A constellation of many satellites provide communication between devices such as user terminals (UTs) and ground stations that are connected to other networks, such as the Internet. A constellation management system (CMS) facilitates management and operation of the satellites in the constellation and facilitates information exchange with other authorized systems to provide for situationally aware operation. The CMS may ingest data such as satellite telemetry, space weather data, object ephemeris data about other orbital objects, and so forth. The CMS uses the ingested data to automatically operate satellites to perform routine activities such as station keeping maneuvers, maintenance activities, interference mitigation, and so forth. Confirmation from a human operator may be obtained before performing some activities. Activities may be planned and coordinated to minimize resource consumption for the individual satellite as well as the constellation. Output, such as ephemeris data, may be provided to other parties as well.

An artificial satellite comprises a satellite structure, an onboard control system including an onboard controller, and a memory system. The memory system is physically coupled to the satellite structure and independently powerable with respect to the onboard controller. The memory system is also arranged to communicatively couple with the onboard controller, and to store data which specifies one or more launch-specific parameters for configuring at least one of the satellite components. The onboard control system is adapted to operate in a transfer phase in response to the satellite separating from a payload dispenser, and to autonomously control, while operating in the transfer phase, one or more aspects of at least one satellite component at least partly based on the data, and particularly the one or more launch-specific parameters specified by or derived from the data.

Provided are a method for maintaining Walker constellation formation and a terminal device. The method comprises: determining a first offset amount of each satellite within a simulation time period according to parameters of a Walker constellation; performing first offset on each satellite according to the first offset amount to obtain a Walker constellation after the first offset; determining a second offset amount of each satellite within the simulation time period according to parameters of the Walker constellation after the first offset; and superimposing the first offset amount and the second offset amount, and performing second offset on each satellite so as to maintain the formation of the Walker constellation.

The present invention discloses a method for autonomous mission planning of Carbon Satellite, which triggers autonomous mission planning for the satellite when it detects the satellite switching from a shadow area to a light area, comprising: determining planning time sequence, wherein the planning time sequence comprise several time nodes; and then, for each time node, carrying out a prediction of the ground attributes of the sub-satellite point, and setting observation arc segment according to the prediction result; and finally, determining the load power-on-off time sequence according to the observation arc segment.

An exemplary system and method are disclosed for a standalone vision-based system for autonomous online navigation, e.g., around an unknown target small body. The exemplary system (also referred to as AstroSLAM) is predicated on the formulation of the SLAM problem as an incrementally growing factor graph. Using the GTSAM library and the iSAM2 engine, the exemplary system and method combine sensor fusion with the prior orbital motion to provide navigation and parameter estimation that improves the performance over a baseline SLAM implementation. The exemplary system and method can incorporate orbital motion constraints into the factor graph by devising a relative dynamics factor that can link the relative pose of the spacecraft to the problem of predicting trajectories stemming from the motion of the spacecraft in the vicinity of the small body.

Systems and methods of collision avoidance between space objects may include: (a) receiving state data corresponding to a plurality of space objects; (b) identifying, based at least in part on the state data, a potential future collision between a first space object of said plurality of space objects and a second space object of said plurality of space objects; (c) transmitting a notification of the potential future collision to a first operator of the first space object and a second operator of the second space object; (d) establishing a communication pathway between the first operator and the second operator; and (e) transmitting, via the communication pathway, a message, automatically generated by the first operator, to the second operator.

A positioning device includes at least one processor. The at least one processor detects a light source and a target object different from the light source in an image captured by an imager. A moving object has the imager and moves in a space. The at least one processor derives a position of the moving object in the space based on positions of the light source and the target object in the image and known positions of the light source and the target object in the space.

A method for capturing and deorbiting space debris includes: deploying a space debris capturing device in planetary orbit; receiving an initial target set including a first database of space debris targets that are within range of the space debris capturing device; performing a first algorithm to convert the initial target set to an accessible target set including a second database of space debris targets that are within range of the space debris capturing device; performing a second algorithm to convert the accessible target set to a final target set including a third database of space debris targets to be captured by the space debris capturing device capturing the first space debris target via a capture mechanism of the space debris capturing device; jettisoning the capture mechanism and the first captured space debris target into a decaying orbit; one of the remaining space debris targets of the third database; and positioning the space debris capturing device and the final captured space debris target into a decaying orbit.

Systems and methods for describing, simulating and/or optimizing spaceborne systems and missions. Configurations for spaceborne systems are generated and validated based on simulation output.

A Vehicle Based Independent Range System (VBIRS) (10) comprised of individual stacked chambered modules that function as a single integrated system that provides a self-contained space based range capability, and is comprised of a power module (12), an artificial intelligence/autonomous engagement/flight termination system module (20), a satellite data modem module system (30) and a navigation, communications and control module system (40), all of which interface with a VBIRS test and checkout system (52) and a weather data system (116). The artificial intelligence/autonomous engagement/flight termination system module (20) is comprised of an inherent artificial intelligence capability that envelopes and interchanges data with an autonomous engagement controller (22) that contains all missile/rocket autonomous cooperative engagement, destruct decision software and range safety algorithm parameters required for optimum mission planning. VBIRS employed aboard an aircraft or between any combination of launching systems allows that aircraft to launch a missile/rocket from any location on earth, whether the missile/rocket is singularly launched by itself or as a larger group of missiles/rockets launched in a salvo arrangement, while providing collaborative real-time targeting to occur directly between missiles/rockets in conjunction with other missile/rocket launch platforms or stand-alone mission control centers.