A method of achieving orbital rendezvous with a target satellite includes launching a spacecraft with a launch vehicle at an optimal time; steering the launch vehicle out-of-plane based on the orbital elements of the target satellite's orbit; and entering a predetermined rendezvous envelope of the target satellite before the target satellite completes one complete orbit from the target satellite's position at the optimal time.

Satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit satellite, and specifically to satellite systems and methods to perform rendezvous and docking between a servicer satellite and an on-orbit client satellite using electric propulsion thrusters. In one aspect, a servicer satellite with a set of thruster arms each attached to an electric propulsion thruster performs acceleration, deceleration, and steering maneuvers through six degree of freedom positioning of the thrusters, the same set of thruster arms and thrusters performing station keeping of the docked servicer-client satellite system.

A method of following a transfer orbit or a phase of orbital placement of a continuous-thrust space vehicle comprises the following steps: a) tracking at least one GNSS signal and using it to determine at least one pseudorange between the space vehicle and one or more GNSS satellites transmitting the signal; b) using an estimation model to jointly estimate a set of state parameters of the space vehicle comprising a plurality of position parameters, a plurality of velocity parameters and at least one thrust error parameter characterizing a discrepancy between an actual thrust force of the space vehicle and a nominal thrust force by taking the pseudorange or pseudoranges as input datum of the estimation model. An apparatus for the implementation of such a method is also provided.

Example methods and systems of deploying a constellation of spacecraft are described. An example method includes releasing a cluster of spacecraft from a launch vehicle at a first orbit, separating spacecraft in the cluster of spacecraft from each other to minimize overlap of visibility periods from a ground station, and raising each of the spacecraft as separated simultaneously in a synchronized ascent to a respective final orbit. An example system includes a cluster of spacecraft in orbit at a first orbit, and a ground station in communication with spacecraft of the cluster of spacecraft when the spacecraft of the cluster are visible to the ground station. The ground station commands each spacecraft to separate from each other and to raise in altitude as separated simultaneously in a synchronized ascent to a respective final orbit.

A satellite propelled by laser ablation comprises: a device for managing the attitude and the orbit of the satellite; a device for capturing and potentially for processing the target spaceborne body; a device for external communication; a laser ablation propulsion device comprising one or more lasers and a module for managing the one or more lasers that is suitable for determining the one or more laser beams to be generated on the captured target spaceborne body according to the movement desired for the satellite; and a device for visually inspecting the target spaceborne body.

A sampling system includes a sampler, a projector, a camera, an arm, and a controller with the sampler, projector, and camera being located at the distal end of the arm. The projector projects a reference mark including a line with a predetermined shape onto a ground surface and the camera captures images of the projected mark. The controller is configured to obtain the size of the projected line based on the camera images. The controller adjusts the projector height position based on the line size and specifies a sampling point for inserting the sampler based on the camera images of the projected mark.

Systems and methods for transferring, storing, and/or processing materials, such as fuel or propellant, in space, are disclosed. A representative system includes a flexible container that is changeable between a stowed configuration in which the flexible container is contained within a satellite, and a deployed configuration in which the flexible container extends away from the satellite. The system can include a tanker with a storage container to dock with and refuel a satellite. Another representative system includes a controller programmed with instructions that position a spacecraft with a storage container in a first orbit, transfer the spacecraft to a second orbit, dock the spacecraft with a satellite in the second orbit, transfer material between the storage container and the satellite, undock the spacecraft from the satellite, and, optionally, return the spacecraft to the first orbit. An androgynous coupling system with mechanical and fluid connectors facilitates docking and material transfer.

A spacecraft 10 includes wings 11 or an airframe 12 which generates lift in an atmosphere 2, a thruster 14 which accelerates or decelerates rotating speed in an orbit, an attitude controller 16 which controls an attitude of the airframe 12, and an orbital plane controller 18 which controls the orbital plane change. The orbital plane controller causes the spacecraft 10 to enter the earth's atmosphere 2 within a pre-change orbital plane Fb (A.fwdarw.B.fwdarw.C), changes the orbital plane by using the lift of the wings 11 or airframe 12 in the earth's atmosphere 2 (C.fwdarw.D.fwdarw.E), and then lifts the spacecraft 10 up to the post-change orbital altitude (E.fwdarw.F).

Energy efficient satellite maneuvering is described herein. One disclosed example method includes maneuvering a satellite that is in an orbit around a space body so that a principle sensitive axis of the satellite is oriented to an orbit frame plane to reduce gravity gradient torques acting upon the satellite. The orbit frame plane is based on an orbit frame vector.

A system and method for transferring a satellite from an initial orbit into a mission orbit. The method includes anchoring to the satellite of an external unit having a tank containing a reserve of propellants. The system includes an autonomous spacecraft having an electric propulsion module and a small internal reserve of propellants, located in a parking orbit close to the initial orbit. The spacecraft with the external unit attached to the satellite is docketed in an initial orbit, to produce a fluidic connection of the propellant tank of the external unit to the propulsion module of the spacecraft. The external unit and satellite is transferred into the mission orbit by the electric propulsion module of the spacecraft supplied with propellants directly from the external unit, thereby releasing the satellite into the mission orbit.