586results 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.

There is provided a technique for implementing instantly responsive communication flexibly by setting communication occasions in an on-demand manner that are not included in a communication plan scheduled in advance for inter-satellite optical communication. One aspect of the present disclosure relates to a satellite including an optical signal obtainer that captures an optical beacon transmitted from a relay satellite in response to a communication request received from an earth station, an image processor that retrieves a bright spot in a captured image frame, an optical beacon detector that detects the optical beacon based on a flickering state of the retrieved bright spot, and an optical communicator that establishes inter-satellite optical communication with the relay satellite based on the detected optical beacon.

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.

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.

Provided is a method for determining a collision candidate object for a tracking target object. The method comprises obtaining position-related information for a tracking target object at a target time point, determining a first collision candidate object group based on position-related information on each object at a first time point prior to the target time point and position-related information on the tracking target object at the target time point, determining a second collision candidate object group based on position-related information on each of a plurality of objects at a second time point prior to the first time point and position-related information on the tracking target object at the target time point, and determining at least one object included in both the first collision candidate object group and the second collision candidate object group as a collision candidate object for the tracking target object at the target time point.

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.

To estimate in real time the positions of obstacles existing in the space between a satellite and a ground station using at least one of the satellite and the ground station.SOLUTION: An apparatus searches for an obstacle O between a satellite and the ground in a satellite communication system consisting of the at least one satellite S1 orbiting in orbit and a plurality of ground stations. The apparatus includes a wireless communication unit 102 that, in response to at least one of the satellite or the ground stations transmits a search radio wave 110, receives a reflected wave R10 of the search radio wave, and a processing unit 103 that controls the wireless communication unit and estimates the position of the obstacle based on information on the reflected wave.SELECTED DRAWING: Figure 1

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.

The invention provides a lightweight spacecraft minimum safety system and an implementation method, aiming at reliable operation of a spacecraft in orbit, through configuration optimization of the minimum safety system, orderly power-up, cold and hot start and control time sequence configuration design are carried out on each component unit, and the reliability of the spacecraft is improved. The system configuration and construction method suitable for reliable operation of the lightweight spacecraft is provided, safe starting control logic and safe mode switching control logic of the spacecraft are achieved, communication of spaceflight energy flow, control flow and information flow can be ensured, the spacecraft operates orderly based on a minimum safety system, and the reliability of the spacecraft is improved. And effective support is provided for autonomous, safe and stable operation of spacecraft faults and ground emergency rescue. Through the configuration and construction method for the minimum safety system of the lightweight spacecraft, the reliability and safety of on-orbit autonomous execution of the lightweight spacecraft can be improved, and the influence of on-orbit faults on the safety of the spacecraft is reduced.

A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

To secure a communication environment between a watching satellite and a ground facility in a group of earth orbiting satellites, and to enable information transfer between a user satellite and the ground facility.SOLUTION: A communication satellite 401 is used for a satellite watching system in which a watching satellite and a watching center perform information transfer through a group of communication satellites. The communication satellite 401 includes a first communication device 41 to perform communication with a ground facility and three second communication devices 42 to perform communication among infrastructure satellites. The communication satellite 401 performs communication with a communication satellite flying on the same orbital plane, the watching satellite, or a user satellite simultaneously.SELECTED DRAWING: Figure 15

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.

An object is to more accurately assist avoidance of a collision between space objects such as satellites or space debris in outer space. A recorder processing unit (110) acquires flight forecast information (401) indicating a flight forecast of each of a plurality of space objects (60) from a management business device (40) used by a management business operator that manages the plurality of space objects (60). Based on the acquired flight forecast information (401), the recorder processing unit (110) sets a forecast epoch of an orbit of each of the plurality of space objects (60), a forecast orbital element that identifies the orbit, and a forecast error that is forecast for the orbit, as orbit forecast information (51). The recorder processing unit (110) stores a space information recorder (50) including the orbit forecast information (51) in a storage unit (140).

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.

A display system can be configured to identify a space object and an object alert associated with a change in one or more movement parameters of the space object. The system can generate data configured to display a display region and an object alert indicator within the display region. The system can display the object alert indicator at a location within the display region and display, within a second display region, a listing of a plurality of alerts comprising the object alert. The system can receive a user selection of an alert from the plurality of alerts configured to be displayed in the second display region and automatically generate updated data configured to display an updated display region based on the user selection of the alert. The updated display region can include a panned, rotated, and / or zoomed perspective of the display region.

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.

To continuously provide service while avoiding collision with a space object, by control of orbits of satellite groups and control of passage timing.SOLUTION: A megaconstellation business device is a business device for managing 100 or more satellite constellations. The satellite constellation provides service by coordination between satellite groups. The megaconstellation business device includes a satellite constellation formation part 11 for forming a satellite constellation having a plurality of orbital planes in which a plurality of satellites fly at the same nominal orbital altitude on the respective orbital planes. The megaconstellation business device includes a satellite constellation formation part 11 for continuously providing service while avoiding collision, by control of orbits of satellite groups and control of passage timing, after having predicted possibility of collision with a space object falling down in an orbit, a launching rocket, a satellite transiting in the orbit, or debris.SELECTED DRAWING: Figure 28

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.