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.

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.

Cell-based systems may interlock in a reconfigurable configuration to support a mission. Space systems, for example, of a relatively large size may be assembled using an ensemble of individual “cells”, which are individual space vehicles. The cells may be held together via magnets, electromagnets, mechanical interlocks, etc. The topology or shape of the joined cells may be altered by cells hopping, rotating, or “rolling” along the joint ensemble. The cells may be multifunctional, mass producible units. Rotation of cell faces, or of components within cells, may change the functionality of the cell. The cell maybe collapsible for stowage or during launch.

Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

Vehicles with control surfaces and associated systems and methods are disclosed. In a particular embodiment, a rocket can include a plurality of bidirectional control surfaces positioned toward an aft portion of the rocket. In this embodiment, the bidirectional control surfaces can be operable to control the orientation and/or flight path of the rocket during both ascent, in a nose-first orientation, and descent, in a tail-first orientation for, e.g., a tail-down landing. Launch vehicles with fixed and deployable deceleration surfaces and associated systems and methods are also disclosed.

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.

A: spacecraft attitude control system comprising •at least one attitude control device (2), the attitude control device comprising •first and second magnets (3, 4) having magnetic dipole moments M1 and M2 respectively, each magnet (3, 4) comprising a north pole face and a south pole face; •the magnets (3, 4) being spaced apart along a length axis by a gap, •for each magnet the pole face closest to the other magnet being termed the closest face, the magnets being arranged with the closest faces being of the same pole; •the first magnet 3 being connected to a rotation mechanism (7), the rotation mechanism being adapted to rotate the first magnet about first and second axes (8, 9), none of the first axis (8), second axis (9) and magnetic dipole moment M1, M2 of the first magnet (3) being parallel to the other.

A satellite communication system in which a plurality of satellites each transit about the Earth in a common mid-Earth orbit. The orbit may be configured such that each satellite of the plurality of satellites follows a common, repeating ground track relative to the surface of the Earth. In turn, one or more repeating sky tracks may be defined relative to at least one ground station such that the ground station is in continuous communication with at least one of the plurality of satellites. In an example, a ground station may have visibility to a plurality of repeating sky tracks such that a plurality of discreet communication channels is provided that use different satellites for communication with user terminals of the satellite communications system.

An orbital analysis unit (431) of a collision avoidance assist business device identifies a mega-constellation satellite group formed in an orbital altitude which the mega-constellation satellite group is anticipated to pass during a flight of an unsteady-operation space object. An announcement unit (432) of the collision avoidance assist business device announces a danger alarm and orbital information of the unsteady-operation space object, to a mega-constellation business device which manages the mega-constellation satellite group. A collision analysis unit (411) of a satellite mega-constellation business device analyzes collision of the unsteady-operation space object with an individual satellite constituting the mega-constellation satellite group. A countermeasure formulating unit (412) of the satellite constellation business device formulates a collision avoidance countermeasure when collision is predicted.

A satellite comprises thrusters disposed with the firing directions each facing away from the mass center of satellite and different from each other. A control amount calculator calculates control amounts of the mean orbital elements from the mean orbital elements and the temporal change rates of the mean orbital elements set by an orbit determiner, and the target values. A distributor calculates firing timings and firing amounts of the thrusters for realizing the control amounts of the mean orbital elements by expressing a motion of satellite with orbital elements, solving an equation taking into account coupling of an out-of-plane motion and an in-plane motion due to thruster disposition angles and thruster firing amounts at multiple times, and combining one or more thruster firings controlling mainly an out-of-the-orbit-plane direction and one or more thruster firings controlling mainly an in-the-orbit-plane direction.