Drift-based rendezvous control system for controlling an operation of a spacecraft to rendezvous the spacecraft to a goal region over a finite time (FT) horizon. The system including accepting data including values of spacecraft states at a specified time period within the FT horizon. A processor at the specified time period selects a set of drift regions corresponding to a desired goal region at a location on an orbit where the target is located at the specified time period. Update a controller having a model of dynamics of the spacecraft with the accepted data. Formulate the set of drift regions as a penalty in a cost function of the updated controller. Generate control commands resulting in a real-time drift-based control policy where upon entering the drift region, the thrusters are turned off in order to minimize an amount of operation of the thrusters while rendezvousing with the desired goal region.

A system includes a satellite assembly. The assembly includes a plurality of satellite devices, where each satellite device includes a processor device, an impulse actuator, and a memory storing instructions. The instructions are executable by the processor device to access a sequence of waypoints. The sequence of waypoints identifies a first waypoint and is associated with formation of a distributed structure including the plurality of satellite devices. The instructions are further executable by the processor device to initiate movement of the satellite device toward the first waypoint at least by initiating activation of the impulse actuator.

In various embodiments, while a self-driving model operates a vehicle, a user monitoring subsystem acquires sensor data associated with a user of the vehicle and a vehicle observation subsystem acquires sensor data associated with the vehicle. The user monitoring subsystem computes values for a psychological metric based on the sensor data associated with the user. Based on the values for the psychological metric, a feedback application determines a description of the user over a first time period. The feedback application generates a dataset based on the description and the sensor data associated with the vehicle. Subsequently, a training application performs machine learning operation(s) on the self-driving model based on the dataset to generate a modified self-driving model. Advantageously, the dataset enables the training application to automatically modify the self-driving model to account for the impact different driving actions have on the user.

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.

The invention relates to small satellites capable to fly in formation (10), in particular nano- or picosatellites with a mass of 10 kg or less, for LEO applications, comprising a housing (12) and at least one plug-in board (14) arranged in the housing (12) with a predetermined functionality and a propulsion system (16) for generating a directed pulse in the direction of the flight trajectory T.sub.k. It is proposed that the small satellite (10) comprises an independent and autonomously working collision avoidance system (18), which is capable of adapting a trajectory correction T.sub.kk of the trajectory T.sub.k by the propulsion system (16), when a collision with an object (30) is expected. In a further independent aspect, the invention relates to a formation (100) composed of several small satellites capable to fly in formation (10), wherein a relative position and flight trajectory T.sub.k of each small satellite (10) is modifiable via the independently and autonomously working collision avoidance system (18).

A method for the safe release of artificial satellite in Earth orbit includes the steps of providing an orbital transport spacecraft able to move at orbital height and comprising a plurality of PODs for releasing satellites transported by the orbital transport spacecraft, housing said orbital transport spacecraft in a space launcher configured to reach an orbital height; generating a release signal and transmitting it to the orbital transport spacecraft to release the orbital transport spacecraft from the space launcher, in case of failure to release the orbital transport spacecraft or in case of breakdown of the orbital transport spacecraft after releasing from the space launcher, activating a safety subsystem of the orbital transport spacecraft to generate a POD activation sequence to release the satellites.

An attitude control apparatus (20) includes an ideal thrust direction calculator (22), an ideal attitude calculator (24), a target attitude calculator (26), and a torque calculator (28). The ideal thrust direction calculator (22) calculates an ideal thrust direction of a thruster. The target attitude calculator (26) calculates a target attitude that is the attitude of a satellite in which a deviation from an ideal attitude is minimized within a movement limitation of an attitude control actuator (14) while a panel surface faces the sun. The torque calculator (28) calculates a torque for turning the satellite from an actual attitude to the target attitude and transmits a torque instruction to the attitude control actuator (14).

An orbital trajectory planning system includes a first computer processor environment configured to preprocess data for providing to a physics-based n-body simulation model, the first computer processor environment including a graphical user interface (GUI) for receiving input from a user. The system also includes a second computer processor environment running at least partially trained neural network software that has been trained to perform nonlinear mapping of the output of the n-body simulation model to a result related to a proposed trajectory for a spacecraft, the second computer processor environment receiving input information from the first computer processor environment. Further the system relates to a third computer processor environment configured to receive data related to the output from the neural network of the second computer processor environment, the third computer processor environment providing user useable output through a GUI running on the third computer processor environment.

A system detects a maneuver of at least one space object by receiving a first data set relating to orbital characteristics of at least one space debris object. The system trains a model, using the first data set, in order to model orbital behaviors of the at least one space debris object. The system then receives a second data set relating to orbital characteristics of the at least one space object, and detects a maneuver of the at least one space object using the trained model and the second data set.

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.