437results about "Cosmonautic vehicle tracking" patented technology

The invention provides an aircraft attitude tracking control method, system and computer equipment, which belongs to the field of aircraft attitude control, comprising: obtaining aircraft operating parameters and establishing a kinematic model of the attitude tracking error of the aircraft. A specified time performance constraint function and attitude error boundary based on the hyperbolic cosecant composite function are then constructed. A constrained attitude error conversion function and its inverse function are utilized to obtain an unconstrained attitude tracking conversion error. Virtual control instructions are solved in kinematics using a sigmoid tracking differentiator to obtain a numerical derivative. The control moment in the dynamics is solved and the complete form of the attitude tracking algorithm is given for the aircraft attitude tracking system. This method provides a computationally efficient means of controlling aircraft to ensure that error convergence is achieved within a preset time.

The invention discloses a service spacecraft multi-orbit maneuvering strategy approaching observation method based on J2 perturbation compensation, solves the problem of how to quickly improve orbit maneuvering accuracy, and belongs to the field of service spacecraft multi-orbit maneuvering strategy approaching observation. Comprising the following steps: constructing a motion equation under J2 item perturbation compensation under a target orbit coordinate system; constructing a service spacecraft multi-orbit maneuvering strategy model through the relative motion propagation relational expression and the motion equation; inputting the termination moment position conforming to the termination moment distance constraint into the model to output a single speed increment, and reserving the single speed increment conforming to the termination moment illumination angle constraint and the single speed increment constraint at the same time to obtain a speed increment solution set; constructing a circular region which takes the space target as a center and has a radius meeting a termination moment distance constraint; when the service spacecraft arrives at the circular area at a specified moment, marking the task successfully, and obtaining a service spacecraft multi-orbit maneuvering strategy for approaching observation; according to the invention, accurate and rapid track maneuvering is realized.

A method of generating a simulated image for training a model to detect resident space objects (RSOs), a method of training the model, and a method of detecting RSOs are provided. The method includes generating a foreground of the simulated image including RSOs by calculating coordinates of an imaging satellite at a given time, determining an area of interest given a field of view (FOV) of the imaging satellite, and calculating coordinates of all RSOs and saving the coordinates if the RSO is within the area of interest. The method further includes generating a background of the simulated image including stars by querying a star catalogue database for coordinates of all stars that fall inside the FOV, adding noise, and translating RSO and star coordinates to pixel coordinates. The method further includes generating the simulated image by choosing an imaging mode, setting an exposure time, and rendering the simulated image.

Transformer neural network model for predicting trajectories of resident space objects is provided. Unlike recurrent neural networks and their subsets, the transformer model simultaneously ingests the input sequence data and employs a self-attention mechanism, to be trained by parallel processing. The developed model can predict RSOs' future trajectory for an extended time horizon. Both state vectors and Keplerian data sets were used for the training. A hybrid SGP-4 interpolation is deployed to transform unsynchronized publicly available data sets to a synchronized data set that is up-sampled to a consistent time of one minute. The transformer ingests the resulting datasets to forecast a subsequent 10-day trajectory of any RSO according to its previous 10-day history input. Then, the model can employ its own forecasted data as a new input to predict RSOs' trajectories to further extend the prediction time horizon.

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.

The present disclosure relates to a method of generating auxiliary data for controlling a satellite travelling in orbit around Earth, the method comprising: receiving tracking data for the satellite; applying an orbit determination algorithm including: estimating an orbit for the satellite based on the tracking data; and predicting, based on the estimated orbit, future ephemerides data of the satellite; generating auxiliary data comprising predicted future ephemerides data; and transmitting the auxiliary data to the satellite for use in the satellite's attitude and orbit control.

The present disclosure relates to systems, methods, and storage media for controlling and simulating spacecraft maneuvers, where the method comprises requesting, using a pilot vehicle interface, a view of the on-orbit operations, wherein the view comprises at least one object; receiving, from a simulation engine executing on a virtual machine, scenario data describing a status of the on-orbit operations; receiving object information about how the at least one object interacts with the on-orbit operations; integrating the scenario data with the object information to obtain the on-orbit operations; and providing, via the pilot vehicle interface, the view of the on-orbit operations.

A display system can be configured to receive, via a user interface, a first identifier associated with a first space object and determine a first maneuver of the first space object. The first maneuver can include a perturbation of the path of the first space object. Based on the first identifier and the first maneuver, the display system can identify one or more path parameters associated with a path of the first space object and generate a display interface. The display interface can include a longitude-time graph having a longitude axis spanning from a lower-longitude limit to an upper-longitude limit and a time axis spanning from the lower-time limit to the upper-time limit and an indication of the one or more path parameters.

Methods and systems of creating accurate data representations of the positions and other characteristics of target space objects using data from a plurality of space-borne artificial satellites and ground-based sensors. Such methods and systems are deployable either on a single satellite, on a plurality or swarm of satellites, and / or in a ground-based system. Various artificial intelligence and machine learning processes described herein are employed to generate a latent data representation of passively-received broad spectrum multi-modal signal data systematically integrated with advanced multi-sensor data fusion algorithms.

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

An almanac method for autonomous neural network navigation of a spacecraft includes performing steps via a computer onboard the spacecraft for determining a current navigation state of the spacecraft and determining a current target epoch for the spacecraft based on the current navigation state. The method also includes reading neural network model parameters from an almanac for the current target epoch. The almanac contains a plurality of neural network models, with each model being valid for an epoch corresponding to a portion of a trajectory. The method further includes executing the neural network model corresponding to the current target epoch to provide one or more thrust commands for the spacecraft.

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.

Systems and methods of the present disclosure enable simulation of imaging of resident space objects (RSOs) by one or more space-based image sensors. The simulation includes obtaining a satellite constellation configuration having satellite configuration parameters for at least one satellite in a constellation of satellites. The simulation also includes obtaining an RSO configuration having RSO configuration parameters RSOs. The simulation may use the satellite and RSO configuration parameters to simulate constellation ephemeris data for each of the satellites and RSOs. Based on the position of each RSO and satellite, detectability of each RSO by each satellite is simulated based on a photometry simulation using the satellite configuration parameters, including sensor characteristics of a simulated sensor. Imagery may also be simulated based on an image generation model, the sensor configuration, the photometry simulation and at least one background model.

For maneuvering a spacecraft, a method calculates a virtual point that represents a plurality of spacecraft orbiting in a spacecraft formation. The method further iteratively calculates an inner polytope boundary relative to the virtual point for a given spacecraft of the plurality of spacecraft. In response to determining the inner polytope boundary will be breached, the method maneuvers the given spacecraft to within the inner polytope boundary based on a switching condition, a guidance law, and model predictive control to minimize fuel consumption.

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.

Provided is a method, system, and computer program product for determining a degree of impact caused by space debris. A processor may receive data from a data stream of one or more satellites, the data including observational data of one or more objects in orbit. The processor may determine, based on an analysis of the observational data, that the one or more objects are space debris. The processor may identify, based on the analyzed observational data, ownership of the one or more objects that are determined to be space debris. The processor may determine, using one or more smart contracts, a degree of impact caused by the one or more objects that are space debris, where the degree of impact is attributed to an identified owner of the one or more objects.

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.

Described are techniques for determining an impact threat of an orbiting object by a crowdsource satellite network. The techniques include capturing, by a satellite included in a crowdsource satellite network, information associated with an orbiting object detected by the satellite. The techniques further include providing, by the satellite, the information associated with the orbiting object to the crowdsource satellite network. The techniques further include collaborating by the satellite with other satellites in the crowdsource satellite network to track the orbiting object, generate an orbital model of the orbiting object, and to analyze a predicted path of the orbiting object represented by the orbital model to determine an impact threat associated with the predicted path of the orbiting object.

The invention relates to a satellite device (100, 200) for imaging space objects (116, 116'), wherein the satellite device (100, 200) is movable along an orbit (102) with a position-dependent orbit coordinate system (104) which comprises an orbit axis (106), a gravitational axis (108) and a pitch axis (109), the satellite device (100, 200) comprising a telescope device (212) having a field of view (112, 112'), a telescope axis (110, 110', 218) and an imaging telescope sensor (210), which is arranged and designed to generate images (132) of space objects (116, 116') in front of a starry background. and a control device (204), which is designed to control the satellite device (100, 200) in such a way that, during operation as intended, 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) in such a way that continuously lined images (132, 134) of space objects (116, 116') and stars are generated, in order to obtain a plurality of lined images (132, 134) for generating a space object overview.

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.