall within a threshold distance, and an alert may be communicated to one or more operators of the set of non-geostationary satellites that a distance between the set of non-geostationary satellites is predicted to fall within the threshold distance.

A satellite tracking system and method, a three-point peaking technique is used to determine the direction of a satellite 50 which includes a signal source. A Kalman filter is used to minimize the effects of noise in the received signal during the three-point peaking operation. This determination may be made at any time. Once the position of a satellite 50 has been determined twice over a time interval, its future position may be estimated by an adaptive continuous step track technique, using a Kalman filter, which assumes that the satellite moves uniformly with time as viewed from the antenna.

The invention discloses a spacecraft real-time tracking situation display method. The method mainly comprises the following steps: analyzing target visibility of equipment; receiving tracking data sent by the processing equipment; coordinate transformation; the tracking situation is displayed in real time; target real-time identification; and warning information. Through the steps, the problems of observation station tracking target visibility analysis, tracking data real-time processing, real-time situation display, real-time target identification, alarm information and the like can be solved, content display is carried out according to personalized requirements of a user, and the tracking and operation situation of a spacecraft is comprehensively and accurately reflected.

The present invention discloses a method and device for jointly planning spacecraft attitude maneuver events and associated events. Among them, the method includes: obtaining element information of multiple attitude maneuver events of the spacecraft, where the element information includes the attitude maneuver type and the first relative moments of multiple first characteristic actions during the attitude maneuver process; obtaining the associated information of the associated events of the spacecraft; determining the attitude maneuver control parameters of the target attitude maneuver event and the attitude prediction data for the target time period according to the absolute time of the reference action, the element information of multiple attitude maneuver events, and the orbit where the spacecraft is located; and planning and executing the associated events according to the attitude maneuver control parameters and the attitude prediction data. The present invention solves the technical problem in the related art that during the space flight control process, personnel at different stages will plan the attitude maneuver events of the spacecraft according to the current state of the spacecraft, resulting in easy conflicts and safety risks.

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.

A system for earth monitoring includes a constellation of satellites (310) and a dispatch computing module (302) located on earth. The dispatch computing module (302) can be configured to implement a satellite management method that receives a post-launch request for a location to be imaged; re-computes an existing schedule of satellites to provide an updated schedule that includes imaging the location; and provides the updated schedule to one or more of the satellites for transmission.

This invention provides a spatial target tracking method based on an optical search component, comprising the following steps: Step 1, rotating the field of view of the optical search component across its entire range to locate the target object; Step 2, transmitting the scene in the field of view in real time from the optical search component, processing the transmitted scene in the field of view, and determining whether the optical search component has tracked the target object; Step 3, establishing a predicted trajectory function for the target object based on its actual motion trajectory to obtain the predicted motion trajectory of the target object; Step 4, rotating the optical search component according to the predicted motion trajectory of the target object to adjust its field of view angle.

To enable high-speed, large-capacity communication of data obtained through space infrastructure.SOLUTION: Each infrastructure satellite 111 includes a two-way communication terminal that realizes reception and transmission by switching between a reception function and a transmission function. The two-way communication terminal of each infrastructure satellite 111 switches between a reception function and a transmission function such that the ratio of the reception operation time during which the reception function operates and the transmission operation time during which the transmission function operates matches the ratio between the amount of mission command data transmitted from a service center 130 and the amount of mission report data sent to the service center 130.SELECTED DRAWING: Figure 10

A display system acquires data indicating an orbit of a satellite and time-series data related to the artificial satellite, and performs a three-dimensional 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.

To provide a monitoring system capable of performing constant global monitoring with a small number of satellites and high in monitoring performance such as spatial resolution and monitoring performance.SOLUTION: A monitoring system 3000 comprises: a plurality of monitor satellites including a first monitoring device directed to an earth surface and a second monitoring device directed to an earth circumference; and a ground facility. Six or more monitor satellites form a satellite constellation of an equator sky satellite group flying over the equator with less than orbit inclination of 10 degrees. The monitoring system 3000 has an elliptic orbit, expands a monitoring range of the second monitoring device to a high latitude side near a remote point, and expands it to a low latitude side near a near point. The monitoring system 3000 can monitor, against a cosmic background, a tangential direction of a north latitude of 20 degrees at an orbit altitude of about 400 km, a tangential direction of a north latitude of 30 degrees at an orbit altitude of about 1,000 km, a tangential direction of a north latitude of 40 degrees at an orbit altitude of about 2,000 km, a tangential direction of a north latitude of 50 degrees at an orbit altitude of about 3,600 km, and a tangential direction of a north latitude of 60 degrees at an orbit altitude of about 12,800 km.SELECTED DRAWING: Figure 44

In a system where multiple satellites autonomously take turns acting as servers, the servers will be rotated according to instructions from a ground station. [Solution] The server, which is a satellite 200 that has obtained server rights, receives a priority notification when a ground station 300 transmits the priority notification. If the server receives the priority notification, it selects the satellite 200 specified in the priority notification as the server for the next time interval. If the server does not receive the priority notification, it selects one of the multiple satellites as the server for the next time interval based on the status information of the server and the status information of each client.

Examples of the present disclosure include a method for approximating a non-carth imaging camera model for a non-earth sensor includes obtaining a physical camera model, receiving a target range value, determining a plurality of space-based coordinates of a plurality of points about a line of sight of the sensor in proximity to a distance corresponding to the received target range value, for each of the plurality of locations, determining line and sample coordinates on an image thereof via the physical camera model based on the space-based coordinates of the plurality of points, and based on the determined line and sample coordinates for each of the plurality of points, fitting an approximate camera model thereto.

In some implementations, a device may obtain historical orbital data indicative of orbital movement of a set of satellites over a period of time, the set of satellites comprising at least a subset of satellites of the satellite constellation. The device may, for each satellite in the set of satellites, estimate a set of orbital parameter values by fitting an orbital model to the historical data of the respective satellite, wherein at least one orbital parameter value of the set of orbital values is common across a group of satellites within the set of satellites. The device may send assistance data to at least one mobile device, the assistance data indicative of the respective set of orbital parameter values for all satellites of the set of satellites.

Angular velocity control device for a spacecraft and corresponding spacecraft. The invention relates to a device (1) for controlling the angular velocity of a decommissioned spacecraft, comprising: - a stator (3) and a rotor (4) movable about an axis (A21) of rotation relative to the stator. The stator (3) comprises an electrically conductive and non-ferromagnetic body (6), while the rotor (4) comprises a magnetized system (7) configured to induce, in the stator (3), braking eddy currents of a relative motion of the rotor (4) with respect to the stator (3); - a levitation magnet (11) intended to cooperate with a magnetic field generated by an external source to induce magnetic levitation of the rotor (4) with respect to the stator (3). The device (1) is made of one or more non-ferromagnetic materials in a zone (11ZI) influenced by the magnetic field generated by the levitation magnet. SAMPLE FIGURE: [Fig.4]

To provide a data relay satellite that enables information transmission without communication interruption, with fewer communication satellites.SOLUTION: A flying-object handling system 700 causes a first data relay satellite 211 and a second data relay satellite 212 to cooperate with each other to transmit monitoring information to handling devices 310, 320. Each of the first data relay satellite 211 and the second data relay satellite 212 includes an optical communication device that changes a pointing direction by ±40 degrees around a +X axis with respect to a +Z axis and by ±40 degrees around a +Y axis facing a plus direction in right-hand orthogonal coordinates with respect to the +Z axis, wherein a +X axis direction facing the plus direction in the right-hand orthogonal coordinates is a satellite traveling direction +X of the data relay satellite and a +Z axis direction facing the plus direction in the right-hand orthogonal coordinates is a geocentric direction +Z of the satellite.SELECTED DRAWING: Figure 18

To enhance versatility in analysis of acceleration and deceleration of a space object.SOLUTION: The acceleration / deceleration analyzing device 700 is included in a space situation monitoring business device that monitors a space object with a monitoring device, analyzes the orbit of the space object 60 to determine whether the space object 60 is accelerating or decelerating, and, when the monitoring device finds a space object A whose orbit information is unknown and is composed of elements of the orbit 6 based on the original t0 and Kepler's law, sets the following parameters as a parameter set 0 indicating an estimated orbit information initial value that is an estimated value of the orbit information of the space object A in the original t0: Monitoring information of a monitoring device about a space object A is acquired three times or more to derive orbit 6 elements in an original period t0. The acceleration and deceleration analyzer 700 also derives the acceleration of the space object A in the out-of-plane direction at the ascending node and the acceleration of the space object A in the out-of-plane direction at the descending node from the difference between the orbit inclination derived from the monitoring information about the space object A and the orbit inclination of the parameter set 0.SELECTED DRAWING: Figure 1